Table of Contents - Space Flight Mechanics Committee

Transcription

Draft Version January 2, 2012 6:44:00 PM
Table of Contents General Information ........................................................................................................................ 3 Registration ..................................................................................................................................... 3 Schedule of Events .......................................................................................................................... 4 Francis Marion Hotel Layout .......................................................................................................... 6 Special Events ................................................................................................................................. 7 Early Bird Reception................................................................................................................... 7 Awards Ceremony and Dirk Brouwer Award Lecture ............................................................... 7 Dirk Brouwer Award Honoree.................................................................................................... 7 Offsite Event – USS Yorktown................................................................................................... 8 Conference Location ....................................................................................................................... 9 The Francis Marion Hotel ........................................................................................................... 9 Transportation Info ..................................................................................................................... 9 Driving Directions ...................................................................................................................... 9 Arrival Information ................................................................................................................... 10 Restaurants ................................................................................................................................ 10 Recreation ................................................................................................................................. 12 Area Map .................................................................................................................................. 14 Additional Information ................................................................................................................. 15 Speaker Orientation .................................................................................................................. 15 Volunteers ................................................................................................................................. 15 Presentations ............................................................................................................................. 15 Preprinted Manuscripts ............................................................................................................. 15 Conference Proceedings............................................................................................................ 15 Satisfaction Survey ................................................................................................................... 16 Committee Meetings ................................................................................................................. 16 Session 1: Formation Flying I ..................................................................................................... 17 Session 2: Space Situational Awareness ..................................................................................... 20 Session 3: Attitude Determination............................................................................................... 23 Session 4: Asteroid and Near-Earth Object Missions I ............................................................... 26 Session 5: Dynamical Systems Theory I ..................................................................................... 28 Session 6: Formation Flying II .................................................................................................... 31 Session 7: Optimal Control ......................................................................................................... 34 Session 8: Trajectory Optimization I ........................................................................................... 36 Session 9: Attitude Dynamics and Control I ............................................................................... 38 Page 1
22nd AAS/AIAA Space Flight Mechanics Meeting Draft Version January 2, 2012 6:44:00 PM
Session 10: Flight Dynamics Operations .................................................................................... 41 Session 11: Dynamical Systems Theory II .................................................................................. 43 Session 12: Spacecraft Guidance, Navigation, and Control I ..................................................... 45 Session 13: Orbit Determination I ............................................................................................... 47 Session 14: Lunar and Planetary Missions .................................................................................. 49 Session 15: Numerical and Analytical Trajectory Techniques ................................................... 51 Session 16: Asteroid and Near-Earth Object Missions II ............................................................ 53 Session 17: Trajectory Optimization II ....................................................................................... 55 Session 18: Attitude Dynamics and Control II ............................................................................ 57 Session 19: Orbital Debris ........................................................................................................... 59 Session 20: Earth Orbital Missions ............................................................................................. 61 Session 21: Orbit Determination II.............................................................................................. 63 Session 22: Spacecraft Guidance, Navigation, and Control II .................................................... 65 Author Index ................................................................................................................................. 67 Record of Meeting Expenses ........................................................................................................ 69 Conference Satisfaction Survey .................................................................................................... 71 22nd AAS/AIAA Space Flight Mechanics Meeting Page 2 Draft Version January 2, 2012 6:44:00 PM
22ND AAS/AIAA SPACE FLIGHT MECHANICS MEETING
CONFERENCE INFORMATION
GENERAL INFORMATION
Welcome to the 22nd Space Flight Mechanics Meeting, hosted by the American Astronautical
Society (AAS) and co-hosted by the American Institute of Aeronautics and Astronautics (AIAA),
January 29 – February 2, 2012. This meeting is organized by the AAS Space Flight Mechanics
Committee and the AIAA Astrodynamics Technical Committee, and held at the Francis Marion
Hotel, 387 King Street, Charleston, South Carolina 29403. Phone: 843-722-0600.
REGISTRATION
Registration Site (https://aas.pxi.com/registration/reg)
In order to encourage early registration, we have implemented the following conference registration
rate structure: Register by 10 Jan 2012 and save $50!
Category
Full - AAS or AIAA Member
Full - Non-member
Retired*
Student*
*does not include proceedings CD
Early Registration
(through 10 Jan 2012)
$450
$550
$125
$125
Late Registration
$500
$600
$175
$175
The USS Yorktown dinner on Tuesday evening is included with all registrations. Guest tickets for
the dinner may be purchased for $50. More information about the Yorktown dinner is included
below.
A conference registration and check-in table will be located on the Mezzanine Level of the Francis
Marion Hotel and will be staffed according to the following schedule:
Sunday Jan. 29
Monday Jan. 30
Tuesday Jan. 31
Wednesday Feb. 1
Thursday Feb. 2
3:00 PM - 6:00 PM
7:30 AM - 2:00 PM
8:00 AM - 2:00 PM
8:00 AM – 2:00 PM
8:00 AM – 10:00 AM
We will accept registration and payment on-site for those who have not pre-registered online, but we
strongly recommend online registration before the conference in order to avoid delays (see URL
above). Pre-registration also gives you free access to pre-print technical papers. On-site payment by
credit card will be only through the AAS website using a computer at the registration table. Any
checks should be made payable to the “American Astronautical Society.”
Page 3 22nd AAS/AIAA Space Flight Mechanics Meeting Draft Version January 2, 2012 6:44:00 PM
SCHEDULE OF EVENTS
Start
End
Registration
Registration Desk
6pm
9pm
Early Bird Reception
Colonial
Start
7am
7:30am
8am
8am
8am
9:40am
12:15
1:30pm
8am
2pm
12:10pm
11:45am
12:10am
10:05am
1:30pm
5:15pm
1:30pm
1:30pm
1:30pm
3:10pm
5:40pm
5:40pm
4:50pm
3:35pm
Start
End
Tuesday
31 January
Room
6pm
Day
Day
Function
3pm
Monday
30 January
Sunday
29
January
Day
End
7am
8am
8am
8am
8am
9:40am
Noon
8am
2pm
11:45am
11:45am
11:45am
10:05am
1:30pm
1:30pm
1:30pm
4:50pm
4:25pm
1:30pm
3:10pm
5:00pm
4:50pm
3:35pm
6:00pm
6pm
9pm
Function
Speakers Breakfast
Registration
Session 1: Formation Flying I
Session 2: Space Situational Awareness
Session 3: Attitude Determination
Morning Break
Joint Technical Committee Lunch
Session 4: Asteroid and Near-Earth Object
Missions I
Session 5: Dynamical Systems Theory I
Session 6: Formation Flying II
Session 7: Optimal Control
Afternoon Break
Function
Speakers Breakfast
Registration
Session 8: Trajectory Optimization I
Session 9: Attitude Dynamics and Control I
Session 10: Flight Dynamics Operations
Morning Break
AAS Space Flight Mechanics Committee
Lunch
Session 11: Dynamical Systems Theory II
Session 12: Spacecraft Guidance, Navigation,
and Control I
Session 13: Orbit Determination I
Afternoon Break
Awards Ceremony and Dirk Brouwer Award
Lecture
Offsite Event
22nd AAS/AIAA Space Flight Mechanics Meeting Room
Colonial
Registration Desk
Carolina A
Carolina B
Calhoun
Prefunction A
Pinckney
Carolina A
Carolina B
Calhoun
Colonial
Prefunction A
Room
Pinckney
Registration Desk
Carolina A
Carolina B
Calhoun
Prefunction A
Pinckney
Carolina A
Carolina B
Calhoun
9th Floor Prefunction
Colonial
USS Yorktown
Page 4 Draft Version January 2, 2012 6:44:00 PM
Wednesday
1 February
Day
Thursday
2 February
Day
Start
End
7am
8am
8am
8am
8am
2pm
11:45am
11:20am
8am
11:45am
9:40am
Noon
10:05am
1:30pm
1:30pm
1:30pm
1:30pm
3:45pm
5:15pm
5:15pm
5:15pm
5:15pm
5:15pm
5:15pm
4:10pm
6:15pm
6:15pm
6:15pm
Start
End
7am
8am
8am
8am
8am
8am
10am
11:20am
10:55am
11:20am
9:40am
10:05am
Function
Speakers Breakfast
Registration
Session 14: Lunar and Planetary Missions
Session 15: Numerical and Analytical
Trajectory Techniques
Session 16: Asteroid and Near-Earth Object
Missions II
Morning Break
AIAA Astrodynamics Technical Committee
Lunch
Session 17: Trajectory Optimization II
Session 18: Attitude Dynamics and Control II
Session 19: Orbital Debris
Afternoon Break
Conference Administration Subcommittee
Technical Administration Subcommittee
Website Administration Subcommittee
Function
Speakers Breakfast
Registration
Session 20: Earth Orbital Missions
Session 21: Orbit Determination II
Session 22: Spacecraft Guidance, Navigation,
and Control II
Morning Break
Room
Pinckney
Registration Desk
Carolina A
Carolina B
Calhoun
Prefunction A
Pinckney
Carolina A
Carolina B
Calhoun
Prefunction A
Carolina A
Carolina B
Calhoun
Room
Laurens
Registration Desk
Carolina A
Carolina B
Calhoun
Prefunction A
FRANCIS MARION HOTEL LAYOUT
Carolina B Carolina A Calhoun Room Colonial Room
Presentation Rooms: Carolina A Carolina B Calhoun Colonial 22nd AAS/AIAA Space Flight Mechanics Meeting Page 6 Draft Version January 2, 2012 6:44:00 PM
SPECIAL EVENTS
EARLY BIRD RECEPTION
Sunday, 29 January
Location:
6 – 9:00 pm
Colonial
AWARDS CEREMONY AND DIRK BROUWER AWARD LECTURE
Tuesday, 31 January
Location:
5 – 6:00 pm (ceremony and lecture)
Colonial (ceremony and lecture)
Review of Quadrilateralized Spherical Cube and
Views of Future Work on Spacecraft Collisions
The first topic concerns an efficient Earth database structure for rapidly storing and retrieving highresolution remotely-sensed global data. This formulation is based on the concept of a
"Quadrilateralized Spherical Cube" (QLSC). It was implemented for global usage by the Navy in
1977, and since then it has been adopted by other government agencies such as NASA in various
applications, the first being the Cosmic Background Explorer (COBE). For the past three decades
QLSC, or some derivative of it, has been used by astronomers and astrophysicists for star-mapping
and radiation-cataloging to the celestial sphere. Atmospheric and ocean scientists use it for database
structure because of its exceptional efficiency in data archiving and retrieval. The QLSC and its
associated Quadtree are presently used by computer scientists in many geographical information
systems for data processing. It is also used in map projections because there are no singularities at
the poles or elsewhere, as is the case with other equal-area mapping schemes.
The second topic concerns the modeling and computation of spacecraft collision probability for the
case in which the statistics no longer obey Gaussian distributions, or the case where the space debris
is so sparse as not to be amenable to description using Poisson statistics. An outline is given for the
computation of collision probability of close encounters when the probability density functions are
non-Gaussian. A discussion is included on the estimation of debris density when there are
pronounced inhomogenieties in the spatial distribution of the debris.
DIRK BROUWER AWARD HONOREE
Ken Chan obtained his Bachelor’s degree from the University of
Pennsylvania, and his Doctoral degree from Princeton University. He
taught at the Catholic University of America in the Space Science and
Applied Physics Department from 1966 to 1970.
For NASA/GSFC and NOAA/NESS, Ken solved many orbit and attitude
problems which required immediate attention. He was instrumental in
solving various satellite navigation problems associated with TIROS-N and
the first series of GOES satellites.
For the Navy, he formulated and developed an efficient Earth database structure for rapidly storing
and retrieving high-resolution remotely-sensed global data. This formulation was based on the
concept of a "Quadrilateralized Spherical Cube" (QLSC). For the Air Force, he has performed many
leading-edge studies related to spacecraft collision probabilities. He is the author of the book
Spacecraft Collision Probability published by AIAA in 2008. One of his algorithms has been
adopted to estimate the lightning strike probability by the 45th Weather Squadron at the Kennedy
Space Center and the Cape Canaveral Air Force Station. He also contributed to the book Multiscale
Optimization Methods and Applications, published by Springer-Verlag in 2006. His chapter in this
book on the simple criteria for the intersection of ellipsoids has been used in the simulation of the
transport, collision and aggregation of blood cells in various types of blood flows.
OFFSITE EVENT – USS YORKTOWN
Tuesday, 31 January
Location
6:15 - 9:00 pm Dinner and Ship Tour
USS Yorktown
40 Patriots Point Road, Mount Pleasant, SC 29464
The USS Yorktown (CV-10) was the tenth aircraft carrier to serve in the United States Navy. The
888-foot Yorktown displaced 27,100 tons during World War II and carried a crew of 380 officers,
3,088 enlisted men, and an air group of 90 planes. She also served in the Vietnam War in the 1960s
and recovered the Apollo 8 astronauts in 1968. Decommissioned two years later, the Yorktown was
towed from New Jersey to Charleston in 1975 to become the centerpiece of Patriots Point Naval and
Maritime Museum. Patriots point also offers a diesel powered submarine, “Clamagore”, and
destroyer, “Laffey”. Vintage military aircraft and weapons are also on display. For more
information, visit the Patriots Point website: http://www.patriotspoint.org.
Docents will be available to give guided tours during the event, and there are also several marked
self-guided tours. The flight simulator will be open for guests who wish to try its three simulations.
A “Lowcountry style” buffet dinner will be served in the Hangar Bay area, with an open bar. The
menu includes local deviled crabs, barbequed pulled pork, red rice, coleslaw, corn on the cob, green
beans almondine, corn bread muffins, and banana pudding. Guests with any dietary restrictions
should contact Matt Berry at mberry@agi.com by January 20th so the caterer can be informed.
All conference registrations will receive an event ticket. Adult guest tickets will be available prior to
January 23, 2012 for $50 each. Tickets for children from 6-12 are available for $25. Children under
6 are free. Please contact the conference chairs if interested in guest tickets prior to January 23,
2011.
Buses have been arranged to provide transportation to the Yorktown. Buses will be departing the
hotel at 6:15 PM. Please meet in the hotel lobby prior to this time to board the buses.
22nd AAS/AIAA Space Flight Mechanics Meeting Page 8 Draft Version January 2, 2012 6:44:00 PM
CONFERENCE LOCATION
THE FRANCIS MARION HOTEL
Francis Marion Hotel
387 King Street
Charleston, South Carolina 29403 USA
Phone: 1-843-722-0600
Fax: 1-843-853-2186
Toll-free: 1-877-756-2121
http://www.francismarionhotel.com
The Conference rate for the conference is $137 (100% of
the current government per diem) plus applicable taxes.
Currently, the tax rate is 12.5% plus a $1.00 per room, per night destination fee. Please request the
AAS/AIAA Space Flight Mechanics Meeting rate. The deadline for securing the conference rate at
the hotel is January 9, 2012. The conference rate is valid for 3 nights before and after the conference
dates, subject to availability.
Complimentary internet access in guest rooms and meeting space is available to all conference
attendees. Complimentary access to the hotel’s fitness center, located on the ground floor, is
included for all guests.
TRANSPORTATION INFO
The Charleston International Airport, www.chs-airport.com, is 12 miles from the Francis Marion
hotel. The airport is served by multiple major carriers, and has direct flights from 15 locations.
The airport has a negotiated rate with shuttle services to bring passengers to downtown hotels. The
rate for these shuttles is $12 per person. These shuttles are located outside at the kiosk across from
the Baggage Claim area of the airport. A private taxi costs approximately $26-30 to the downtown
area. These are also available at the kiosk.
DRIVING DIRECTIONS
From Airport:  Exit airport on International Drive and follow signs for I-526 to Mt. Pleasant
 From I-526 follow signs for I-26 East to Charleston.
 Travel on I-26 to the end (Meeting Street Exit)
 Turn right onto Meeting Street
 Stay on Meeting Street in the right hand lane for 0.6 miles
 Pass the Charleston Visitor’s Center and turn right at the light, which is John Street.
 Take John Street one block to King Street and turn left on King Street. The Francis Marion
Hotel is on the right.
From the North:  I-95 South to I-26 East
 Follow Driving directions from Airport (3rd bullet)
From the South:  I-95 North to US Hwy 17 North.
 Follow Hwy 17 (Savannah Hwy) North and cross the Ashley River Bridge.
 Hwy 17 will make a sharp turn to the left as it forks with Cannon Street. Follow the sign for
Cannon Street.
 Take Cannon Street until it ends at King Street. Turn right onto King Street.
 The Francis Marion is approximately 6 blocks on the right.
ARRIVAL INFORMATION
CheckIn and Checkout  Check-in: 4:00 PM
 Check-out: 12:00 PM
Departure dates of each guest will be verified upon check-in. At that time, the guest may make
adjustments to the actual departure date. After check-in, any individual attendee departing prior to
their departure date will be charged an early departure fee of 50% of the room rate plus sales tax.
Parking Valet parking is available at a rate of $17.00 plus tax per night, automatically billed to your room.
Self-parking is available in the City Garage located next to the hotel, at $12 per 24-hour period
payable in cash to the garage attendant.
RESTAURANTS
The following options are within a few blocks of the hotel. Please see the concierge desk for a
complete list of local restaurants including more fine dining and upscale choices.
Hotel The Swamp Fox Restaurant and Bar. Classic southern flavor in a comfortable atmosphere.
Starbucks Coffee Shop. Located at street level.
Quick and Casual Boone’s Bar & Grill, 345 King Street. Big menu of burgers, sandwiches & appetizers.
King Street Grill, 304 King Street. Upscale sports grill with fabulous build your own salads.
Closed for Business, 453 King Street. Great burgers, salads and sandwiches.
O’Malley’s Bar & Grille, 549 King Street. Irish pub and sports bar with great tavern food.
Midtown Bar & Grill, 559 King Street. Southern casual cuisine with house smoked BBQ, burgers
& wraps.
HoM, 563 King Street. Burger boutique and ping pong lounge.
Five Guys Burgers & Fries, 364 King Street.
MidRange Joe Pasta, 428 King Street. Pasta with you-pick-it sauces & toppings. Italian/American
sandwiches, salads, appetizers.
Sermet’s Corner, 276 King Street. Inventive Mediterranean dishes and wines.
Basil Restaurant, 460 King Street. Refined Thai cuisine with only the finest ingredients.
The Kickin’ Chicken, 350 King Street. Great sandwiches, salads, and such. Fried food at its best
and buffalo wings too.
Mellow Mushroom, 309 King Street. Gourmet pizzas, calzones, hoagies, and salads. Also, a large
beer selection.
Moe’s Southwest Grill, 381 King Street. Innovative Southwest/Mexican fare.
Jim & Nick’s BBQ, 288 King Street. Pulled pork piled high. Sandwiches, burgers and salads.
Juanita Greenberg’s Nacho Royale, 439 King Street. Mexican, with interesting twists.
Monza, 451 King Street. Neapolitan style specializing in pizza, pastas & salads. Everything is
made in house.
39 Rue De Jean, 39 John Street (one block to the left (North) exiting on King Street). French
Bistro—great mussels & sushi bar.
Fish, 422 King Street. Fresh local seafood served in an innovative fashion.
Virginia’s, 412 King Street. Great Southern comfort fare.
Coast, 39 John Street (one block to the left (North) exiting on King Street). Fresh seafood, with
island flair!
Tasty Thai & Sushi, 350 King Street. Spicy Thai food and full sushi bar.
Chai’s Lounge & Tapas, 462 King Street. Fusion-style tapas in an awesome Asian-inspired space.
Jestine’s Kitchen. 251 Meeting Street. Southern Home Cooking
Il Cortiel del Re, 194A King Street. Northern Italian fare—very fresh and delicious!
Fine Dining / Upscale Charleston Grill, 224 King Street (Located in Charleston Place). World-class dining with
imaginative cuisine.
The Macintosh, 479B King Street. Upscale, hip atmosphere with exceptional locally inspired fare.
La Fourchette, 432 King Street. Hearty French peasant food, wonderfully prepared.
O-Ku, 463 King Street. Celebrates authentic traditional Japanese cuisine.
Hall’s Chop House, 434 King Street. Prime steaks, lamb and veal chops, seafood specials and
fancy Southern-inspired sides.
RECREATION
The suggestions below are a partial list of the many things to do and see in Charleston. For more
information and suggestions visit the concierge desk. The Charleston visitor’s bureau also has a very
informative website: www.charlestoncvb.com/visitors/.
Tours Carriage and walking tours of Charleston are available from a variety of tour operators. In addition,
many of the historic homes in Charleston offer tours. See the concierge or the visitor’s bureau
website for a complete list of tour operators.
Attractions and Landmarks Fort Sumter/Spiritline Cruises, 360 Concord Street. (843) 881-7337.
Departs daily from Liberty Square and Patriot’s Point. www.fortsumtertours.com.
South Carolina Aquarium, 100 Aquarium Warf. (843) 720-1990, www.scaquarium.org.
Drayton Hall, 3380 Ashley River Road, West Ashley. (843) 769-2600, www.DraytonHall.org.
Middleton Place, 4300 Ashley River Road, West Ashley. (843) 556-6020,
www.middletonplace.org.
Old Exchange Building and Provost Dungeon, 122 East Bay Street. (843) 727-2165.
300 years of pirates, patriots, presidents, and preservation. www.oldexchange.com.
Boone Hall Plantation, 1235 Long Point Road, Mt. Pleasant. (843)884-4371,
www.boonehallplantation.com.
Magnolia Plantation and Gardens, 3550 Ashley River Road, West Ashley. (843)571-1266,
www.magnoliaplantation.com.
Battery Park / White Point Gardens.
Located at the southern point of the Charleston peninsula, the park features a display of civil war
cannons and offers views of Charleston Harbor and Fort Sumter.
Museums Charleston Museum, 360 Meeting Street. (843)722-2996.
America’s First and Oldest Museum. www.charlestonmuseum.org.
Gibbes Museum of Art, 135 Meeting Street. (843)722-2706.
Features one of the finest collections of American art in the southeast. www.gibbesmuseum.org.
Children’s Museum of the Lowcountry, 25 Ann Street. (843) 853-8962. www.explorecml.org.
Four blocks from the hotel. Features an art room, pirate ship, castle, and more.
Shopping City Market, Meeting and Market Streets. Traditionally open 9am-5pm daily. Gift Shops,
Souvenir Shops, Eateries, and Bars on the North and South Market sides.
Upper King Street. Upscale Boutique Shopping.
Lower King Street. Popular Chain Stores & Small Boutiques.
Tanger Outlet Center (North Charleston), 4840 Tanger Outlet Blvd. (843) 529-3095.
Golf Patriots Point Links, 1 Patriots Point Road, Mount Pleasant. 843-881-0042,
www.patriotspointlinks.com.
Wild Dunes Resort Golf, 5757 Palm Blvd, Isle of Palms. (843) 886-2164, www.wilddunes.com.
AREA MAP
Additional maps are located at www.charlestoncvb.com/visitors/travel_support/maps.html.
ADDITIONAL INFORMATION
SPEAKER ORIENTATION
On the day of their sessions, authors making presentations meet with their session chairs at 7:00 am.
Breakfast will be served. Check the schedule at the beginning of the program for the location of the
speaker’s breakfast each morning. Speaker attendance is mandatory.
VOLUNTEERS
Volunteers that would like to staff the registration table may sign up at the registration table.
PRESENTATIONS
Each presentation is limited to 20 minutes. An additional five minutes is allotted between
presentations for audience participation and transition. Session chairs shall maintain the posted
schedule to allow attendees the option of joining a parallel session. Each room is equipped with a
laser pointer, an electrical outlet, and a video projector that can be driven by a computer. Presenters
shall coordinate with their Session Chairs regarding the computing equipment, software, and media
requirements for the session; however, each presenter is ultimately responsible for having the
necessary computer and software available to drive the presentation. Microsoft PowerPoint and
PDF are the most common formats.
"No-Paper, No-Podium" Policy Completed manuscripts shall be electronically uploaded to the
submission site before the conference, limited to 20 pages in length, and conform to the AAS
conference paper format. If the completed manuscript is not contributed on time, it will not be
presented at the conference. If there is no conference presentation by an author, the contributed
manuscript shall be withdrawn.
PREPRINTED MANUSCRIPTS
Physical copies of preprinted manuscripts are no longer available or required for the Space Flight
Mechanics Meetings or the Astrodynamics Specialist Conferences. Electronic preprints are available
for download at least 72 hours before the conference at https://aas.pxi.com/registration/reg/ for
registrants who use the online registration system. The hotel provides conference guests with
complimentary wireless internet access in guest rooms and the conference meeting space.
Registrants without an internet-capable portable computer, or those desiring traditional paper copies
should download and print preprint manuscripts before arriving at the conference.
CONFERENCE PROCEEDINGS
All full registrants will receive a CD of the proceedings mailed to them after the conference (extra
copies are available for $45 during the conference). However, the hardbound volume of Advances in
the Astronautical Sciences covering this conference will be available to attendees at a reduced prepublication cost, if ordered at the registration desk. After the conference, the hardbound proceedings
will more than double in price, although authors will still receive a special 50% discount off the
post-conference rate even if they delay their order until after the conference. Cost of Proceedings:

Conference Rate
$250 domestic ($300 international)
Post-Conference Rate
$520 (approx.)
Authors (post-conference)
$260 (approx.)
Although the availability of hardcopy proceedings enhances the longevity of your work and elevates
the importance of your conference contribution, please note that conference proceedings are not
considered an archival publication. Authors are encouraged to submit their manuscripts after the
meeting to one of the relevant journals, such as:
Journal of Guidance, Control and Dynamics
Editor-in-Chief: George T. Schmidt, Massachusetts Institute of Technology
Manuscripts can be submitted via: www.writetrack.net/aiaa/
Journal of Spacecraft and Rockets
Editor-in-Chief: E. Vincent Zoby, NASA Langley Research Center
Manuscripts can be submitted via: www.writetrack.net/aiaa/
Journal of the Astronautical Sciences
Editor-in-Chief: Kathleen C. Howell
School of Aeronautics and Astronautics
3233 Armstrong Hall
Purdue University
West Lafayette, IN 47907
(765) 494-5786
howell@purdue.edu
SATISFACTION SURVEY
Registrants are highly encouraged to record their level of satisfaction and conference preferences in
an anonymous survey taken throughout the time of the conference. Please return the survey form
included in this program to the registration table before departing from the conference.
COMMITTEE MEETINGS
Committee seating is limited to committee members and invited guests. Committee and
subcommittee meetings will be held according to the schedule at the beginning of the program.
Jan 30, 2012
Carolina A
Session 1: Formation Flying I
Chair: Dr. Aaron Trask, Apogee Integration
08:00
AAS 12 - 100
Early Formation Design using a Geometrical Approach
Jason Tichy, a.i. solutions, Inc.
High-fidelity spacecraft formation design requires numerical integration of ordinary differential
equations that incorporate perturbations from atmospheric drag, solar radiation pressure, other
celestial bodies, as well as effects from a non-spherical Earth. Numerically based optimization
algorithms are often required to develop solutions that are consistent with these perturbations, and
incremental improvements to model fidelity generates little insight into the overall design space
within the context of mission feasibility and requirements. A new method for formation design, based
on geometrical Keplerian ellipses, is introduced to facilitate the understanding of the design space and
alleviate numerical complexity.
08:25
AAS 12 - 101
Effects of Staggering Formation Maneuvers on the Magnetospheric MultiScale
(MMS) Mission Trajectories
Khashayar Parsay and Laurie Mann, a.i. solutions, Inc.; Trevor Williams, NASA
Goddard Space Flight Center
To execute a formation maneuver during the MMS mission, each spacecraft employs a two-burn
transfer to achieve its desired state. Because of communication limitations, only one spacecraft can
fire its thrusters at any given time. Therefore, the maneuvers are staggered 75 minutes apart resulting
in having two maneuver sets, one that includes all the first maneuvers and one that includes all the
second maneuvers. The selection of the staggering sequence has a significant impact on the fuel and
the spacecraft close approach profile. This paper examines this impact for Phase I of the mission.
08:50
AAS 12 - 102
Formation Maneuver Planning for Collision Avoidance and Direction Coverage
Liam M. Healy and C. Glen Henshaw, Naval Research Laboratory
We develop techniques for determining the maneuvers needed to keep an inspector vehicle close to
the host without colliding while being able to inspect the desired faces of the host. We use apocentral
coordinates and the geometric relative orbital elements developed earlier. We separate change in
relative velocity (maneuvers) into radial and cross-track components and use a waypoint technique to
plan the maneuvers. By considering maneuvers that only preserve the relative orbital plane and those
that only change the cross-track component of relative velocity, we simplify maneuver planning while
maintaining passive safety.
09:15
AAS 12 - 103
A Lyapunov-Floquet Generalization of the Hill-Clohessy-Wiltshire Equations
Ryan E. Sherrill and Andrew J. Sinclair, Auburn University; T. Alan Lovell, Air
Force Research Laboratory
The relative motion between chief and deputy satellites in close proximity in orbits of arbitrary
eccentricity can be described by linearized time-varying equations of motion. The linear timeinvariant Hill-Clohessy-Wiltshire equations are typically derived from these equations by assuming
the chief satellite is in a circular orbit. However, a Lyapunov-Floquet transformation relates the
linearized equations of relative motion to the Hill-Clohessy-Wiltshire equations through a periodic
coordinate transformation without requiring an eccentricity assumption. This transformation is based
on the invariant form of the Tschauner-Hempel equations, and evaluates the Hill-Clohessy-Wiltshire
equations at a virtual time.
09:40
Break
10:05
AAS 12 - 104
Impulsive Stabilization and Re-Configuration Strategies for Two-Craft
Coulomb Formations
Drew R. Jones, The University of Texas at Austin
Charged spacecraft formations are being investigated for a variety of missions, since propellant less
control via charge modulation is highly advantageous. Unfortunately, charge control has its
complications and has often been supplemented with inertial thrusting. This research seeks formation
maneuvering methods that better exploit the natural system dynamics and charge modulation, for the
dynamically unstable, two-craft Hill frame equilibria, which exist in the Keplerian problem. A stationkeeping method is presented that eliminates unstable modal perturbations by initiating periodic,
impulsive thrusting and charge changes. Finally, configuration transfers are considered where nearly
intersecting invariant manifolds are differentially corrected using impulsive charge changes.
10:30
AAS 12 - 105
Effective Coulomb Force Modeling in a Space Environment
Laura A. Stiles, Carl R. Seubert, and Hanspeter Schaub, University of Colorado at
Boulder
Coulomb formation flight is an emerging concept that utilizes electrostatic forces to maintain a
formation of close proximity spacecraft. This paper explores to what extent the plasma environment
affects the magnitude of the Coulomb force. This is achieved through the use of analytic models that
bound the extent of Coulomb forces as well as fitting an effective Debye length to numerical solutions
to more accurately, yet still efficiently, calculate the force. Effective Debye lengths at GEO and LEO
conditions are examined and are found to be significantly larger. These results increase feasibility of
Coulomb applications in dense LEO plasmas.
10:55
AAS 12 - 106
Multi-Sphere Modeling for Electrostatic Forces on Three-Dimensional
Spacecraft Shapes
Daan Stevenson and Hanspeter Schaub, University of Colorado at Boulder
The use of electrostatic (Coulomb) actuation is attractive for formation flying, but current analytical
electrostatic force models do not capture any orientation dependent forces or torques on generic
spacecraft geometries as encountered during very close operations. The Multi Sphere Model (MSM)
uses a collection of finite spheres to represent a complex shape and analytically approximate the
Coulomb interaction with other charged bodies. Using the MSM, six degree of freedom electrostatic
simulations of relative spacecraft motion are possible in real time, which is crucial for the
development of robust relative position and orientation control algorithms in local space situational
awareness applications.
11:20
AAS 12 - 107
Analysis on Spacecraft Formation Flying in Elliptic Reference Orbits
Jonghee Bae and Youdan Kim, Seoul National University
Formation analysis is performed for the periodic relative motion between two spacecraft in Keplerian
elliptic orbits. While the relative motion in the circular orbit has an ellipse in the in-plane, the follower
spacecraft in the elliptical orbit does not have an ellipse of fixed eccentricity due to the eccentricity of
the reference orbit. In this study, the spacecraft formation flying is analyzed and the instantaneous
eccentricity of the relative motion is derived to describe the natural periodic relative motion.
Numerical simulations are demonstrate the formation trajectories, and finally the desired constraints
are provided for the formation design.
11:45
AAS 12 - 108
Comparison and Application Analysis of Classical Relative Motion Models
Jianfeng Yin and Chao Han Beihang University
In this paper several classical relative motion models are compared for a wide variety of conditions.
The accuracy and applicability of these models are analyzed. The models involved in this
investigation are the familiar Hill’s equations, Lawden’s equations, Alfriend’s geometric method, a
new model based on a new set of relative orbit elements and a numerical propagator. The effects of
variations of orbital parameters, orbit types, the relative orbit size and the reference orbit eccentricity
are analyzed. The four relative model’s capability of formation design is also researched. The
proposed method and conclusions are validated through numerical examples.
Jan 30, 2012
Carolina B
Session 2: Space Situational Awareness
Chair: John Seago, Analytical Graphics, Inc.
08:00
AAS 12 - 109
Agile RSO Attitude Estimation Using Lightcurve Inversion and Bayesian
Estimation with Shape Model Uncertainty
Marcus J. Holzinger and Kyle T. Alfriend, Texas A&M University; Charles J.
Wetterer and Kris Hamada, Pacific Defense Solutions, LLC; K. Kim Luu and Chris
Sabol, Air Force Research Laboratory; Andrew Harms, Princeton University
The problem of estimating attitude for actively maneuvering or tumbling Resident Space Objects
(RSOs) with unknown mass properties / external torques and uncertain shape models is addressed.
Exponentially Correlated Acceleration (ECA) approaches from manned aircraft tracking are applied
to the attitude dynamics, and model uncertainty is accounted for in a bias state with dynamics derived
using first-principles. Bayesian estimation approaches are suggested as a means by which severely
non-Gaussian and multi-model state distributions may be properly captured. Simulated results are
given, conclusions regarding performance are made, and future work is outlined.
08:25
AAS 12 - 110
Delta-V Distance Object Correlation and Maneuver Detection with Dynamics
Parameter Uncertainty and Generalized Constraints
Marcus J. Holzinger and Kyle T. Alfriend, Texas A&M University; Daniel J.
Scheeres and Daniel P. Lubey, University of Colorado at Boulder
Correlating observations with one another or with known objects as well as detecting and
characterizing maneuvers is examined. A survey of existing observation correlation and maneuver
detection techniques is given, and potential shortcomings for maneuver spacecraft identified. Existing
optimal control correlation and maneuver detection methods are extended to accommodate arbitrary
numbers of general intermediate state constraints and associated distributions, as well as dynamics
parameter uncertainty. Simulated results are reviewed, and conslusions and future work are outlined.
08:50
AAS 12 - 111
Utilizing Stability Metrics to Aid in Sensor Network Management Solutions for
Satellite Tracking Problems
P.S. Williams and D.B. Spencer, The Pennsylvania State University;
R.S. Erwin, Air Force Research Laboratory
The following work examines how measuring the stability of satellite dynamics through calculation of
Lyapunov exponents can be utilized to help create sensor tasking decisions for a multi-object, multisensor satellite tracking problem. These methods willbe applied to a simulation which attempts to
represent a simplified tracking component of the Space Situational Awareness problem with one
hundred simulated satellites and five sensors. Results from various simulations will be analyzed in
order to determine the possible effectiveness of such methods to reduce the overall uncertainty of all
tracked objects, aiding in the effectiveness in detecting possible in-space collisions.
09:15
AAS 12 - 112
Comparison of Two Single-Step, Myopic Sensor Management Decision
Processes Applied to Space Situational Awareness
P.S. Williams and D.B. Spencer, The Pennsylvania State University;
R.S. Erwin, Air Force Research Laboratory
The following work describes a sensor tasking approach for a multi-object, multi-sensor tracking
problem analogous to the monitoring of resident space objects known as Space Situational Awareness
(SSA). To conduct this tasking, two information theory-based utility metrics are implemented in order
to task sensors to observe satellites which will maximize the total information gained at discrete
simulation time-steps. Using a simple simulation of the nonlinear estimation and tasking components
of the SSA problem, comparisons will be made between combinations of tasking and estimators in
regards to their impact on overall tracking performance.
09:40
Break
10:05
AAS 12 - 113
Co-Orbiting Anti-Satellite Vulnerability
Salvatore Alfano, Center for Space Standards and Innovation
This work uses simple orbital dynamics to initially assess the vulnerability of a satellite to a SpaceBased Interceptor (SBI) launched from an orbiting, anti-satellite, carrier platform. The method
produces an engagement volume derived from the position and velocity vectors of the launching
platform, the range of impulsive velocities that can be imparted to the SBI upon deployment, and the
maximum expected time-of-flight from release until intercept. If a satellite is likely to pass through
the volume, then it is considered vulnerable although the SBI would have launched much earlier.
10:30
AAS 12 - 115
Inverse Problem Formulation Coupled with Unscented Kalman Filtering for
State and Shape Estimation of Space Objects
Laura Henderson, Pulkit Goyal and Kamesh Subbarao,
The University of Texas at Arlington
Given time series astromeric and photometric measurements from the Space Survilance Network
(SSN) as explicit and implicit functions of position, attitude, and resident space object's (RSO) shape
and size, in addition to governing equations for the system dynamics and appropriate measurement
models the following problem will be solved. Combined Direct + Inverse Problem: This problem aims
to determine the position, velocity, angular velocity, attitude and the RSO's shape and size. The
parameters are estimated using a maximum likelihood approach and integrated into the UKF. The
results of this hybrid algorithm are then compared with the joint state/parameter estimation technique.
10:55
AAS 12 - 116
Small Satellite Missions for Debris Tracking and Mitigation
Joseph W. Gangestad, Sarah A. Whalley, Glenn E. Peterson and Thomas J. Lang,
The Aerospace Corporation
Results are presented from a study into the feasibility of small satellites, such as CubeSats, to perform
proximity operations near potentially hazardous space debris and to provide higher precision tracking
measurements than available from ground-based assets. Candidate orbital communications relays for
the CubeSats were identified along with their associated link and coverage statistics, the performance
of optical ranging systems were considered relative to the estimated reflectivity of spacecraft
materials, and propellant requirements were estimated for non-cooperative formation-keeping
between the CubeSat and a debris target.
11:20
AAS 12 - 117
Inactive Space Object Shape Estimation via Astrometric and Photometric Data
Fusion
Richard Linares and John L.Crassidis, University at Buffalo
This paper presents methods to determine the shape of a space object in orbit while simultaneously
recovering the observed space object's inertial orientation and trajectory. The filter employs the
Unscented estimation approach, reducing passively-collected electro-optical data to infer the unknown
state vector comprised of the space object inertial-to-body orientation, position and their respective
temporal rates. Recovering these characteristics and trajectories with sufficient accuracy is shown in
this paper. The performance of this strategy is demonstrated via simulated scenarios.
Jan 30, 2012
Calhoun
Session 3: Attitude Determination
Chair: Dr. Sergei Tanygin, Analytical Graphics, Inc.
8:00
AAS 12 - 118
Filtering Solution to Relative Attitude Determination Problem Using Multiple
Constraints
Richard Linares and John Crassidis, University at Buffalo; Yang Cheng, Mississippi
State University
In this paper a relative attitude filtering solution of a formation of two vehicles with multiple
constraints and gyro measurements is shown. The solution for the relative attitude between the two
vehicles is obtained only using line-of-sight measurements between them and a common (unknown)
object observed by both vehicles. The constraint used in the solution is a triangle constraint on the
vector observations and gyro mesurements. This approach is extended to multiple objects by apply
this constraint for each object. Simulation runs to study the performance of the approach will be
shown.
08:25
AAS 12 - 119
Complete Closed Form Solution of a Tumbling Triaxial Satellite under GravityGradient Torque
Martin Lara and Sebastian Ferrer, University of Murcia
We revisit the attitude dynamics of a tumbling triaxial satellite under gravity-gradient. The total
reduction of the Euler-Poinsot Hamiltonian provides a suitable set of canonical variables that expedite
the perturbation approach. Two canonical transformations reduce the perturbed problem to its secular
terms. The secular Hamiltonian and the transformation equations of the averaging are computed in
closed form of the triaxiality coefficient, thus being valid for any triaxial body. The solution depends
on Jacobi elliptic functions and integrals, and is valid for non-resonant rotations under the assumption
that the tumbling rate is much higher than the orbital or precessional motion.
08:50
AAS 12 - 120
Cayley Attitude Technique
John E. Hurtado, Texas A&M University
Single point attitude determination is the problem of estimating the instantaneous attitude of a rigid
body from a collection of vector observations taken at a single moment in time. Many methods have
been proposed to solve this problem, most of which are based on Wahba's problem. Here, a new
technique is presented that uses a generalized Cayley transform. Algorithms to optimally solve the
attitude estimation problem for a wide family of attitude parameters are given.
09:15
AAS 12 - 121
Attitude Estimation in Higher Dimensions
To date, there has been only one archival journal paper devoted to attitude determination in
dimensions higher than three. A review of literature reveals, however, that the kinematics, kinetics,
and control of bodies that occupy abstract higher dimensional spaces has been extensively
investigated. Many of those studies tell of a relevant connection between real physical systems in
three dimensions and a counterpart in higher dimensions. Therefore, it is with similar hopes in mind
that the problem of single instance attitude estimation for bodies in abstract higher dimensional spaces
is reviewed.
09:40
Page 23 Break
10:05
AAS 12 - 122
Linear Solutions to Single Instance Position and Attitude Estimation
The combined attitude and position estimation problem has received less attention than the attitudeonly problem. Here, new developments are presented for this problem that use a generalized Cayley
transform. One interesting viewpoint involves casting the position and attitude in three dimensions as
an attitude-only problem in four dimensions.
10:30
AAS 12 - 123
Analysis and Comparison of Rate Estimation Algorithms
Using Coarse Sun Sensors and a Three-Axis Magnetometer
Tae W. Lim, United States Naval Academy; Frederick A. Tasker, Naval Research
Laboratory
This paper examines various rate estimation approaches using sun vector and earth magnetic field Bvector measurements, either individually or collaboratively, for safehold design applications. Three
possible approaches of estimating body rates using coarse sun sensors (CSS's) and a three axis
magnetometer (TAM) are presented in detail including sun vector only (or CSS only) approach,
magnetic field vector only (or TAM only) approach, and combined sun vector and magnetic field
vector approach. Using simulations and flight operations experiences the paper discusses their
advantages and disadvantages to help design a safehold mode that will meet the design requirements
most effectively.
10:55
AAS 12 - 124
Autonomous Spacecraft Attitude Resource Sharing
Shawn C. Johnson and Norman G. FItz-Coy, University of Florida; Seth L. Lacy, Air
This paper investigates the use of attitude sharing between two satellites. The first, sharing, satellite,
has inertial and relative attitude sensors. The second, receiving, satellite can only propagate attitude.
Relative attitude is available only under certain alignment conditions consistent with proper
orientation of a relative attitude sensor on the sharing satellite and attitude fiducials on the receiving
satellite. An uncertainty-based metric is derived from the Extended Kalman Filter, as an autonomous
switching condition for resource sharing. Simulation results indicate that one star tracker can
accommodate the pointing requirements for multiple spacecraft, with performance advantages over a
fixed-measurement schedule.
11:20
AAS 12 - 125
Novel Multiplicative Unscented Kalman Filter for Attitude Estimation
Renato Zanetti, The Charles Stark Draper Laboratory; Kyle J. DeMars, Air Force
Research Laboratory; Daniele Mortari, Texas A&M University
A novel spacecraft attitude estimation algorithm is presented. The new algorithm utilizes unit vector
measurements and is based on the unscented Kalman filter (UKF). The UKF, like the extended
Kalman filter, employs a linear update in which an additive residual is formed. The residual is given
by the difference between the measurement and its mean. This work utilizes a multiplicative residual
in which the measurement and the mean are multiplied together using the vector cross product.
Because of the nature of the problem a multiplicative residual combined with a multiplicative update
is a more natural solution.
11:45
AAS 12 - 126
Projective Geometry of Attitude Parameterizations with Applications to Control
and Tracking
Sergei Tanygin, Analytical Graphics, Inc.
Vectorial attitude parameterizations can be viewed as projections from the unit quaternion
hypersphere onto a hyperplane tangential to the hypersphere at a point representing zero rotation. It is
shown that, if the projection hyperplane is moved to any other point on the hypersphere, the resulting
parameterization and its kinematics follow directly from the formulations that are well-known in
attitude tracking problems. It is also shown how a generalization of stereographic projection geometry
can support various attitude parameters, and how one particular stereographic projection can
efficiently and accurately approximate the rotation vector parameterization for a full range of rotation
angles.
Jan 30, 2012
Carolina A
Session 4: Asteroid and Near-Earth Object Missions I
Chair: Kenneth Williams, KinetX, Inc.
13:30
AAS 12 - 127
Earth Delivery of a Small NEO with an Ion Beam Shepherd
Claudio Bombardelli, Hodei Urrutxua and Jesus Pelaez, Technical University of
Madrid
The possibility of capturing a small Near Earth Asteroid (NEA) and deliver it to the vicinity of the
Earth has been recently explored by different authors. Among the different challenges related to this
operation stands the difficulty of robotically capturing the object, whose composition and dynamical
state could be problematic. In order to simplify the capture operation we propose the use of a
collimated ion beam ejected from a hovering spacecraft in order to maneuver the object without direct
physical contact. The feasibility of this approach and the mass cost of a possible asteroid retrieval
mission is evaluated.
13:55
AAS 12 - 128
Conceptual Design of Planetary Defense Technology Demonstration Mission
Alan Pitz, George Vardaxis and Bong Wie, Iowa State University
When the lead time of the probable impacting NEO is short, nuclear explosives delivered by an
innovative design of a versatile, two-body hypervelocity nuclear interceptor spacecraft (HNIS) may
be mandated to safeguard the Earth. With the current survival limitations of nuclear triggering
systems, flight demonstrations are mandatory to validate viable HNIS concepts, terminal guidance
instruments and sensors, thermal shielding on the follower spacecraft, and mission operations.
Considering three different budget constraints ($250M, $500M, and $1B), conceptual mission designs
to a target NEO are created using AGI’s Satellite Tool Kit, NASA’s General Mission Analysis Tool,
and ADRC's mission analysis software.
14:20
AAS 12 - 129
Design of Spacecraft Missions to Test Kinetic Impact for Asteroid Deflection
Sonia Hernandez, The University of Texas at Austin; Brent Barbee, NASA Goddard
Space Flight Center
Earth has previously been struck with devastating force by near-Earth asteroids (NEAs) and will be
struck again. Telescopic search programs aim to provide advance warning of such an impact, but no
techniques or systems have yet been tested for deflecting an incoming NEA. To begin addressing this
problem, we have analyzed the more than 8000 currently known NEAs to identify those that offer
opportunities for safe and meaningful near-term tests of the proposed kinetic impact asteroid
deflection technique. In this paper we present our methodology and results, including complete
mission designs for the best kinetic impactor test mission opportunities.
14:45
AAS 12 - 130
Displaced Periodic Orbits with Low-Thrust Propulsion: Application to Binary
Asteroid
Jules Simo and Colin R. McInnes, University of Strathclyde
This paper investigates displaced periodic orbits at linear order in the circular restricted Earth-Moon
system (CRTBP), where the third massless body utilizes a hybrid of solar sail and a solar electric
propulsion (SEP). Attention is now directed to binary asteroid systems as an application of the
restricted problem. The idea of combining a solar sail with an SEP auxiliary system to obtain a hybrid
sail system is important especially due to the challenges of performing complex trajectories.
15:10
Break
15:35
AAS 12 - 131
Dynamical Characterization of 1:1 Resonance Crossing Trajectories at Vesta
Alex Haro, Universitat de Barcelona; Josep-Maria Mondelo, Universitat Autonoma
de Barcelona; Benjamin F. Villac, University of California at Irvine
Motivated by the challenges associated with the 30-days transfer of the 1:1 resonance crossing of the
Dawn mission, which entered its high-altitude mapping orbit on 29 September 2011, this paper
analyzes the dynamical structure and sensitivity of 1:1 resonance crossing ballistic transfers at Vesta.
In particular, a combination of chaoticity maps with frequency analysis and invariant object
continuations is proposed to provide the necessary support for design and analysis risk mitigation
strategies in these regions.
16:00
AAS 12 - 132
Close Proximity Asteroid Operations Using Sliding Control Modes
Roberto Furfaro, University of Arizona; Dario O. Cersosimo, University of Missouri
at Columbia; Julie Bellerose, Carnegie Mellon University Silicon Valley / NASA
Ames Research Center
Close proximity operations around small celestial bodies are extremely challenging due to their
uncertain dynamical environment. In this paper, we show that the Multiple Sliding Surface Guidance
(MSSG) algorithm, already proposed for autonomous asteroid pin-point guidance, can be extended to
guide the transition of the spacecraft from any two desired states, including hovering and orbital
states. Constructed using two sliding surfaces, the algorithm takes advantage of the system’s ability to
reach the sliding surfaces in finite time. The algorithm does not require either ground-based or onboard trajectory generation but computes an acceleration command that target a specified state.
16:25
AAS 12 - 133
Fourth-order Gravity Gradient Torque of Spacecraft Orbiting Asteroids
Yue Wang and Shijie Xu, Beihang University
To improve previous fourth-order model, a full fourth-order gravity gradient torque model of a rigid
spacecraft around an asteroid with a 2nd degree and order-gravity field is established by introducing
spacecraft’s higher-order inertia integrals. A numerical simulation is carried out to verify our model
using a special rigid body consisted of 36 point masses moving on the synchronous orbit. Simulation
results show that the motion of previous fourth-order model is quite different from the exact motion,
while our full fourth-order model fits exact motion very well, and our model is precise enough for
practical applications.
16:50
AAS 12 - 134
On the Planar Motion in the Full Two-Body Problem
Pamela Woo and Arun K. Misra, McGill University
The motion of binary asteroids, modeled as the full two-body problem, is studied. The shape and mass
distribution of the bodies are considered. Using the Lagrangian approach, the equations governing the
planar motion are derived. The resulting system of four equations are nonlinear and coupled. In the
particular case where the bodies are axisymmetric around an axis normal to the plane, the system
reduces to a single equation, with small nonlinearity. The method of multiple scales is used to obtain a
first-order solution. This is proven to be sufficient when compared with the numerical solution.
Jan 30, 2012
Carolina B
Session 5: Dynamical Systems Theory I
Chair: Dr. Robert Melton, Pennsylvania State University
13:30
AAS 12 - 135
Invariant Manifolds to Design Scientific Operative Orbits in the Pluto-Charon
Binary System
Davide Guzzetti and Michele Lavagna, Politecnico di Milano
Feasibility of operative orbits in the Pluto-Charon system has been investigated in this work. Given
that currently only the New Horizon NASA mission will perform a quick fly-by of Pluto-Charon, the
chance to close a spacecraft in orbit around the system would represent a significant add-on in the
science knowledge domain and an interesting challenge from the flight dynamics perspective. A
R3BP coupled with the invariant manifolds are the main tools here exploited to manage the
trajectories design; itineraries and strategies, that can meet the requirements of costs minimization,
long operative life and adequate coverage of the surfaces, are proposed.
13:55
AAS 12 - 136
Approaching Moons from Resonance via Invariant Manifolds
Rodney L. Anderson, Jet Propulsion Laboratory
In this work, the approach phase from the final resonance of the endgame scenario in a tour design is
examined within the context of invariant manifolds. Previous analyses have typically solved this
problem either by using numerical techniques or by computing a catalog of suitable trajectories. The
invariant manifolds of a selected set of libration orbits and unstable orbits are computed here to serve
as guides for desirable approach trajectories. The analysis focuses on designing the approach phase
sothat it ties in with the final resonance in the endgame sequence while also targeting desired
conditions at the moon.
14:20
AAS 12 - 137
Attainable Sets in Space Mission Design: A Method to Define Low-Thrust,
Invariant Manifold Trajectories
Giorgio Mingotti, Universitat Paderborn; Francesco Topputo and Franco BernelliZazzera, Politecnico di Milano
A method to incorporate low-thrust propulsion into the invariant manifolds technique for space
trajectory design is presented in this paper. Low-thrust propulsion is introduced by means of
attainable
sets that are used in conjunction with invariant manifolds to define first guess solutions in the
restricted-three body problem. They are optimized in the restricted four-body problem where an
optimal control problem is formalized. Several missions are investigated in the Earth--Moon system:
transfers to libration point orbits and to periodic orbits around the Moon. Attainable sets allow the
immediate design of efficient complex space trajectories.
14:45
AAS 12 - 138
Efficient Trajectory Correction for L2 Halo-Orbit Transfer using Stable
Manifolds
Yoshihide Sugimoto and Triwanto Shimanjuntak, The Graduate University for
Advanced Studies; Masaki Nakamiya and Yasuhiro Kawakatsu, Japan Aerospace
Exploration Agency
Halo orbit around Lagrange point (L point), especially at L2 point, is recently in the spotlight because
of its periodicity, suitable location for deep-space astronomical observations, and stable thermal
environment. In near future, several missions like technical demonstration and observation missions
will be launched to utilize a Halo orbit. Stable manifolds, which are constructed by dynamical system
theory, are strong feature to insert the spacecraft naturally into a Halo orbit. In this paper, we show
stable manifolds prediction first using a scaling method and then an efficient trajectory correction
method by means of predicted stable manifolds in the Circular Restricted Three-Body Problem.
15:10
Break
15:35
AAS 12 - 139
Discrete-Time Bilinear Representation of Continuous-Time Bilinear State-Space
Models
Minh Q. Phan, Dartmouth College; Yunde Shi, Raimondo Betti and Richard W.
Longman, Columbia University
This paper develops techniques to represent a first-order continuous-time bilinear state-space model
by various first-order discrete-time bilinear state-space models. Although it is generally possible to
discretize any well-behaved continuous-time model, presented are techniques that keep the discretetime bilinear model in first-order form while maintaining the simple bilinear structure of the original
continuous-time model. A class of techniques based on Adams-Bashforth integration methods is
found to meet these requirements, whereas simpler Euler methods produce unstable discrete-time
models. Application of the developed techniques to derive discrete-time bilinear models of satellite
attitude dynamics is presented.
16:00
AAS 12 - 140
Expanding Transfer Representations in Symbolic Dynamics for Automated
Trajectory Design
Eric Trumbauer and Benjamin Villac, University of California at Irvine
Previous studies have shown symbolic dynamics can be used to find transfers with desirable global
transit characteristics using libration point region and manifold structures in the CR3BP. However,
this method cannot control for practical orbital elementssuch as altitude and inclination. Extensions of
existing symbolic dynamic methods are needed for automated selection of trajectories with these
attributes. Enabling this are recent studies which have shown connections between important classical
characteristics and structures such as resonant orbits, collision trajectories, and manifolds. This paper
analyzes the utility of such an extension in the planar problem as a first step in this direction.
16:25
AAS 12 - 141
Homotopy Continuation Solution of the Free Rigid Body Equations of Motion
Josue D. Munoz, Air Force Research Laboratory
The solution to the free rigid body equations of motion via homotopy continuation is explored in this
paper. Euler parameters (i.e., unit quaternion) are used to describe the orientation and Euler’s second
law is used to describe the rotational motion. The procedure for obtaining the solution is presented
and it is shown that the solution has a parametric structure (i.e., depends on inertia parameters, initial
conditions, and homotopy parameters) and is an explicit function of time. The homotopy solution is
compared to the numerically integrated solution to characterize its radius of convergence (for both
axisymmetric and triaxial cases).
16:50
AAS 12 - 142
A Theory of Low Eccentricity Satellite Motion
William E. Wiesel, Air Force Institute of Technology
Earth satellite motion is considered from the point of view of periodic orbits and Floquet theory in the
earth's zonal potential field. Periodic orbits in the zonal potential are nearly circular, except near the
critical inclination. Since the earth's oblateness is included in the periodic orbit, perturbations
generally begin at one part in a hundred thousand, not one part in a thousand. Perturbations to the
periodic orbit are calculated for sectoral and tesseral potential terms, for air drag, and for third body
effects. There results a compact, purely numerical set of algorithms that may be quite accurate.
17:15
AAS 12 - 143
Two-Point Boundary Value Problem of the Relative Motion
Zhang Hao, Zhao Yushan, Shi Peng and Li Baojun, Beihang University
The two-point boundary value problem of relative motion is studied both in the frameworks of
relative motion theory and relative Lambert’s problem theory. It is shown that the solutions obtained
by the above two methods are equivalent to the first order. Singularity occurs when linearization is
used in both methods. It is proved that the singularity is also equivalent. Singularity is then studied in
the point of view of multiple-revolution Lambert’s problem. Further analysis shows that whether the
singularity can happen or not depend on the boundary values. Several examples are given to illustrate
the findings.
Jan 30, 2012
Calhoun
Session 6: Formation Flying II
Chair: Dr. Matthew Wilkins, Schafer Corporation
13:30
AAS 12 - 144
Circular Lattice String-of-Pearls Constellations for Radio Occultation Mission
Sanghyun Lee and Daniele Mortari, Texas A&M University
This paper addresses the problem of designing suitable satellite constellation for Radio Occultation
mission. Radio occultation for Earth atmosphere usually requires global coverage and short interval
measurements. The Circular (2-D) Lattice Flower Constellation theory is here applied to design
constellations maximizing active time with providing global coverage and frequent measurements.
Optimizations are performed using Genetic Algorithms to estimate constellation design parameters.
Optimization is constrained by altitude range (drag and Van Allen belt avoidance) and nodal
precession is used to obtain global coverage. The performance of some solutions are provided to help
optimality selection.
13:55
AAS 12 - 145
Common-Period Four-Satellite Continuous Global Coverage Constellations
Revisited
John E. Draim, Consultant; Weijung Huang, University of Missouri at Columbia;
David A. Vallado and David Finkleman, Center for Space Standards and Innovation;
Paul J. Cefola, Consultant in Aerospace Systems
Global constellation coverage has been a topic of interest for many years. The Draim four-satellite
continuous global coverage constellation has significant improvement over traditional coverage
constellations. We re-look at this constellation using new analytical search techniques, computational
methods to assess the dynamic performance, and graph-ical depictions. Using the original orbits, we
vary orbital parameters to determine how the constellation reacts to additional constraints. Evaluation
criteria are expanded to include the number of satellites, distance from the earth, orbital regimes,
conjunction probabilities, communication link margins, etc. Technical statistics of satellite access
parameters and graphical depictions are also examined.
14:20
AAS 12 - 146
Optimization of Hybrid Orbit Constellation Design for Space-Based
Surveillance System
Hongzheng Cui, Xiucong Sun and Chao Han, Beihang University
The focus for this paper is to design the satellite constellation to observe GEO regime, and HEO,
SubGEO, and hybrid orbit with both HEO and SubGEO are adopted as mission orbits for Space-Based
Surveillance System (SBSS). A new method called the rapid method for satellite constellation
performance calculation is developed by the Hermite interpolation technique to reduce the computing
complication and time. The SBSS constellation optimization models are presented and the
evolutionary algorithm is adopted to optimize the configuration parameters.
14:45
AAS 12 - 147
Reducing Walker, Flower, and Streets-of-Coverage Constellations to a Single
Constellation Design Framework
Jeremy J. Davis, VectorNav Technologies, LLC; Daniele Mortari, Texas A&M
University
Satellite constellations are typically designed using either Walker or streets-of-coverage methods. In
some cases, the constellation may be optimized on the individual satellite level to produce nonuniform distributions. The recently developed lattice theory of Flower Constellations has generalized
Walker constellations but cannot accommodate non-uniformity or streets-of-coverage. By inverting
the integer lattice, one can define three continuous variables that generalize Flower and streets-ofcoverage constellations while permitting non-uniform designs. Transitioning from integer parameters
to continuous ones increases computational complexity but provides greater design flexibility and
optimization. Both global navigation and regional coverage examples are provided, demonstrating the
power of this new method.
15:10
Break
15:35
AAS 12 - 148
Perturbation Effects on Elliptical Relative Motion Based on Relative Orbit
Elements
Jianfeng Yin and Chao Han, Beihang University
A new elliptical relative motion model with no singularity problem is derived based on the relative
orbit elements. The inverse transformation of state transfer matrix is obtained to analyze perturbation
effects and control strategy. The velocity impulse control laws, including out-of-plane and in-plane
control, are also proposed. Mean orbit elements theory are introduced into the new dynamic model to
analyze the perturbation effects, mainly J2. The effects of gravitational perturbations are simulated
andanalyzed using the proposed feedback control method. The simulations presented clearly show that
the new relative motion model could describe dynamics of formation flying more efficiently.
16:00
AAS 12 - 149
Review of the Solutions to the Tschauner-Hempel Equations for Satellite
Relative Motion
Andrew J. Sinclair and Ryan E. Sherrill, Auburn University; T. Alan Lovell, Air
The Tschauner-Hempel equations model the motion of a deputy satellite relative to a chief satellite
with arbitrary eccentricity. They are linear non-autonomous differential equations with the chief’s true
anomaly as the independent variable. Since they first appeared, numerous analytical solutions have
been presented. This paper provides a focused review of some of these solutions: highlighting how
they are related and their singularities. The fundamental solutions of the Tschauner-Hempel equations
can be interpreted geometrically as generalizations of the drifting two-by-one ellipse that describes
relative motion in circular orbits. General solutions are formed by taking linear combinations of these
fundamental solutions.
16:25
AAS 12 - 150
Satellite Formation Design Using Synchronous Optimal Rendezvous Solutions
Weijun Huang, University of Missouri
Estimating fuel consumption for each satellite is important for designing a satellite formation.
Parametric solutions of the Clohessy-Wiltshire equations are widely used to design basic elliptic
formation (BEF), which can be viewed as a basic building block of a more complicated formation. In
this paper, linear primer vector theory is used to study the problem of designing a coplanar target BEF
for a known BEF. Lemmas and theorems that lead to an optimal design of a target BEF are proved.
This research surprisingly reveals the advantage of using synchronous optimal rendezvous solutions to
design satellite formations.
16:50
AAS 12 - 151
Three-Dimensional Linear Stability Analysis of Spinning Three-Craft Coulomb
Formations
Erik A. Hogan, Peter D. Jasch and Hanspeter Schaub, The University of Colorado at
Boulder
This paper analyzes the stability of collinear three-craft Coulomb formations with set charges,
assumed to be spinning in deep space. Previous work analytically proves in-plane marginal stability.
However, the unstable out-of-plane motion is shown to decouple to first order from the marginally
stable in-plane motion. Further, the degree of instability is small such that the departure drifts are
reasonably slow. In this paper, the out-of-plane motion is analyzed in more detail. This paper
illustrates that the unstable out-of-plane motion can be feedback stabilized without requiring in-plane
motion control, yielding an elegant and simple spinning spacecraft cluster control strategy.
17:15
AAS 12 - 152
Velocity Extrema in Spacecraft Formation Flight
Shawn E. Allgeier, University of Florida; R. Scott Erwin, Air Force Research
Laboratory; Norman G. Fitz-Coy, University of Florida
This paper considers the analysis of relative motion between two spacecraft in orbit. Specifically, the
paper seeks to provide bounds for relative spacecraft velocity- based measures which impact
spacecraft formation-flight mission design and analysis. The range rate metric is derived and then
bounded for certain special cases. A methodology for bounding the metrics is presented. The
extremal equations for the range rate are formulated as an affine variety and solved using a Groebner
basis reduction. A numerical example is included to demonstrate the efficacy of the method.
Jan 30, 2012
Colonial
Session 7: Optimal Control
Chair: Dr. Marcus Holzinger, Texas A&M University
13:30
AAS 12 - 153
Necessary Conditions for Optimal Impulsive Rendezvous in a
Newtonian Gravitational Field
Thomas Carter, Eastern Connecticut State University; Mayer Humi, Worcester
Polytechnic Institute
The problem of planar optimal impulsive rendezvous with fixed end conditions in a Newtonian
gravitational field is approached through a transformation of variables that was recently used by the
authors to successfully investigate the problem of optimal impulsive rendezvous near circular orbit.
New necessary conditions for solution of this more general problem are presented in terms of these
transformed variables.
13:55
AAS 12 - 154
Existence and Sufficiency Conditions for Optimal Impulsive Rendezvous in a
Newtonian Gravitational Field
Thomas Carter, Eastern Connecticut State University; Mayer Humi, Worcester
Polytechnic Institute
An investigation of the question of existence of solutions of an optimal impulsive rendezvous in a
Newtonian gravitational field reveals that if the initial and terminal angular momentum are positive,
either a solution exists, or else an approximate solution exists to any degree of accuracy. If the
differences in the values of the true anomaly where the velocity increments are applied are not integer
multiples of pi, then an actual solution exists, not an approximate one. Under these conditions,
necessary and sufficient conditions for optimality are available. An example is presented of an
optimal solution having a finite radial distance.
14:20
AAS 12 - 155
Modified Chebyshev-Picard Iteration Methods for Station-Keeping of
Translunar Halo Orbits
Xiaoli Bai and John L. Junkins, Texas A&M University
The halo orbits around the Earth-Moon L2 libration point provide a great candidate orbit for a lunar
communication satellite, where the satellite remains above the horizon on the far side of the Moon is
visible from the Earth at all times. Such orbits are generally unstable and station-keeping strategies are
required to control the satellite to remain close to the reference orbit. A recently developed Modified
Chebyshev-Picard Iteration method is used to compute corrective maneuvers at discrete time intervals
for station-keeping of halo orbit satellite and several key parameters affecting the mission
performance are analyzed through numerical simulations.
14:45
AAS 12 - 156
Fixed-Duration, Free Departure Time Satellite Transfer Problem With Path
Constraint
Weijun Huang, University of Missouri at Columbia
In Satellite Formation Flying (SFF) mission, satellite transfer between two formations could be
modeled as Fixed-Duration, Free Departure Time (FDFDT) transfer problem. Because at many cases,
it is not the starting time of the transfer, but the duration of the transfer is important for the maneuver
planning. At this paper, a more difficult FDFDT transfer problem with path constraint is considered.
Calculus of variation is used to derive an algorithm to solve the FDFDT problem with impulsive
engine. Analytical solutions of specific scenarios are also obtained through a technique of patching
different primer vector curves.
15:10
Break
15:35
AAS 12 - 157
Optimal Aeroassisted Orbital Transfer with Time Linear Control
S. Praneeth Reddy and Ashish Tewari, Indian Institute of Technology
It is demonstrated that the solution of the nonlinear, two-point boundary value problem for optimal
aeroassisted orbital transfer with minimal control effort and fixed terminal time leads to a time-linear
control profile. Numerical results are compared with those of an approximate optimal, free terminal
time scheme and observed to have a significant reduction in the maximum control input, control
power, and maximum heating rate. The time linear control profle is shown to be typical, and can be
easily implemented by a simple timing mechanism. An empirical relationship is derived for the
control profile as a function of the entry conditions.
16:00
AAS 12 - 158
Optimal Solutions and Guidance for Quasi-planar Ascent over a Spherical
Moon
David G. Hull and Matthew W. Harris, University of Texas at Austin
The minimum-time trajectory of a constant-thrust rocket in quasi-planar ascent from the surface of
the moon to lunar orbit over a spherical moon is obtained for small thrust angles. The solution of the
resulting TPBVP involves modified thrust integrals and requires an iteration. An indicated
approximate solution exists leading to a non-iterative analytical solution in terms of the well known
thrust integrals. Both solutions are tested in sample and hold guidance and satisfy the final
conditions, consume the same mass, and use approximately the same thrust pitch angle history. The
approximate solution merits further consideration for onboard guidance.
16:25
AAS 12 - 159
Space Object Maneuver Detection via a Joint Optimal Control and Multiple
Hypothesis Tracking Approach
Navraj Singh, Joshua T. Horwood and Aubrey B. Poore, Numerica Corporation
An optimal control framework is presented as a post-processor to a multiple hypothesis tracker
(MHT) for resolving uncorrelated tracks (UCTs) generated by space object maneuvers. The optimal
control framework uses the total velocity increment (delta-V) as the cost functional to determine
feasibility of maneuvers. The method obtains accurate delta-V estimates for connecting two UCTs via
fuel-optimal maneuvers. In addition, a method is proposed for treating uncertainty in the UCT states,
via the unscented transform, to determine the probability that a maneuver is feasible. The approach is
most applicable to routine but unannounced fuel-optimal maneuvers conducted by space objects.
Jan 31, 2012
Carolina A
Session 8: Trajectory Optimization I
Chair: Dr. Anil Rao, University of Florida
08:00
AAS 12 - 160
A Method Ensuring Rapid High-Fidelity Solution of the Analytic Switching
Function for Coast Arcs
Brian Jamison and Victoria Coverstone, University of Illinois Urbana-Champaign
During coast arcs of the two-body problem, application of analytic expressions for the co-states
allows for analytic expression of the Switching Function. Former works considered periodic sampling
and root-finding in order to determine the zeros of this function to provide for rapid determination of
the re-ignition angle. Whereas previously published approaches had the possibility of failure, this
work provides a method guaranteeing solution for the correct re-ignition zeros of the Switching
Function atthe greatest possible fidelity. Initial testing indicates that this method provides solutions at
comparably high levels of fidelity and speed.
08:25
AAS 12 - 162
Automated Inclusion of V-Infinity Leveraging Maneuvers in Gravity-Assist
Flyby Tour Design
Demyan Lantukh and Ryan Russell, The University of Texas at Austin; Stefano
Campagnola, Jet Propulsion Laboratory
Interplanetary and moon tour missions have benefited from the implementation of leveraging
maneuvers that efficiently change spacecraft energy relative to a flyby body. These v-infinity
leveraging maneuvers are reformulated into a boundary value problem more suitable for broad
trajectory searches and for the ephemeris case by using the same boundary conditions as the Lambert
problem. A root-solve on a complicated one-dimensional function space results from this
reformulation. The method allows the inclusion of maneuvers in broad tour design searches with few
additional search dimensions while also keeping the Lambert-based architecture. Examples are
presented using representative interplanetary and intermoon tours.
08:50
AAS 12 - 163
Closed-Form Solutions for Open Orbits Around an Oblate Planet
Vladimir Martinusi and Pini Gurfil, Technion - Israel Institute of Technology
The paper develops the closed-form solution for the motion around an oblate planet in the situation
wherein the orbit is unbounded. It is proven that when the effect of the J2 zonal harmonic is taken into
account, the orbit is different from its Keplerian counterpart, having a marked influence on the
deflection angle, thereby changing the Keplerian flyby geometry. Numerical simulations quantify this
difference, which is closely related to the minimum flyby altitude of the spacecraft. The analytic
developments can be applied to the preliminary design of gravity-assisted maneuvers.
09:15
AAS 12 - 164
Design of Optimal Transfers Between North and South Pole-Sitter Orbits
Jeannette Heiligers, Matteo Ceriotti, Colin R. McInnes, and James D. Biggs,
Advanced Space Concepts Laboratory, University of Strathclyde
Recent studies have investigated Earth pole-sitter missions where a spacecraft follows the Earth's
polar axis to have a continuous, hemispherical view of the polar regions for Earth observation and
high latitude telecommunications. However, the tilt of the polar axis causes the North and South poles
to be alternately situated in darkness for long periods during the year which constrains observations
and decreases the mission scientific return. This paper therefore investigates optimum, hybrid
sail/SEP propulsion transfers between North and South pole-sitter orbits before the start of the Arctic
and Antarctic winters to enable observation of the polar regions only when lit.
09:40
Break
10:05
AAS 12 - 165
Efficient Lunar Gravity Assists for Solar Electric Propulsion Missions
Damon Landau, Tim P. McElrath, Dan Grebow, and Nathan J. Strange,
Jet Propulsion Laboratory
The combination of lunar gravity assists for Earth escape and around 1.25 year of V-infinity
leveraging with SEP effectively boosts the performance of a given launch vehicle. Two methods are
presented to establish a launch period with lunar gravity assists, where the energy achievable with
lunar escape has been characterized as a function of right ascension, declination, and launch energy.
The increased launch efficiency makes a Falcon 9 perform like an Atlas V (401) at low C3 or like an
Atlas V (531) at high C3. An Atlas V (551) outperforms a Delta IV Heavy for C3 above 24 km2/s2
10:30
AAS 12 - 166
Global Optimization Techniques for Deep Space Trajectory Maneuvers Using
Satellite Tool Kit
Sruthi Krishnan, Virginia Polytechnic Institute and State University
The European Space Agency (ESA) recently proposed a test problem to model the Cassini2 trajectory
for global optimization. At present, algorithms for all proposed models are coded in Matlab or C++.
This project introduces a new method by using algorithms that are built within the Satellite Tool Kit
(STK) with the integration of Matlab to optimize the model trajectories necessary for deep space
maneuvers. The Matlab code provided online by ESA is used to integrate with STK to optimize the
current trajectory model for Cassini2. This project expects to find Delta-V results similar to current
optimum value 8.383 km/sec.
10:55
AAS 12 - 167
Optimization of Debris Removal Path for TAMU Sweeper
Jonathan Missel, and Daniele Mortari, Texas A&M University
This paper develops a method to evaluate and optimize the trajectory of a satellite designed for debris
removal, focusing on the proposed TAMU Sweeper mission. Using an evolutionary algorithm, it
observes interaction order, transfer trajectories, and sequence timing while optimizing fuel burned and
effectiveness towards debris mitigation. For a fixed time interval and number of debris interactions,
the most efficient and effective sequence is determined. Also, the debris mass estimation technique
proposed with TAMU Sweeper is analyzed for sensitivity to elements of hardware design. The
broader goal of this work is to evaluate feasibility of such missions.
Jan 31, 2012
Carolina B
Session 9: Attitude Dynamics and Control I
Chair: Dr. Peter Lai, The Aerospace Corporation
08:00
AAS 12 - 168
Delayed Feedback Attitude Control Using Neural Networks and LyapunovKrasovskii Functionals
Ehsan Samiei, Morad Nazari, and Eric A. Butcher, New Mexico State University;
Hanspeter Schaub, University of Colorado at Boulder
This paper addresses the regulation control and stabilization problem of spacecraft attitude dynamics
when there exists an unknown constant discrete delay in the measurements. Radial basis function
neural networks are used to approximate the kinematic and inertial nonlinearities, while a back
propagation algorithm is employed to update neural network weights. By employing a LyapunovKrasovskii functional, a delay independent stability condition is obtained in terms of a linear matrix
inequality, the solution of which gives the suitable controller gains. Finally, simulations are
performed and compared with results obtained using the method for delayed feedback control
suggested by Ailon et al.
08:25
AAS 12 - 169
A New Method for Simulating the Attitude Dynamics of Passively Magnetically
Stabilized Spacecraft
Roland Burton and Joseph Starek,Stanford University and NASA Ames Research
Center; Stephen Rock, Stanford University
A new method for simulating the attitude dynamics of passively magnetically stabilized spacecraft is
presented that offers an order of magnitude reduction in simulation run time compared to existing
methods with no loss in accuracy. The new method is applied to the modeling of the attitude dynamics
of the ARC 3U nanosatellite bus, with simulation results compared to on orbit data from O/OREOS, a
nanosatellite that was launched in late 2010. To improve simulation fidelity, magnetic properties of
the type of hysteresis material used were measured in the laboratory at Ames Research Center.
08:50
AAS 12 - 170
Design of Satellite Control Algorithm Using the State-Dependent Ricatti
Equation and Kalman Filter
Luiz DeSouza, National Institute for Space Research - S.J. Campos; Victor Arena,
Federal University of ABC - Santo André
This paper discusses application of the State-Dependent Riccati Equation (SDRE) method along with
Kalman filter to design and test a control algorithm for a 3D attitude satellite simulator. The control
strategy is based on gas jets and reaction wheel torques to perform large angle manuevers in three
axes. The simulator model allows investigating the dynamics and the control system taking into
account effects of the plant non-linearities and noises using the Kalman filter to estimate the
unavailable states. Simulation has shown the performance and robustness of the SDRE controller
applied for angular velocity reduction associated with a stringent "pointing requirement."
09:15
AAS 12 - 171
Artificial Potential Steering for Angular Momentum Exchange Devices
Josue D. Munoz and Frederick A. Leve, Air Force Research Laboratory
The artificial potential function methodology is well-suited for avoiding saturation and steering away
or through internal singularities in angular momentum exchange devices (AMED). The angular
momentum artificial potential steering (AMAPS) method is developed by first defining a reference
trajectory in the angular momentum space of the AMED. Next, the saturation for both reaction wheel
assemblies (RWA) and control moment gyros (CMG) are handled by using a repulsive artificial
potential function. The internal singularities of CMGs are handled by defining a potential to ensure
that the columns of the Jacobian stay orthogonal.
09:40
Break
10:05
AAS 12 - 172
Converting Repetitive Control Robustification Methods to Apply to Iterative
Learning Control
Richard Longman and Yunde Shi, Columbia University
Iterative learning control (ILC) can be used for high accuracy tracking with fine pointing equipment
on board spacecraft that need to perform repeated scanning maneuvers. This paper converts methods
of robustification of repetitive control systems used for vibration isolation on spacecraft to apply to
the ILC problem. Robustification is particularly important for ILC since it asks for zero error in
hardware tracking by iterating with the real world instead of a mathematical model. Model uncertainty
is used directly in the ILC design process, to perform the minimum possible compromise in
performance.
10:30
AAS 12 - 173
De-orbit Attitude Dynamics and Control of Spacecraft with Residual Fuel Based
on Fluidic Ring Actuator
Hong Guan and Shijie Xu, Beihang University
The fluidic ring actuator (FRA), based on the principle of conservation of angular momentum, is
introduced in this paper. The FRA accelerates the fuel in the ring pipe to generate the control
momentum, which is applied to stabilize the attitude of the spacecraft. The attitude control system of
FRA is proposed. The simulation model of the attitude dynamics combined with the fluid dynamics is
conducted. Simulation results show that the FRA is successful in stabilizing the attitude of the
spacecraft in the presence of the disturbances of the fuel sloshing.
10:55
AAS 12 - 174
A Computational Efficient Suboptimal Algorithm for Dynamic Thruster
Management
Mengping Zhu, Beihang University
A computational efficient algorithm based on the searching of the optimal feasible cone is proposed to
reduce the online computation load. The algorithm first concentrates on finding an optimal feasible
cone for the unconstrained problem. Then, constraints are taken into account to select out the target
thruster and compute the corresponding control contribution. Control error is thus obtained for next
cycle until being eliminated. An Illustrative example based on the core module of space station is
provided to verify the effectiveness of the proposed method as well as to demonstrate its advantage in
computational requirement and adaptiveness to thruster failure.
11:20
AAS 12 - 175
Analysis of Small-Time Local Controllability of Spacecraft Attitude Using Two
Control Moment Gyros
Haichao Gui, Shijie Xu and Lei Jin, Beihang University
Small-time local controllability of the dynamics of a spacecraft carrying two ar-bitrarily installed
control moment gyros (CMGs) is investigated via nonlinear controllability theory. With the gimbal
rates being treated as control inputs, STLC property of the system is found to be closely related to
geometric posi-tions of two angular momentum vectors of the CMGs at the system equilibrium. The
dynamics fails to be STLC when gimbals of the CMGs reach certain con-figurations resulting in
saturation of their total angular momentum. Apart from these cases, the dynamics is STLC.
Jan 31, 2012
Calhoun
Session 10: Flight Dynamics Operations
Chair: Laurie Mann, a.i. solutions, Inc.
08:00
AAS 12 - 176
Effects of High Frequency Density Variations on Orbit Propagation
Craig A. McLaughlin, Dhaval M. Krishna and Travis Locke, University of Kansas
Accelerometer derived densities for CHAMP and GRACE have multiple high frequency variations
that are not present in empirical density models or in density derived from precision orbit ephemeris
(POE) data. These high frequency density variations appear in all data sets, but are especially
prevalent during geomagnetic storms, near the polar cusps, and when the orbit plane is near the
terminator. This paper examines the effects of these high frequency density variations on orbit
propagation by comparing orbits propagated using accelerometer derived density to those propagated
using POE derived density, High Accuracy Satellite Drag Model density, and Jacchia 1971 density.
08:25
AAS 12 - 177
End-of-Life Procedures for Air Force Missions: Orbital Debris Mitigation with
CloudSat and TacSat-3
Michael Nayak, Space Development and Test Directorate, United States Air Force
At altitudes of less than 2,000 km, fragmentation wreckage caused by accidental explosions aboard
spacecraft accounts for 42% of catalogued space debris. Using currently operational satellites
CloudSat and TacSat-3 as examples, this paper discusses Air Force Space Command, NASA and DoD
requirements for mitigation of orbital debris during creation of an End-of-Life (EOL) plan, detailing
an outline for such plans with special applicability to military missions. EOL spacecraft passivation,
re-entry survivability analysis, casualty expectation analysis, methods to assess debris generation due
to intentional breakup, passivation, accidental explosions and on-orbit collisions; as well as USAF
operational execution of EOL are covered.
08:50
AAS 12 - 178
Extended Mission Maneuver Operations for the Interstellar Boundary Explorer
(IBEX)
Ryan Lebois, Lisa Policastri, John Carrico Jr. and Marissa Intelisano, Applied
Defense Solutions
This paper describes the operational strategies designed and executed by the IBEX Flight Dynamics
Group to transfer IBEX from its nominal science orbit onto a Lunar-Resonant trajectory that is
predictable beyond the expected lifetime of the spacecraft. This paper will highlight operational
constraints involved in planning the Orbit Maintenance Maneuvers (OMMs) as well as the steps
involved in calibrating the maneuvers, re-planning the maneuvers during operations, and analyzing
the success of the OMM execution based on operational results. A comparison of current orbit
predictions with the final pre-maneuver plan will also be discussed.
09:15
AAS 12 - 179
Flight Results of the Precise Autonomous Orbit Keeping Experiment on the
Prisma Mission
Sergio De Florio and Gianmarco Radice, University of Glasgow; Simone D’Amico,
DLR
The Autonomous Orbit Keeping (AOK) experiment on the PRISMA mission was executed
successfully from 18th of July to 16th of August 2011 demonstrating the capability of autonomous
precise absolute orbit control. The main performance requirement was a control accuracy of the
osculating ascending node of 10 m (1 sigma) with a maneuver budget of 0.5 m/s. The control
accuracy requirement was fully fulfilled. The mean value of the LAN deviation controlled by AOK
was -3.6 m with a standard deviation of 9.5 m during the fine control phase. The total delta-v spent
during the entire experiment was 0.1347 m/s.
09:40
Break
10:05
AAS 12 - 180
Numerical Prediction of Satellite Surface Forces with Application to Rosetta
Benny Rievers, Takahiro Kato, Jozef van der Ha and Claus Lämmerzahl, University
of Bremen
The precise determination of non-gravitational disturbances acting on a spacecrafts orbit is of major
importance for accurate orbit determination, orbit propagation as well as the successful interpretation
of scientific data. Most non-gravitational disturbances such as Solar radiation pressure (SRP) and
thermal recoil pressure (TRP) interact with the spacecraft surface and thus strongly depend on the
accurate modelling and implementation of the spacecraft's configuration. We present a numerical
approach for the high precision determination of non-gravitational surface forces based on Finite
Element modelling as well as a ray-tracing method. The method is applied in full detail to the Rosetta
spacecraft.
10:30
AAS 12 - 181
Mass Ejection Anomaly in Lissajous Orbit: Response and Implications for the
ARTEMIS Mission
Brandon D. Owens, Daniel Cosgrove, Jeffrey E. Marchese, John W. Bonnell, David
H. Pankow, Sabine Frey and Manfred G. Bester, University of California at Berkeley
On October 14, 2010, a 0.092 kg instrument sphere unexpectedly detached from the first spacecraft to
ever orbit an Earth-Moon libration point and a quick response was required to prevent the spacecraft
from falling out of Lissajous orbit. In this paper, the actions of the spacecraft operations team and the
changes to the spacecraft’s flight characteristics are described for the benefit of future Earth-Moon
libration point orbiting missions. Specifically, the authors detail how the timing of the event and
response affected the trajectory of the departing sphere and the prospects of preventing the
spacecraft’s fall out of Lissajous orbit.
10:55
AAS 12 - 182
Optimizing ARTEMIS Libration Point Orbit Stationkeeping Costs through
Maneuver Performance Calibration
Brandon D. Owens, Jeffrey E. Marchese, Daniel Cosgrove, Sabine Frey and
Manfred G. Bester, University of California at Berkeley
The first two spacecraft to orbit earth-moon libration points’ARTEMIS P1 and P2’performed a total
of 70 stationkeeping maneuvers over a period of 10 months. The degree of precision required for
these orbit corrections exceeded that which had been obtained on these spacecraft prior to their
Lissajous orbit insertions. This paper includes details of the in-flight calibration techniques used to
obtain the necessary level of performance for these maneuvers. With these techniques, the operations
team routinely reduced maneuver magnitude and phase errors to less than 2 millimeters/second and
one degree, respectively (the minimum maneuver magnitude error was 46.3 micrometers/second).
11:20
AAS 12 - 183
Optimizing Solar Radiation Coefficient as a Solve-For Parameter for the Orbit
Determination Process during the ARTEMIS Libration-Point Orbit Phase
Jeffrey E. Marchese, Daniel Cosgrove, Brandon D. Owens, Sabine Frey and
Manfred Bester, University of California at Berkeley; Mark Woodard and Dave
Folta, NASA Goddard Space FLight Center; Patrick Morinelli, Honeywell
Technology Solutions Inc.
The first two spacecraft to orbit Earth-Moon libration points--ARTEMIS P1 and P2--performed a total
of 70 station-keeping maneuvers over a period of 10 months. With short durations between maneuvers
and software restrictions that required data arcs be reset subsequent to each maneuver, it was critical
to ensure that successive orbit determinations converged to an accurate solution in a timely manner.
This paper details the in-flight techniques used to optimize solve-for parameters, such as solar
radiation coefficient and a constraint on its standard deviation, in the orbit solutions to ensure
accuracy and while still providing short convergence intervals.
Jan 31, 2012
Carolina A
Session 11: Dynamical Systems Theory II
Chair: Dr. David Spencer, Pennsylvania State University
13:30
AAS 12 - 184
Optimized Three-Body Gravity Assists and Manifold Transfers in End-to-End
Lunar Mission Design
Piyush Grover, Mitsubishi Electric Research Labs; Christian Andersson, Lund
University
We describe a modular optimization framework for GTO-to-moon mission design using the planar
circular restricted three-body problem (PCR3BP) model. The three-body resonant gravity assists and
invariant manifolds in the PCR3BP are used as basic building blocks of this mission design. The
mission is optimized by appropriately timed delta-Vs, which are obtained by a shooting method and a
Gauss-pseudospectral collocation method for different phases of the mission. Depending upon the
initial and final orbits, the optimized missions consume between 10-15 % less fuel compared to a
Hohmann transfer, while the time of flight is around 4 to 5 months.
13:55
AAS 12 - 185
Tisserand-Leveraging Transfer and Their Application to Real Missions
Stefano Campagnola and Anastassios Petropoulos, Jet Propulsion Laboratory;
Arnaud Boutonnet and Johannes Schoenmaekers, European Space Operations
Center, ESA; Ryan P. Russell, The University of Texas at Austin
This paper introduces a new technique called Tisserand-leveraging transfers (TILTs) that reduces the
orbit insertion maneuvers. TILTs connect two distant flybys at the minor body with an impulsive
maneuver at an apse. Using the CR3BP, TILTs extend the concept of v-infinity leveraging beyond
the patched-conics domain. In this paper we present a method to design TILTs and we apply them to
proposed missions to the Jupiter moons Ganymede and Europa. We also show that the "lunar
resonance" technique implemented by SMART1 can be re-interpreted as a sequence of low-thrust
TILTs.
14:20
AAS 12 - 186
Utilization of Sun-Earth Libration Points as Staging Locations for Human
Exploration Missions to Near-Earth Asteroids
Aline K. Zimmer and Ernst Messerschmid, Institute of Space Systems, University of
Stuttgart
In an effort to reduce the mass launched per mission, cargo modules are stationed in SEL orbits for
reuse in subsequent missions in an effort to reduce the mass launched per mission. Performing Oberth
maneuvers in close proximity to the Earth, the cargo modules rendezvous with the crew vehicle
launched from Earth on the outbound trajectory to the NEA and return to the SEL orbit after the
mission while the crew vehicle directly re-enters the Earth's atmosphere. The SEL orbits are matched
to the interplanetary trajectory leg by means of a differential correction algorithm and the delta-v
required is minimized.
14:45
AAS 12 - 187
Preliminary Study of the Transfer Trajectory from the Moon to the Halo Orbit
for the Small Scientific Spacecraft, DESTINY
Masaki Nakamiya and Yasahiro Kawakatsu, Japan Aerospace Exploration Agency
This study investigates the trajectory design of the small scientific spacecraft, DESTINY
(Demonstration and Space Technology for INterplanetary voYage), which aims to be launched by the
third Japanese next-generation solid propellant Epsilon rocket around 2016. In the DESTINY mission,
the spacecraft will go to the moon by the ion engine from the large elliptical orbit. Afterward, the
spacecraft will use a lunar swingby to go to the periodic orbit near the libration point (Halo orbit) of
the Sun- Earth L2. This study focuses on the transfer trajectories from the moon to the Halo orbit.
15:10
Break
15:35
AAS 12 - 188
Circular Restricted Three-Body Problem with Photonic Laser Propulsion
F.Y. Hsiao, P.S. Wu, Z.W. Cheng, Z.Y. Yang, J.W. Sun, H.K. Chen, H.Y. Chen, Y.T.
Jan, and D.H. Lien, Tamkang University
This paper studies the trajectory of spacecraft propelled by the photonic laser propulsion (PLP) system
under the environment of circular restricted three-body problem (CRTBP). The PLP system is an
innovative technology proposed by Dr. Bae. With repeated reflections of laser beam, it can generate
continuous and tremendous power by consuming very small energy. This paper studies the trajectory
under the CRTBP. At beginning, the PLP system At beginning, the PLP system is briefly introduced.
Then we model the PLP system a force potential, and the conventional procedure of analysis to the
CRTBP is applied. Numerical simulations are also provided.
16:00
AAS 12 - 189
Canonical Perturbation Theory for the Elliptic Restricted-Three-Body Problem
Brenton Duffy and David F. Chichka, The George Washington University
Canonical transformations of a Hamiltonian system may be generated using Deprit’s Lie transform
method such that the normalized system possesses ideal properties of integrability. The purpose of
this study is to derive an extension of Deprit's method to non-autonomous, bi-parametric Hamiltonian
systems and then to apply the extended method to the elliptic restricted three-body problem. The
elliptic restricted three-body problem is represented in terms of a doubly-expanded Hamiltonian
function and then normalized using the extended Deprit’s method. The resultant system is expressed
in Birkhoff normal form such that the stability of the equilibrium points may be analyzed using KAM
theory.
16:25
AAS 12 - 190
A Visual Analytics Approach to Preliminary Trajectory Design
Wayne R. Schlei and Kathleen C. Howell, Purdue University
Visual analytics, a new science that combines visualization, human-computer interaction, and
theoretical analysis, enhances the development of spacecraft trajectories in multi-body environments.
The application of visual analytics supplies an immensely powerful tool for rapid research and
development and access to a wider range of options for the construction of trajectories that meet
mission requirements.
This investigation connects spacecraft trajectory design with the
implementation of visual analytics, thereby merging visualization tools, numerical algorithms, and
designer knowledge into one expansive design approach.
Jan 31, 2012
Carolina B
Session 12: Spacecraft Guidance, Navigation, and Control I
Chair: Dr. Shyam Bhaskaran, Jet Propulsion Laboratory
13:30
AAS 12 - 191
Adaptive Pinpoint and Fuel Efficient Mars Landing Using Reinforcement
Learning
Brian Gaudet and Roberto Furfaro, The University of Arizona
Future missions to Mars will require advanced guidance algorithms that are able to adapt to more
demanding mission requirements, e.g. landing with pinpoint accuracy while autonomously flying fuelefficient trajectories. In this paper we will present a novel guidance algorithm using reinforcement
learning. Preliminary results show that one can achieve pinpoint landing accuracy with fuel
consumption comparable to that of current practice. The algorithm has the potential to considerably
expand the range of feasible landing sites. This appears, to the best of our knowledge, to be the first
application of reinforcement learning to the problem of autonomous planetary landing.
13:55
AAS 12 - 192
Design and Assessment of Open-loop Variable Coast Time Guidance for the
Mars Ascent Vehicle
Kevin E. Witzberger, NASA Glenn Research Center; Dave Smith, Wyle LLC
A variable coast time open-loop guidance scheme for NASA’s Mars ascent vehicle (MAV) is
described. An optimal two-stage trajectory is found using OTIS. The scheme utilizes a table lookup of
optimal OTIS Euler angles for the powered portion of flight. A Newton-Raphson root-finding
technique determines the upper stage ignition time that ensures the final altitude constraints are
satisfied. Allowing the ignition time to be a free variable is a simple and straightforward way to
accommodate environmental and hardware performance variations. The guidance scheme is
implemented in MASTIF. Robustness of the guidance scheme is tested with Monte-Carlo dispersion
simulations.
14:20
AAS 12 - 194
Flight-Path Control for Solar Sail Spacecraft
Geoffrey G. Wawrzyniak, a.i. solutions, Inc.; Kathleen C. Howell, Purdue University
Recent interest in missions to observe planetary poles or to communicate with an outpost at a lunar
pole has motivated investigations of trajectory options that utilize solar sails. Designing reference
trajectories and understanding their fundamental dynamics are necessary first steps toward flying
spacecraft in dynamically complicated regimes. However, the existence of a reference orbit alone is
insufficient for flight operations. Two variations of a turn-and-hold strategy are examined for flightpath control: an approach that implements multiple turns to achieve a target in an error-free scenario
and an approach that incorporates a receding-horizon strategy to accommodate representative errors.
14:45
AAS 12 - 195
Integrated Guidance and Attitude Control for Pinpoint Lunar Guidance Using
Higher Order Sliding Modes
Daniel R. Wibben and Roberto Furfaro, University of Arizona
A novel non-linear guidance and attitude control scheme for pinpoint lunar landing is presented.
Based on High Order Sliding Mode control theory, the proposed Multiple Sliding Surface Guidance
and Control (MSSGC) algorithm has been designed to take advantage of the ability of the system to
converge to the sliding surface in a finite time. The proposed approach is proven globally stable using
a Lyapunov-based approach. Preliminary results demonstrate that the MSSGC law not only drives the
spacecraft to the desired position with zero velocity, but also with the desired attitude and angular
rates.
15:10
Break
15:35
AAS 12 - 196
Waypoint-Optimized Zero-Effort-Miss/Zero-Effort-Velocity (ZEM/ZEV)
Feedback Guidance for Mars Landing
Yanning Guo, Matt Hawkins and Bong Wie, Iowa State University
This paper investigates the optimization approach to generate waypoint for the Mars landing problem
employing Zero-Effort-Miss/Zero-Effort-Velocity (ZEM/ZEV) feedback guidance. By dividing the
overall time into two or more time domains and discretizing dynamic equations in each segment, the
performance index and constraints are expressed as to-be-determined waypoints, converting the
original energy-optimal control problem to a nonlinear programming problem to find optimal
waypoints. This novel idea exploits parameter optimization techniques for feedback control
implementation, and combines the advantages of open-loop and closed-loop methods to achieve near
optimal performance with acceptable robustness, while meeting various practical restrictions and
requirements.
16:00
AAS 12 - 197
Zero-Effort-Miss/Zero-Effort-Velocity (ZEM/ZEV) Feedback Guidance:
Theory and Applications
Matt Hawkins, Yanning Guo and Bong Wie, Iowa State University
This paper investigates the use of Zero-Effort Miss/Zero-Effort Velocity (ZEM/ZEV) feedback
guidance for a variety of asteroid intercept and rendezvous missions. This guidance law is shown in
most cases to be more effective than classical laws, such as proportional navigation. Through
simulations, ZEM/ZEV guidance is compared with the open-loop optimal solution. It can approach
optimal performance, with the robustness advantages of feedback. Practical limitations, such as
collision avoidance and control saturation, are considered. A novel strategy for choosing one or more
waypoints to further improve performance is given.
Jan 31, 2012
Calhoun
Session 13: Orbit Determination I
Chair: W. Todd Cerven, The Aerospace Corporation
13:30
AAS 12 - 198
Dual Accelerometer Usage Strategy for Onboard Space Navigation
Renato Zanetti, The Charles Stark Draper Laboratory; Chris D'Souza, NASA
Johnson Space Center
This work introduces a dual accelerometer usage strategy for onboard space navigation. In the
proposed algorithm the accelerometer is used to propagate the state when its value exceeds a threshold
and it is used to estimate its errors otherwise. Numerical examples and comparison to other
accelerometer usage schemes are presented to validate the proposed approach.
13:55
AAS 12 - 199
Expected Navigation Flight Performance for the Magnetospheric Multiscale
(MMS) Mission
Corwin Olson, Cinnamon Wright and Anne Long, a.i. solutions, Inc.; Russell
Carpenter, NASA Goddard Space Flight Center
The Magnetospheric Multiscale (MMS) mission consists of four formation-flying spacecraft in highly
elliptical orbits about the Earth. The primary mission objective is to study magnetic reconnection.
The baseline navigation concept is the independent estimation of each spacecraft state using GPS
pseudorange measurements referenced to an Ultra Stable Oscillator (USO) and accelerometer
measurements during maneuvers. MMS state estimation is performed onboard each spacecraft using
the Goddard Enhanced Onboard Navigation System, which is embedded in the Navigator GPS
receiver. This paper describes the latest efforts to characterize expected navigation flight performance
using upgraded simulation models derived from recent analysis.
14:20
AAS 12 - 200
Minimum L1 Norm Orbit Determination Using A Sequential Processing
Algorithm
Steven Gehly, Brandon Jones, Penina Axelrad and George Born, University of
Colorado at Boulder
Orbit determination often involves processing noisy data containing outliers and biases, which result
from physical instrumentation and modeling errors. Least squares filters assume a Gaussian
distribution of the measurement errors, which may lead to poor performance for noisy data. The
minimum L1 norm filter has the potential to aid current orbit determination filters in the space
situational awareness (SSA) application. This paper develops a minimum L1 sequential processing
algorithm and demonstratesits effectiveness in processing noisy data. Results of testing indicate this
algorithm is a suitable first step toward removing the assumption of Gaussian error in the estimation
process.
14:45
AAS 12 - 201
Orbit Determination Based on Variations of Orbital Elements
Reza R. Karimi and Daniele Mortari, Texas A&M University
A novel technique of angles-only initial orbit determination based on variations of orbital elements is
presented. The fact that the estimated orbit, both shape and orientation, should remain constant at
every instant of time is the foundation of the new technique. The orbital elements are estimated for
every measurement and the residuals are minimized with respect to the unknown ranges. In this
formulation, the spacecraft ranges (leading to position and velocity vectors) along with the orbital
elements are estimated all together. This method is also capable of using multiple observations.
15:10
Break
15:35
AAS 12 - 202
Relative Navigation for Satellites in Close Proximity Using Angles-Only
Observations
Hemanshu Patel, Georgia Institute of Technology; Thomas Alan Lovell, Air Force
Research Laboratory; Andrew Sinclair, Auburn University; Ryan Russell, The
University of Texas at Austin
This research investigates relative navigation using angles-only observations. Observability issues
dictate that the unique relative orbit of a deputy satellite cannot be found using angles-only
measurements from the chief satellite when a linear relative motion model is used. This work
examines the possibility of partial observability in this case, which consists of a basis vector that
corresponds to a family of relative orbits. A Preliminary Orbit Determination method is introduced
that calculates an initial guess for the basis vector from three Line-of-Sight measurements. The
application of both batch and extended Kalman filters to this problem is explored.
16:00
AAS 12 - 203
Preliminary Assessment of Orbit Restitution Capability of a Multiple-Antenna,
GNSS Receiver on a Highly Elliptic Orbit Reaching above GNSS Altitude
Stefano Casotto and Massimo Bardella, Universita' di Padova; Alberto Zin, Thales
Alenia Space
Astronomical missions are often characterized by high altitude, highly elliptic orbits. We report on the
results of a study on the orbit determination capability of a receiver equipped with several GNSS
antennas on a 1,000 km by 25,000 km altitude orbit. Detailed visibility analysis shows how these
antennas can help extend the tracking periods to GNSS constellations. Account is taken of the side
lobe radio link allowed by the real GPS antennas radiation pattern. High accuracy OD is shown to be
possible due to the smooth character of the force field, even in the presence of unmodelled attitude
variations.
16:25
AAS 12 - 204
Second-Order Kalman Filter Using Multi-Complex Step Derivatives
Vivek Vittaldev and Nitin Arora, Georgia Institute of Technology; Ryan P. Russell,
The University of Texas at Austin; David Gaylor, Emergent Space Technologies, Inc.
The Second Order Kalman Filter (SOKF) uses second order Taylor series expansion (TSE) to account
for non-linearities in an estimation problem. In this work, the derivatives required for the SOKF are
computed using Multi-complex (MCX) derivatives. This method uses function overloading in order to
compute the derivatives to machine precision without having to compute the derivatives analytically.
Thus, the SOKF can be easily implemented, while at the same time having fewer tuning parameters
than the second order sigma-point filters. The standard SOKF is also extended by using a square-root
version and combining with Gaussian Mixture models (GMM).
Feb 1, 2012
Carolina A
Session 14: Lunar and Planetary Missions
Chair: Lauri Newman, NASA Goddard Space Flight Center
08:00
AAS 12 - 205
An Orbit Plan toward AKATSUKI Venus Re-encounter and Orbit Injection
Yasuhiro Kawakatsu, Chikako Hirose and Nobusaki Ishii, Japan Aerospace
Exploration Agency; Stefano Campagnola, Jet Propulsion Laboratory
On December 7, 2010, AKATSUKI, the Japanese Venus explorer reached its destination and tried to
inject itself into the Venus orbit. However, due to a malfunction of the propulsion system, the
maneuver was interrupted and AKATSUKI again escaped out from the Venus into an interplanetary
orbit. The telemetry data from AKATSUKI suggests the possibility to perform orbit maneuvers to
reencounter the Venus and retry the Venus orbit injection. Reported in this paper is an orbit plan
investigated under this situation. The latest results reflecting the test maneuver conducted in
September, 2011 is introduced as well.
08:25
AAS 12 - 206
Practical Design of 3D Phasing Orbit in Lunar Transfer Trajectory
Yasuhiro Kawakatsu, Japan Aerospace Exploration Agency
The moon is attracting attention again as a target of space exploration. To focus on the lunar transfer,
there is a sequence named ‘phasing orbit’ which is different from the widely used direct transfer
sequence. The design of the phasing orbit is simple under two body approximation, while the design
under practical condition faces with the problems, namely ‘orbit connecting problem’ and ‘phase
shifting problem’. In the paper, the methods to cope with these problems are clarified in detail with
concrete example.
08:50
AAS 12 - 207
Mission Analysis for the JUICE Mission
Arnaud Boutonnet and Johannes Schoenmaekers, HSO-GFA, ESA/European Space
Operations Centre
This paper presents the mission analysis of JUICE, a mission to study Jupiter, its environment and its
Galilean moons. This mission, inherited from EJSM Laplace, features new phases, like the Europa
fly-bys or the Jupiter high inclined orbits. The Europa phase required a very specific strategy that
minimises the radiation integrated dose. Jupiter high inclined orbits are obtained via resonant swingbys with Callisto. There are also updates of Laplace like the moon resonant transfer to Ganymede, but
also the Ganymede in-orbit science phase that uses frozen orbits based on the effect of Ganymede’s
gravity potential and Jupiter’s attraction.
09:15
AAS 12 - 208
Sensitivity Analysis of Non-Gravitational Perturbations on a Mercury Orbiter
Takahiro Kato, Benny Rievers, Jozef van der Ha and Claus Laemmerzahl, ZARM
This paper presents the effects of the non-gravitational forces acting on a Mercury orbiter. The effects
induced by the Albedo and the InfraRed radiations originating from Mercury’s surface are expected to
have significant effects on the orbital motion of the orbiter. Therefore, we study the effects of the
Albedo and the InfraRed radiations from the planet Mercury in addition to the Solar Radiation
Pressure and the Thermal Recoil Pressure. In order to obtain the practical illustration of the results, we
introduce several assumptions and the orbital elements of NASA’s MESSENGER mission.
09:40
Page 49 Break
10:05
AAS 12 - 209
Cassini Orbit Determination Performance (July 2008 - November 2011)
Frederic Pelletier, Peter Antreasian, Shadan Ardalan, Brent Buffington, Kevin
Criddle, Rodica Ionasescu, Robert Jacobson, Jeremy Jones, Sumita Nandi, Simon
Nolet, Daniel Parcher, Duane Roth, Jonathon Smith and Paul Thompson, Jet
Propulsion Laboratory
The Cassini spacecraft has now completed its prime and first extended mission and is now in its
second extension, flying its 160th Saturn revolution at the time of this meeting. After years of
stunning science returned to Earth, it is worth looking at one key engineering aspect of this mission
that made it all possible: navigation. This paper reports on the orbit determination performance from
July 2008 to November 2011. During this period, Cassini made 83 Saturn revolutions and had 50
targeted satellites flybys. Predicting the accuracy of the satellite ephemerides is a key challenge for
successful navigation.
10:30
AAS 12 - 210
Preliminary Mission Design for a Far-Side Solar Observatory using Low-Thrust
Propulsion
Jon Herman and Ron Noomen, Delft University of Technology
This paper discusses the preliminary mission design for a solar observatory placed on the far side of
the Sun by means of low-thrust propulsion to allow for prolonged far-side observation. The research
also investigates the heliocentric inclination that can be achieved with current or near-term propulsion
technology to evaluate the feasibility of high-latitude observations. The optimization of the low-thrust
trajectory is achieved through a direct method in a two-body model, using a nonlinear programming
method for optimization.
10:55
AAS 12 - 211
On-Orbit Sail Quality Evaluation Utilizing Attitude Dynamics of Spinner Solar
Sailer IKAROS
Yuichi Tsuda, Yuya Mimasu and Ryu Funase, Japan Aerospace Exploration Agency;
Yoshinobu Okano, Tokyo Metropolitan University
This paper describes a method of evaluating sail quality utilizing in-flight attitude behavior of
spinning solar sailer IKAROS. Since the successful deployment of the sail, IKAROS has received
SRP which strongly affects both translational and rotational motion of the spacecraft. Authors derived
the ‘Generalized Spinning Sail Model (GSSM)’ to reproduce the observed unique attitude behavior of
IKAROS. Following the previous work, this paper attempts to relate the GSSM with sail quality such
as flatness and reflectivity variation. This method is useful not only for on-orbit sail performance
evaluation, but also for quality assurance of sails in design and production processes.
11:20
AAS 12 - 212
Transfer of Impact Ejecta Material from the Surface of Mars to Phobos and
Deimos
L. Chappaz, H. J. Melosh, M. Vaquero and K. C. Howell, Purdue University
If successful, the Russian Phobos-Grunt mission will return approximately 200 grams of surface
material from Phobos to Earth in mid-August 2014. Although it is anticipated that this material is
mainly from the body of Phobos, there is a possibility that the sample may also contain material
ejected from the surface of Mars by large impacts. An analysis of this possibility is performed using
the best current knowledge of the different aspects of impact cratering on the surface of Mars and of
the productionof high-speed ejecta that might be able to reach Phobos or Deimos.
Feb 1, 2012
Carolina B
Session 15: Numerical and Analytical Trajectory Techniques
Chair: Angela Bowes, NASA Langley Research Center
08:00
AAS 12 - 213
A Closed Form Solution of the Two Body Problem in Non-Inertial Reference
Frame
Daniel Condurache, Technical University of Lasi
In this paper a closed form solution of the fundamental two-body problem in non-inertial reference
frame is presented. In order to obtain this solution a sym-bolic tensorial method is used. This approach
generates new prime integrals for the two-body problem and the solution can be used for any central
type interaction. If gravitational interaction is considered an explicit closed form solution is given
using the hypercomplex eccentric anomaly. This is a new method pro-posed by the author of the paper
andallows the solution to be expressed in a coordinate free vectorial form.
08:25
AAS 12 - 214
A Survey of Symplectic and Collocation Integration Methods for Orbit
Propagation
Brandon A. Jones, University of Colorado at Boulder; Rodney L. Anderson, Jet
Propulsion Laboratory
Demands on numerical integration algorithms for astrodynamics applications continue to increase.
Common methods, like explicit Runge-Kutta, meet most orbit propagation needs, but more
specialized scenarios require new techniques to meet both computational efficiency and accuracy
needs. This paper provides an extensive survey on the application of symplectic and collocation
methods to astrodynamics. Both of these methods benefit from relatively recent theoretical
developments, which improve their applicability to satellite orbit propagation. This paper also details
their implementation, with several tests demonstrating their advantages and disadvantages.
08:50
AAS 12 - 215
Appropriate Modeling of Solar Radiation Pressure Effects on Uncontrolled
Orbiting Objects for Accurate Dynamical Predictions
Jay W. McMahon and Daniel J. Scheeres, University of Colorado at Boulder
The study of this SRP effects are often made by using a constant force model with zero torques,
however improvement in the predictions can be made by using a more detailed model. This paper
contains a comprehensive discussion of the effects seen with highly detailed dynamical models versus
simplified models such as the cannonball model. The goal is to understand under what circumstances
a more simplified SRP model can sufficiently describe the effects on a given orbiting object. The
determination of the correct fidelity depends on the body properties, the dynamical state, and the time
horizon, which are studied here.
09:15
AAS 12 - 216
Assessment of a New Numerical Integration Technique in Astrodynamics
Ben K. Bradley, Penina Axelrad, Gregory Beylkin and Brandon A. Jones, University
of Colorado at Boulder
Faster numerical integration techniques are needed to cope with the large increase in the space catalog
that is expected due to improvements in tracking capabilities. This paper presents a new and
innovative numerical integration technique and compares its efficiency at propagating orbits to
existing techniques commonly used in astrodynamics today. This implicit Runge-Kutta scheme is
shown to require significantly fewer force function calls than other integrators through the use of
generalized Gaussian nodes and both low and high fidelity force models.
09:40
Page 51 Break
10:05
AAS 12 - 217
Analytical Stability Analysis of Displaced, Geostationary Orbits using
Perturbation Theory
Andrew Rogers, Ryan Stanley and Troy Henderson, Virginia Tech
Recent research on trajectory design using low-thrust propulsion has opened up new avenues in
orbital mechanics. One application is the displaced, geostationary orbit. A displaced orbit will afford
the stationary component of the GEO belt, but in a noncrowded environment, as well provide the
spacecraft with higher latitudes of continuous coverage. The equations of motion for this orbit are
highly nonlinear, but there is a determined stability below which a satellite will be able to maintain
station when perturbed, and above which the orbit will degrade. Specific perturbations will be
analyzed for linearized cases and then verified numerically.
10:30
AAS 12 - 218
Comparison of Delaunay Normalization and the Krylov-BogoliubovMitropolsky Method
Juan F. San-Juan, Luis M. Lopez, David Ortigosa and Martin Lara, University of La
Rioja; Paul J. Cefola, University at Buffalo (SUNY)
A scalable second-order analytical orbit propagator program (AOPP) is being carried out. This AOPP
combines modern and classical perturbation methods in function of orbit types or the requirements
needed for a space mission, such as catalog maintenance operations, long period evolution, and so on.
As a first step on the validation and verification of part of our AOPP, we only consider the
perturbation produced by the zonal harmonic coefficients in the Earth’s gravity potential, so that it is
possible to analyze the behavior of the mathematical expression involved in the corresponding
analytical theory in depth and determine its limits.
10:55
AAS 12 - 219
Detailed Analysis of Solar and Thermal Accelerations Acting on Deep-Space
Satellites
Takahiro Kato, Benny Rievers, Jozef van der Ha and Claus Laemmerzahl, University
of Bremen
This paper presents novel generic analytical and numerical approaches for modeling the Solar
Radiation Pressure and Thermal Recoil Pressure effects for high accuracy applications. Good fidelity
is achieved by implementing the detailed spacecraft model andthe operational history of the high-gain
antenna as well as the spacecraft articulations. Both analytical and numerical approaches are applied
in full detail to ESA’s current deep-space mission Rosetta during its cruise phases. The results of the
two approaches are compared and evaluated with respect to the actually observed non-gravitational
accelerations in orbit. The detailed analysis of the Thermal effects will also be presented.
11:20
AAS 12 – 220 Extension of the DSST Semi-analytical Theory Architecture
Paul J. Cefola, University at Buffalo (SUNY); Zachary J. Folcik, MIT/Lincoln
Laboratory; Chris Sabol, Air Force Research Laboratory; Keric Hill and Daron
Nishimoto, Pacific Defense Solutions, LLC
The semi-analytical theory replaces the Cowell equations with two formulas: differential equations
for the mean equinoctial elements, and short periodic formulas. There is a theory for the partial
derivatives. An interpolation strategy produces the outputs. The semi-analytical theory has been
interfaced with least squares and recursive estimation processes. Recently, the software architecture
was extended so (1) the mean element equations and mean partial derivatives can be integrated
backwards in time and (2) the epoch in a mean orbit determination process can have an arbitrary
location in an observation span. The current paper describes the continued testing of these new
capabilities.
Feb 1, 2012
Calhoun
Session 16: Asteroid and Near-Earth Object Missions II
Chair: Dr. Roby Wilson, Jet Propulsion Laboratory
08:00
AAS 12 - 221
Imaging LIDAR Mapping of an Asteroid for Autonomous Operations
B. Marsella, B. Udrea, P. Patel, D. Viane and M. Frederickson, Embry-Riddle
Aeronautical University; Paul Anderson, University of Colorado at Boulder
Autonomous proximity operations of an asteroid scout spacecraft are analyzed for the following
operations: specifying requirements for the guidance navigation and control subsystem of the
spacecraft, identifying performance metrics for on-board autonomy, and developing navigation and
mapping algorithms. The focus of the paper is on the asteroid mapping with the LIDAR and point
cloud reconstruction of the asteroid surface. The long term goal is to integrate the sensor models and
the algorithms into an onboard autonomy architecture controlled by a system such as Jet Propulsion
Laboratory's Continuous Activity Scheduling Planning Execution and Re-planning (CASPER).
08:25
AAS 12 - 222
Sensitivity Analysis of the Touchdown Footprint at (101955) 1999 RQ36
P. Patel, B. Udrea, B. Marsella, D. Viane and M. Frederickson, Embry-Riddle
Aeronautical University; P. Anderson, University of Colorado at Boulder; K.
Getzandanner, NASA Goddard Space Flight Center
The NASA Origins Spectral Interpretation Resource Identification Security Regolith Explorer
(OSIRIS-REx) mission is scheduled to launch in 2016. It is set to rendezvous with, map, and collect a
sample from asteroid (101955) 1999 RQ36 in 2019, and return the sample to Earth in 2023. This
paper addresses the analysis of the shapes and sizes of touchdown footprints for a spacecraft similar to
OSIRIS-REx and its spacecraft-to-asteroid relative velocity at touchdown. Furthermore, alternative
approaches for modeling the gravity field by finite and variable sphere models are examined for
simulations. Conclusions will be drawn regarding the suitability and efficiency of these models.
08:50
AAS 12 - 223
Refined Gravity Determination at Small Bodies through Landing Probes
Julie Bellerose, Carnegie Mellon University - NASA Ames Research Center
Spacecraft orbit determination at very small asteroids involves large error due to their very low mass.
This results in higher error on bulk density estimation, and can affect subsequent operation planning.
We investigate an additional mean for local gravity measurement using landing probes. The landing
dynamics can be retrieved from relative motion and through the spacecraft orbit determination. We
show simulations, performance, and mission concepts to measure and refine the mass and local
density of an NEA using probes released from a spacecraft.
09:15
AAS 12 - 224
Surface Gravity Fields for Asteroids and Comets
Yu Takahashi and D. J. Scheeres, University of Colorado at Boulder
The ultimate goal of a small body sample return mission is the retrieval of actual specimens from an
asteroid, and a spacecraft must operate in close proximity to the asteroid’s surface to this end.
However, the conventional expression of the spherical harmonic gravity field breaks down within the
Brillouin sphere. To overcome this problem, we will introduce the theory of the interior gravity field,
discuss the conversion between the spherical harmonic gravity field and the interior gravity field, and
present a method to numerically approximate the interior spherical harmonics from a shape model
with a homogeneous density distribution.
09:40
Page 53 Break
10:05
AAS 12 - 225
Preliminary Design of Hypervelocity Nuclear Interceptor Spacecraft for
Disruption/Fragmentation of NEOs
Alan Pitz, Brian Kaplinger and Bong Wie, Iowa State University
When the warning time of an Earth-impacting NEO is short, a nuclear explosive device (NED) may
become necessary to disrupt/fragment the target NEO. Given this situation, an original design of a
versatile hypervelocity nuclear interceptor spacecraft (HNIS) is needed to execute a nuclear disruption
option to the NEO. This paper describes the development of innovative technology and system
architectures to aid in the design and analysis of a two-body interceptor configuration, targeting
sensors, thermal shielding, and mission sequencing. Simulations using ADRC’s hydrodynamic code
are conducted to calculate the thermal and structural limitations of the HNIS.
10:30
AAS 12 - 226
Target Selection for a Planetary Defense Technology Demonstration Mission
Tim Winkler, Sam Wagner and Bong Wie, Iowa State University
During the past two decades, various technologies for mitigating the impact threat of near-Earth
objects (NEOs) have been proposed and studied. Mitigation methods include nuclear explosions,
kinetic impactors, and slow-pull gravity tractors. However, as of now, there is no consensus on how
to reliably deflect or disrupt a hazardous NEO in a timely manner, nor have any of the necessary key
technologies been validated on a flight demonstration mission. This paper presents at least 5 potential
asteroid candidates for a planetary defense technology demonstration mission currently being studied
at the Asteroid Deflection Research Center (ADRC).
10:55
AAS 12 - 227
The SIROCO Asteroid Deflection Demonstrator
Claudio Bombardelli, Technical University of Madrid; Andres Galvez and Ian
Carnelli, European Space Agency
The paper describes a space mission concept that could demonstrate some of the key technologies to
rendezvous with an asteroid and accurately measure its trajectory during and after a deflection
maneuver. The mission concept, called SIROCO, makes use of the recently proposed ion beam
shepherd (IBS) concept where a stream of accelerated plasma ions is directed against the surface of a
NEO to transmit a deflection force. We show that by carefully selecting the target NEO a measurable
deflection can be obtained in a few weeks of thrust with a small spacecraft and state of the art electric
propulsion hardware.
11:20
AAS 12 - 228
Validation and Application of a Preliminary Target Selection Algorithm for the
Design of a NEA Hopping Mission
Michael V. Nayak, Kirtland Air Force Base; Bogdan Udrea, Embry-Riddle
Aeronautical University
This paper describes the setup and results of an algorithm employed for preliminary asteroid target
selection for a manned multi-asteroid prospecting mission. The algorithm is used to determine the
order of transfer between viable targets, keeping delta-V at a minimum, minimizing the computational
burden of optimization and maximizing the number of targets visited within the mission timeline.
Based on distance from the originating asteroid, inclination change and planetary perturbation effects,
the algorithm is employed to support a ‘decision-tree’ approach to target selection, with results
validated using Satellite Tool Kit V.9.1’s Design Explorer and used to plan a six-asteroid hopping
mission.
Feb 1, 2012
Carolina A
Session 17: Trajectory Optimization II
Chair: Dr. Ryan Russell, The University of Texas at Austin
13:30
AAS 12 - 229
Homotopy Method for Solving Minimum Consumption Orbit Transfer Problem
Hao Huang, Pei Chen and Chao Han, Beihang University
Minimum consumption orbit transfer problem always leads to bang-bang optimal control problem,
and difficult to solve with shooting methods. A homotopy approach is proposed to deal with these
difficulties. Scaling techniques, global search for initial costates and modified RKF45 are combined
with homotopy approach to reduce the searching space of costates, increase the possibility to get the
global solution, and improve the precision of integration with discontinuous differential equations. A
numerical example is solved to illustrate the effectiveness of our method.
13:55
AAS 12 - 230
Integrated Launch Window Analysis and Precision Transfer Trajectory Design
for Mars Missions
Zhong-Sheng Wang, Embry-Riddle Aeronautical University
The iteration may not converge when linear correction is applied in precision transfer trajectory
design for interplanetary missions. It was shown that the ‘rope-climbing’ algorithm can be applied to
solve this problem effectively. This paper proposes amore efficient ‘rope-climbing’ scheme that leads
to faster convergence. Also discussed is the important practical issue of integrating launch window
analysis and precision transfer trajectory design for Mars missions. It is shown that an iterative
procedure can be used to resolve this issue effectively. This work and the author’s previous work
constitute a complete theory of conventional transfer trajectory design for Mars missions.
14:20
AAS 12 - 231
Iterative Model Refinement for Orbital Trajectory Optimization
Jennifer Hudson and Ilya Kolmanovsky, University of Michigan
An iterative trajectory optimization method is developed for optimal control of a low-thrust
spacecraft. A high-fidelity model and a low-fidelity model are used to iteratively refine solutions. The
high-fidelity model accurately represents the system but has high computational complexity, such that
numerical optimization is prohibitively time-consuming. The low-fidelity model can be used for
numerical optimization, but approximates the system dynamics with an unknown error. The iterative
model refinement method systematically reduces the difference between the two models and
converges on a solution with efficient execution time.
14:45
AAS 12 - 232
New Orbit Propagator for Motion Around an Oblate Planet
Vladimir Martinusi and Pini Gurfil, Technion - Israel Institute of Technology
This paper offers an alternative to the classical orbit variational equations, by proposing a new method
for the numerical integration of perturbed orbits. The actual nominal orbit is considered to be the so
called "J2 central orbit", which is modeled by the same initial value problem as the J2 problem, but
with the colatitude-dependent terms excluded. This initial value problem has a closed-form solution,
expressed using elliptic integrals, and it forms the generating solution for the perturbed problem.
15:10
Page 55 Break
15:35
AAS 12 - 233
Optimal Mission Planning for Agile Earth-Observing Satellites
Darin Toscano and Anil Rao, University of Florida
This paper examines the problem of planning a mission for an agile, Earth-observing satellite
(AEOS). The problem is broken into two stages of optimization. The inner loop explores time-optimal
reorientation of the AEOS to track an Earth-fixed target, while the outer loop attempts to optimally
sequence a list of targets to maximize the utility of the AEOS during the mission. The inner loop is
solved using computational optimal control techniques, while the outer loop is solved using a genetic
algorithm to perform a global search. Finally, an example problem is examined to discuss the
feasibility of this method.
16:00
AAS 12 - 234
Optimal Solar Sail Trajectory Analysis for Interstellar Missions
Xiangyuan Zeng and Junfeng Li, Tsinghua University; K. T. Alfriend, Texas A&M
University
Interstellar probe trajectory optimization using solar sails is investigated for a single solar photonic
assistance. A new objective function with a variable parameter is adopted to find the truly global-time
optimal solution using an indirect method. A technique of scaling the adjoint variables is used to make
the optimization much easier than before. The influence of the departure point from the Earth orbit is
discussed without consideration of the geocentric escape phase. During simulation, there is an
interesting discovery that the angular momentum reversal trajectory is a local-optimal solution, which
is discussed and compared with the direct flyby.
16:25
AAS 12 - 235
Optimal Use of Perturbations for Space Missions
Francesco de Dilectis and Daniele Mortari, Texas A&M University
In this study we use orbital perturbations as an aid in orbit design. Compared to previous studies, here
the combined effect of many different perturbations is taken into account, by using a propagator based
on the SGP4 method. Each satellite position on an assigned orbit can be considered a point in a 6-D
space, and each can be propagated either backward or forward in time to determine a trajectory in
such hyperspace. A genetic algorithm is then used to optimize the impulse sequence for maneuvers, or
thestarting point in the configuration space for perturbed designed orbits.
16:50
AAS 12 - 236
Recent Improvements to the Copernicus Trajectory Design and Optimization
System
Jacob Williams, ERC Inc.; David Lee, NASA Johnson Space Center; Cesar Ocampo,
The University of Texas at Austin; Juan Senent, Odyssey Space Research
The Copernicus trajectory design and optimization system represents a comprehensive approach to
on-orbit mission design, trajectory analysis and optimization. Copernicus allows the user to design
spacecraft missions, from simple to complex, to nearly all possible solar system destinations. The
system accommodates the use of many types of propulsion systems, any number of spacecraft, and
any user-definable force field model. This paper describes recent development of the tool at
NASA/JSC, including the implementation of new features to allow greater flexibility to design gravity
assist trajectories, halo orbit transfers, and low-thrust missions. Examples highlighting the
Copernicus approach to mission design are given.
Feb 1, 2012
Carolina B
Session 18: Attitude Dynamics and Control II
Chair: Dr. Don Mackison, University of Colorado
13:30
AAS 12 - 237
Attitude Stabilization Using Nonlinear Delayed Actuator Control with an
Inverse Dynamics Approach
Morad Nazari, Ehsan Samiei and Eric A. Butcher, New Mexico State University;
Hanspeter Schaub, University of Colorado at Boulder
The dynamics of a rigid body with nonlinear feedback control and actuator delay are considered. A
control law incorporating both delayed and non-delayed states is sought for the controlled system to
have the desired linear closed-loop dynamics using an inverse dynamics approach. The closed-loop
stability is shown to reduce to a second order linear delay differential equation for which the HsuBhatt-Vyshnegradskii stability chart can be used to choose the control gains that result in a stable
closed-loop response. Both analytical and numerical approaches are used to obtain the stability
characteristics, while the controlled simulations agree with the stability predictions.
13:55
AAS 12 - 238
Backstepping Simple Adaptive Attitude Control and Disturbance Rejection for
Spacecraft with Unmodeled Dynamics
Min Liu, Shijie Xu and Chao Han, Beihang University
Based on backstepping control algorithm, a nonlinear backstepping simple adaptive controller is
derived for spacecraft with unknown dynamics and disturbance. The spacecraft system is divided into
the dynamics subsystem and the kinematics subsystem. Firstly, the angular velocity is selected as the
intermediate control vector and a constant feedback intermediate control law is designed to stabilize
the kinematics subsystem. Then backing a step, using backstepping method, nonlinear simple adaptive
control method and Lyapunov-LaSalle approach, the backstepping adaptive attitude controller is
derived. Finally, a numerical example is studied to validate the efficiency of the controller.
14:20
AAS 12 - 239
Hybrid Method for Constrained Time-Optimal Spacecraft Reorientation
Maneuvers
Robert G. Melton, Pennsylvania State University
Time-optimal spacecraft slewing maneuvers with path constraints are difficult to compute even with
direct methods. This paper examines the use of a hybrid, two-stage approach, in which a particle
swarm optimizer provides a rough estimate of the solution,and that serves as the input to a
pseudospectral optimizer. Performance is compared between a particle swarm optimizer and a
differential evolution optimizer in the first stage.
14:45
AAS 12 - 240
Laboratory Experiments for Position and Attitude Estimation using the Cayley
Attitude Technique
Kurt A. Cavalieri, Brent Macomber and John E. Hurtado, Texas A&M University;
Manoranjan Majji, The State University of New York at Buffalo
Single point attitude determination is the problem of estimating the instantaneous attitude of a rigid
body from a collection of vector observations taken at a single moment in time. A new attitude
estimation technique uses a generalized Cayley transform and finds algorithms to optimally solve the
attitude estimation problem for a wide family of attitude parameters. The four dimensional Cayley
attitude technique provides an elegant solution to the single point position and attitude estimation
problem. Robustness of this technique in the presence of noise is tested through experiments at the
Land, Air, and Space Robotics Laboratory.
15:10
Break
15:35
AAS 12 - 241
Projective Geometry of Attitude Parameterizations with Applications to
Estimation
Sergei Tanygin, Analytical Graphics, Inc.
Vectorial attitude parameterizations, defined as products of the unit axis of rotation and various
functions of the rotation angle, can be viewed as projections from the unit quaternion hypersphere
onto a hyperplane tangential to this hypersphere. It is shown how additive and multiplicative errors
can be geometrically interpreted using projective geometry of vectorial parameterizations. It is also
shown how these errors can be propagated using variational equations derived and analyzed in the
general form. The effect of specific generating functions of the rotation angle on the attitude error
propagation is examined.
16:00
AAS 12 - 242
Under-Actuated Moving Mass Attitude Control for a 3U Cubesat Mission
Brad Atkins and Troy Henderson, Virginia Polytechnic Institute and State University
An internal, linear two moving mass actuator system is being developed for consideration for the
attitude control mechanisms of a Virginia Tech 3U CubeSat mission set to launch within the next
year. The rotational dynamics about the instantaneous center of mass are presented independent of
external torques followed by a full MATLAB dynamics simulation of moving mass profiles for a
system comparable to the actual 3U CubeSat setup. The dynamics simulation demonstrates roll, pitch,
and with coupled mass inputs, yaw maneuvers. The full paper will present both a linear and nonlinear
control approach for pointing maneuvers.
16:25
AAS 12 - 243
Using Kane's Method to Incorporate Attitude Dynamics in the Circular
Restricted Three Body Problem
A.J. Knutson and K.C. Howell, Purdue University
The dynamical framework in the circular restricted three body problem (CR3BP) has been explored
extensively in recent years for application to trajectory design; however, considerably fewer studies
incorporate the effects of spacecraft attitude in this regime. Recent work has explored the motion of a
single asymmetric rigid body in the vicinity of the Sun-Earth L2 point, using linear planar Lyapunov
orbit approximations. The goal of the current investigation is the examination of the effects of
combining attitude dynamics and non-linear orbital dynamics in the CR3BP, specifically offering
comparable results in the Earth-Moon system.
16:50
AAS 12 - 244
Using the Magnetospheric Multiscale (MMS) TableSat IB for the Analysis of
Attitude Control and Flexible Boom Dynamics for MMS Mission Spacecraft
Timothy John Roemer, Nicholas F. Aubut, William K. Holmes, Joshua Chabot,
Abigail Jenkins, Michael Johnson and May-Win L. Thein, University of New
Hampshire
The NASA Magnetosphereic Multiscale (MMS) Mission (to be launched in 2014) consists of four
spin-stabilized spacecraft (s/c) flying in precise formation. To analyze the MMS s/c with wire booms
up to 60m long, the UNH MMS TableSat IB, a limited 3-DOF rotation (full spin, limited nutation)
table top prototype of the MMS s/c, is used. A preliminary controller is implemented on TableSat IB
to observe the effects of spin rate and nutation control on the experimental s/c bus as well as the
scaled booms. The experimental results of the s/c bus are expected to match those of its analytical
simulation.
Feb 1, 2012
Calhoun
Session 19: Orbital Debris
Chair: Dr. Thomas Starchville, The Aerospace Corporation
13:30
AAS 12 - 245
An Orbital Conjunction Algorithm Based on Taylor Models
Roberto Armellin, Pierluigi Di Lizia, Alessandro Morselli and Michele Lavagna,
Politecnico di Milano
The study of orbital conjunctions between space bodies is of fundamental importance in space
situational awareness programs. The identification of potentially dangerous conjunctions, either
between Near Earth Objects and our planet, or space debris and operative spacecraft, is most
commonly done by looking at the distance between the objects in a given time window. A method
based on Taylor models and Taylor differential algebra is presented for the computation of the time
of closest approach and the minimum distance, including the effect that uncertainties on orbital
parameters and other quantities (e.g., spacecraft ballistic coefficient) produce on the conjunction.
13:55
AAS 12 - 246
Relative Dynamics and Control of an Ion Beam Shepherd Satellite
Claudio Bombardelli, Hodei Urrutxua, Mario Merino, Eduardo Ahedo and Jesus
Pelaez, Technical University of Madrid
The ion beam shepherd (IBS) is a recently proposed concept for modifying the orbit and/or attitude of
a generic orbiting body in a contactless manner, which makes it a candidate technology for active
space debris removal. In this paper we deal with the problem of controlling the relative position of a
shepherd satellite coorbiting at small separation distance with a target debris. After deriving the orbit
relative motion equations including the ion beam perturbation we study the system stability and
propose different control strategies.
14:20
AAS 12 - 247
Including Velocity Uncertainty in the Probability of Collision Between Space
Objects
Vincent T. Coppola, Analytical Graphics, Inc.
While there has been much research on computing the probability of collision between space objects,
there is little work on incorporating velocity uncertainty into the computation. We derive the formula
from first principles, including both position and velocity uncertainty. Moreover, trajectories will
evolve according to differential equations and not by approximating the relative motion. The end
result is a 3-dimensional integral over time on the surface of a sphere. We show that the formula
recovers the standard formula in the limit as the uncertainty approaches zero. Several examples will
show the impact of the velocity uncertainty on the probability.
14:45
AAS 12 - 248
Evaluating the Short Encounter Assumption of the Probability of Collision
Formula
Vincent T. Coppola, Analytical Graphics, Inc.
The formula for the probability of collision for space objects results from a myriad of assumptions
about the motion of the objects, not least of which is that the encounter duration is short. We develop
a formula that characterizes the encounter durationfor the conjunction of two space objects. We then
compute the encounter duration for every conjunction in an all-on-all assessment of the entire public
catalog. The encounter duration metric provides the means for assessing whether a conjunction
satisfies the short encounter assumption so that the standard collision probability metric is valid.
15:10
Page 59 Break
15:35
AAS 12 - 249
Lambert Targeting for On-Orbit Delivery of Debris Remediation Dust
Liam M. Healy, Naval Research Laboratory
Rapid delivery of material on-orbit (without regard to final velocity) is possible by pre-positioning on
orbit a vehicle with the intended cargo. If the goal is to reach a specified point in inertial space to
precede the return of another vehicle to that point using Lambert targeting, and there is a limit to the
amount of delta v available, then certain orbits are better choices than others. For dispensing a dust to
enhance drag for elimination of debris, I examine the combination of vehicles which gives the most
coverage to treat the most populous altitude band of satellites.
16:00
AAS 12 - 250
Spacecraft Debris Avoidance Using Positively Invariant Constraint Admissible
Sets
Morgan Baldwin and R. Scott Erwin, Air Force Research Laboratory; Avishai Weiss
and Ilya Kolmanovsky, University of Michigan
To cope with the rapidly growing amount of space debris, the spacecraft debris avoidance
maneuvering capabilities need to be developed. In this paper, we propose an approach to debris
avoidance maneuvering based on the use of safe positively invariant sets to steer the spacecraft, under
closed-loop control, around the debris. Simulation results are reported that illustrate this approach.
16:25
AAS 12 - 251
Target Identification and Delta-V Sizing for Active Debris Removal and
Improved Tracking Campaigns
Glenn E. Peterson, The Aerospace Corporation
Long-term projections of the low Earth orbit debris environment show the number of objects is
increasing, even without future launches. Various proposals have been made to mitigate the growth
including actively removing objects from orbit or tracking currently orbiting objects to a greater
degree of precision to facilitate more effective risk assessment. However, the cost of single removal or
tracking missions is most likely prohibitive. An alternative is for a single mission to engage multiple
targets. This paper determines desirable targets for such missions in terms of likelihood of future
debris production and minimization of delta-V requirements.
16:50
AAS 12 - 252
Tethered Tug For Large Low Earth Orbit Debris Removal
Lee Jasper, Hanspeter Schaub and Carl Seubert, University of Colorado at Boulder;
Valery Trushkyakov and Evgeny Yutkin, Omsk State Technical University
The low Earth orbit debris environment continues to be a concern for the space community. A debris
removal system is proposed which uses fuel reserves from the second stage of a heavy launch vehicle
after it has delivered its primary payload. Upon tethering (a Soyuz-like craft) to a large debris object,
such as a Cosmos-3M rocket body, a burn is performed to lower both objects’ periapses. The tether
dynamics are modeled similar to a spring-mass and then explored with emphasis on collision
avoidance. On-orbit dynamics reduce collision likelihood however throttle adjustments can also avoid
collisions.
Feb 2, 2012
Carolina A
Session 20: Earth Orbital Missions
Chair: Dr. Xiaoli Bai, Texas A&M University
08:00
AAS 12 - 253
APCHI Technique for Rapidly and Accurately Predicting Multi-restriction
Satellite Visibility
Xiucong Sun, Hongzheng Cui and Chao Han, Beihang University
Multi-restriction Satellite Visibility Prediction (MSVP) problem is of great significance in space
missions such as Earth observation and space surveillance. This paper presents a numerical method to
rapidly and accurately compute site-satellite and satellite-satellite access time, taking various
restrictions into consideration. APCHI (Adaptive Piecewise Cubic Hermite Interpolation) technique is
introduced to accomplish curve fitting for approximating waveforms that represent restriction
functions. Test results obtained from this approach are almost identical to those obtained with brute
force method but cost less time. At last, this method is more broadly applicable compared with other
methods advanced in this research area.
08:25
AAS 12 - 254
Landsat Data Continuity Mission (LDCM) Ascent and Operational Orbit
Design
Laurie Mann, Ann Nicholson and Susan Good, a.i. solutions, Inc.;Mark Woodard,
NASA Goddard Space Flight Center
For the past 40-years, Landsat Satellites have collected Earth’s continental data and enabled scientists
to assess change in the Earth’s landscape. The Landsat Data Continuity Mission (LDCM) is the next
generation satellite supporting the Landsat science program. LDCM will fly a 16-day ground repeat
cycle, Sun-synchronous, frozen orbit with a mean local time of the descending node ranging between
10:10 am and 10:15 am. LDCM is scheduled to launch in December 2012 on an Atlas 5 launch
vehicle. This paper will present the preliminary ascent trajectory design from the injection orbit to its
final operational orbit.
08:50
AAS 12 - 255
Launch Window Analysis for the Magnetospheric Multiscale Mission
Trevor Williams, NASA Goddard Space Flight Center
The NASA Magnetospheric Multiscale mission will study the magnetosphere using four spacecraft in
eccentric orbit, with launch in late 2014. The orbit must satisfy many constraints, both scientific and
engineering, at points months after launch. Mapping these to the launch orbit is complicated: the low
perigee gives significant oblateness effects; the high apogee gives significant lunisolar perturbations.
This paper describes a new launch window tool that uses a VOP equation model of the dominant
perturbations, plus geometric interpretations of the constraints, to produce (in 10 s on a laptop) a
graphical representation of the launch window for a given date.
09:15
AAS 12 - 256
Two Geometric Aspects of the Orbiting Carbon Observatory Mission
Mark A. Vincent, Raytheon Intelligence and Information Systems
Two completely separate analyses will be presented in this paper. They both have been performed in
support of the re-flight of the Orbiting Carbon Observatory (OCO-2). The first involves the location
that the mission has been allocated at the front of theA-Train. The geometry involved in safely staying
in front of JAXA’s soon-to-be-launched GCOM-W1 while avoiding the tail of the Morning
Constellation will be described. The other analysis involves the geometry in obtaining the OCO-2
measurements while in Glint Mode. The algorithms for calculating the Glint Spot on a smooth sphere
and an ellipsoid will be described and compared.
09:40
Break
10:05
AAS 12 - 257
Static Highly Elliptical Orbits Using Hybrid Low-Thrust Propulsion
Pamela Anderson and Malcolm Macdonald, University of Strathclyde
Newly proposed, static highly elliptical orbits using hybrid solar-sail/solar electric propulsion, for free
selection of ‘critical inclination’ are investigated. These orbits, termed Taranis orbits, use continuous
acceleration, to compensate for the drift in argument of perigee caused by Earth’s gravitational field.
Two cases are considered, firstly where the spacecraft launch mass is fixed which is shown to produce
negligible increase in mission lifetime. Secondly, the maximum thrust of the thruster is fixed, which is
shown to increase the lifetime of the mission. Strawman mass budgets are conducted for each case, as
well as sizing of solar arrays, propellant tanks and solar-sails.
10:30
AAS 12 - 258
Sun-Synchronous Orbit Slot Architecture: Analysis and Development
Eric Watson, California Polytechnic State University; T. Alan Lovell, Air Force
Research Laboratory
Growing concern over the space debris issue as well as a possible influx in space traffic will create a
need for increased space traffic management. Currently, an orbital slot framework is internationally
agreed upon for geostationary satellites. Sun-synchronous orbit is the next logical orbit regime to
apply a slot architecture, due to its population density and likely future growth. This paper furthers
work done in Sun-synchronous orbit slot architecture design by accomplishing in-depth analysis,
presenting a slot architecture based on the results of that analysis, and proposing a strategy for future
design.
10:55
AAS 12 - 259
Preliminary Design of a Mini-Satellite for Drag Estimation (MinDE)
D. Armstrong, R. Despins, C. Doerper, A. DuVal, M. Gambal, A. Garcia, D. Haller,
N. Murphy, G. Peters, J. Rubino, J. Slane, M. Wolfson, K. Fanelli and B. Udrea,
Embry-Riddle Aeronautical University; F. Herrero , NASA Goddard Space Flight
Center
The Mini-Satellite for Drag Estimation is a proposed design for a satellite capable of accurately
determining atmospheric densities in low Earth orbit. Current density values have error deviations of
10-15% arising from uncertainties in the measurements taken. It is the goal of the proposed satellite to
reduce this error to 1% or less. Reduction is possible through the careful design of the satellite's drag
coefficient and by employing highly accurate accelerometers and miniature mass spectrometers. The
paper presents the preliminary design of the satellite with detail of the mass, power, and link budgets.
Feb 2, 2012
Carolina B
Session 21: Orbit Determination II
Chair: Lisa Policastri, Applied Defense Solutions
08:00
AAS 12 - 260
Initial Orbit Determination via Gaussian Mixture Approximation of the
Admissible Region
Kyle J. DeMars and Moriba K. Jah, Air Force Research Laboratory
The concept of the admissible region for optical angles and their rates provides a convenient method
for bounding the set of all possible range/range-rate combinations that can provide Earth-bound orbit
solutions. Previous approaches to the problem of utilizing the admissible region for initial orbit
determination have implemented discretization schemes to generate either hypotheses or
triangulations which are then forecast in order to assimilate future incoming data. This work
investigates a method that applies Gaussian mixture approximations to the admissible region in order
to generate an initial probability density function that is associated with uniform ambiguity within the
admissible region.
08:25
AAS 12 - 261
Methods for Splitting Gaussian Distributions and Applications within the
AEGIS Filter
Kyle J. DeMars and Moriba K. Jah, Air Force Research Laboratory; Yang Cheng,
Mississippi State University; Robert H. Bishop, Marquette University
The tracking of space objects is characterized by the lack of frequent observations of the objects. As
such, long periods of time in which the object’s uncertainty must be propagated are often encountered.
The AEGIS filter has been proposed for uncertainty propagation. The AEGIS filter employs an online
adaptation of a Gaussian mixtures representation of the space object’s uncertainty by applying
splitting libraries.. This work examines several cost functions based on information theoretic
divergences in order to develop alternate splitting libraries and and assesses the libraries in the context
of uncertainty propagation for space object tracking.
08:50
AAS 12 - 262
Solution of the Liouville’s Equation for Keplerian Motion: Application to
Uncertainty Calculations
Manoranjan Majji, University at Buffalo; Kyle Alfriend and Ryan Weisman, Texas
A&M University
In the absence of process noise, the evolution of uncertainty for nonlinear dynamical systems is
governed by the stochastic Liouville’s equation. The first order, n-dimensional partial differential
equation can be solved in closed form by the method of characteristics. However, much simpler
techniques can be employed to solve this equation. This paper proposes the use of the transformation
of variables formula to develop a closed form analytic solution to the probability density function at
any time t, given the initial condition uncertainty in terms of a density function. Applications orbit
uncertainty calculations are also discussed.
09:15
AAS 12 - 263
Non-Linear Propagation of Uncertainty with Non-Conservative Effects
Kohei Fujimoto and Daniel J. Scheeres, The University of Colorado at Boulder
One topic of interest in space situational awareness (SSA) is the accurate and consistent representation
of an observed object's uncertainty under non-linear dynamics, which can be approached analytically
by employing a special solution to the Fokker-Planck differential equations for Hamiltonian
dynamical systems. In this paper, we expand this method to include the effects of non-conservative
forces. In order to describe the evolution of a pdf over time for a dynamical system with no diffusion,
one only needs to find the solution flow to the dynamics regardless of whether the forces are
conservative or not.
09:40
Break
10:05
AAS 12 - 264
Nonlinear Management of Uncertainties in Celestial Mechanics
Monica Valli, Roberto Armellin, Pierluigi Di Lizia and MichŠle Lavagna,
Politecnico di Milano
The problem of nonlinear uncertainty propagation represents a crucial issue in celestial mechanics. In
this paper a method for nonlinear propagation of uncertainties based on differential algebra is
presented. Working in the DA framework enables a general approach to nonlinear uncertainty
propagation that can provide high estimate accuracy with low computational burden. The nonlinear
mapping of the statistics is here shown adopting the two-body problem as working framework,
including coordinate system transformations. The general feature of the proposed method is also
demonstrated by presenting long-term integrations in a complex dynamical framework, such as the nbody problem.
10:30
AAS 12 - 265
Quadrature Methods for Orbit Uncertainty Propagation under Solar Radiation
Pressure
Matthew R. Turnowicz, Bin Jia, Ming Xin and Yang Cheng, Mississippi State
University; Kyle J. DeMars and Moriba K. Jah, Air Force Research Laboratory
Long-term orbit uncertainty propagation for space objects needs to account for the effect of solar
radiation pressure. With the flat-plate model for solar radiation pressure, the orbital motion is coupled
with the attitude motion, resulting in high-dimensional integration in propagation of the moments of
the orbital and attitude parameters. Three quadrature methods (the Monte Carlo method, the QuasiMonte Carlo method, and the sparse grid method) are applied to the moment propagation problem and
compared in simulation of geosynchronous orbits over one day, one week, and one month. The
quadrature methods are easy to implement and can handle Gaussian and non-Gaussian distributions.
Feb 2, 2012
Calhoun
Session 22: Spacecraft Guidance, Navigation, and Control II
Chair: Dr. Felix Hoots, The Aerospace Corporation
08:00
AAS 12 - 267
Application of the Generalized Transfer Equation for Mission Planning
Darren D. Garber, University of Southern California
This paper describes the Generalized Transfer Equation which extends the technique of patched
conics to now include any curve as a template to account for perturbed orbits and powered flight
trajectories. Through the derived Generalized Transfer Equation the velocity necessary to transfer
between any two orbits can be determined directly. The utility of this approach is demonstrated for
maneuver and mission planning by enabling the use of both impulsive maneuvers and low-thrust
profiles to model the trajectory.
08:25
AAS 12 - 268
Asymptotic Solution for the Two Body-Problem with Low-Thrust
Manuel Sanjurjo-Rivo, Universidad Carlos III; Claudio Bombardelli and Jesus
Pel ez, Universidad Politcnica de Madrid
An analytical solution of the restricted two-body problem with low thrust is derived. The
methodology to obtain the solution is based on perturbation theory techniques. The thrust magnitude
is represented by a small parameter, whereas the direction of the thrust is determined by two variable
angles. The mass variation along the trajectory and its impact on the low-thrust acceleration are also
accounted for. A comparison with high-accuracy numerical results is made in order to show the
suitability of the analytical solution to reproduce interplanetary trajectories and Earth orbit transfers
with small error.
08:50
AAS 12 - 269
Frozen Orbits for Scientific Missions Using Rotating Tethers
Hodei Urrutxua, Jesus Pelaez and Martin Lara, Technical University of Madrid
We give an insight into the potential applications of rotating space tethers for the exploration of
planetary satellites, pursuing a semi-analytic model that permits to study the influence of a tether in
the design of orbits of interest for science missions. This model eases the analysis of the long-term
evolution of the tether's attitude, unveiling a precession of its rotation plane. In addition, the model is
applied to the search for frozen orbits, revealing promising orbit stabilization features that allow for
the modification of frozen orbits by purely mechanical means, which leads to lower eccentricity
orbits.
09:15
AAS 12 - 270
Backstepping Adaptive Control for Flexible Space Structure with Noncollocated
Sensors and Actuators
Min Liu, Shijie Xu and Chao Han, Beihang University
A new nonlinear back-stepping adaptive control method is presented and applied to large flexible
structures with non-collocated sensor and actuator pairs. Utilizing the backstepping method,
decompose the structure system into a dynamic subsystem and a kinetic subsystem. The velocity
output is selected as a virtual control vector. A constant coefficient feedback intermediate control laws
is designed to stabilize the kinetic subsystem. Then the backstepping adaptive control law for flexible
structures is derived by Lyapunov theory and the positive real theory. Finally, a general example of
noncollocated flexible space structure is used to demonstrate the efficiency of the controller.
09:40
Page 65 Break
10:05
AAS 12 - 271
Simulation and Analysis of a Phobos-Anchored Tether
Andrew Klesh, Nathan Strange and Brian Wilcox, Jet Propulsion Laboratory
We investigate the dynamics and feasibility of a light-weight tether anchored to Phobos near Stickney
crater. The tether is initially deployed along the Mars-Phobos line with its tip sitting beyond the MarsPhobos L1 point. Unfortunately, trajectories near the L1 point are unstable, and there are
proportionally large disturbance forces (solar gravity, solar radiation pressure, the libration of Phobos,
the ellipticity of Phobos’ orbit, the Martian bulge and Deimos’s gravity) that can affect the movement
of the tether. Here we model the tether and simulate the evolution of its position to examine feasible
tether lengths and materials.
10:30
AAS 12 - 272
Solving and Analyzing Relative Lambert's Problem through Differential Orbital
Elements
Changxuan Wen, Yushan Zhao, Baojun Li and Peng Shi, Beijing University of
Aeronautics and Astronautics
With the application of differential orbital elements and Lagrange’s time equation, a novel approach is
developed to solve relative Lambert's problem on circular reference orbit. Then the problem is
analyzed to explain the causes and find out the conditions of singularity occurrence. Analytical results
reveal that any significant change of classical orbit elements with respect to the reference orbit will
lead to singularity. However, singularities can be avoided by adjusting the initial and final relative
positions properly.
10:55
AAS 12 - 273
Three Lambert Formulations with Finite, Computable Bounds
Marc DiPrinzio, The Aerospace Corporation
Three parameterizations of the classical Lambert problem are described. Relations are derived so the
flight path angle, true anomaly, and argument of perigee can each be used as the independent variable
to solve Lambert’s problem. It is shown that each of these parameters have finite, computable
bounds; therefore, the desired root is ‘bracketed’ in this known interval. While many root-finding
algorithms exist, some of these offer guaranteed convergence (at least theoretically) for a bracketed
root. These methods are unlikely to replace the elegant transformational methods of Battin or
Gooding, but remain of interest due to their novelty and simplicity.
AUTHOR INDEX
Author
Session
Ahedo, E.
19
Alfano, S.
2
Alfriend, K.
2, 17, 21
Allgeier, S.
6
Anderson, P.
16, 20
Anderson, R.
5, 15
Andersson, C.
11
Antreasian, P.
14
Ardalan, S.
14
Arena, V.
9
Armellin, R.
19, 21
Armstrong, D.
20
Arora, N.
13
Atkins, B.
18
Aubut, N.
18
Axelrad, P.
13, 15
Bae, J.
1
Bai, X.
7
Baldwin, M.
19
Baojun, L.
22
Barbee, B.
4
Bardella, M.
13
Bellerose, J.
4, 16
Bernelli-Zazzera, F.
5
Bester, M.
10
Betti, R.
5
Beylkin, G.
15
Biggs, J.
8
Bishop, R.
21
Bombardelli, C. 4, 16, 19, 22
Bonnell, J.
10
Born, G.
13
Boutonnet, A.
11, 14
Bradley, B.
15
Buffington, B.
14
Burton, R.
9
Butcher, E.
8, 9
Campagnola, S. 8, 11, 14
Carnelli, I.
16
Carpenter, R.
13
Carrico Jr., J.
10
Carter, T.
7
Casotto, S.
13
Cavalieri, K.
18
Cefola, P.
6, 15
Ceriotti, M.
8
Cersosimo, D.
4
Chabot, J.
18
Changxuan, W.
22
Chao, H.
6
Chappaz, L.
14
Chen, H.
11
Chen, P.
17
Cheng, Y.
3, 21
Cheng, Z.
11
Page 67 Author
Session
Chichka, D.
11
Condurache, D.
15
Coppola, V.
19
Cosgove, D.
10
Coverstone, V.
8
Crassidis, J.
2, 3
Criddle, K.
14
Cui, H.
6, 20
D'Amico, S.
10
Davis, J.
6
de Dilectis, F.
17
De Florio, S.
10
DeMars, K.
3, 21
DeSouza, L.
9
Despins, R.
20
Di Lizia, P.
19, 21
DiPrinzio, M.
22
Doerper, C.
20
D'Souza, C.
13
Duffy, B.
11
DuVal, A.
20
Erwin, R.
2, 19
Erwin, S.
6
Fanelli, K.
20
Ferrer, S.
3
Finkleman, D.
6
Fitz-Coy, N.
3, 6
Folcik, Z.
15
Folta, D.
10
Frederickson, M.
16
Frey, S.
10
Fujimoto, K.
21
Funase, R.
14
Furfaro, R.
4, 12
Galvez, A.
16
Gambal, M.
20
Gangestad, J.
2
Garber, D.
22
Garcia, A.
20
Gaudet, B.
12
Gaylor, D.
13
Gehly, S.
13
Getzendanner, K.
16
Good, S.
20
Goyal, P.
2
Grebow, D.
8
Grover, P.
11
Guan, H.
9
Gui, H.
9
Guo, Y.
12
Gurfil, P.
8
Gurfil, P.
17
Guzzetti, D.
5
Hamada, K.
2
Han, C. 1,6, 17, 18, 20, 22
Author
Session
Harms, A.
2
Haro, A.
4
Harris, M.
7
Hawkins, M.
12
Healy, L.
1, 19
Heiligers, J.
8
Henderson, L.
2
Henderson, T.
15, 18
Henshaw, G.
1
Herman, J.
14
Hernandez, S.
4
Hill, K.
15
Hirose, C.
14
Hogan, E.
6
Holmes, W.
18
Holzinger, M.
2
Horwood, J.
7
Howell, K. 11, 12, 14, 18
Hsiao, F.
11
Huang, H.
17
Huang, W.
6, 7
Hudson, J.
17
Hull, D.
7
Humi, M.
7
Hurtado, J.
3, 18
Intelisano, M.
10
Ionasecu, R.
14
Ishii, N.
14
Jacobson, R.
14
Jah, M.
2, 21
Jamison, B.
8
Jan, Y.
11
Jasch, P.
6
Jasper, L.
19
Jenkins, A.
18
Jia, B.
21
Jin, L.
9
Johnson, M.
18
Johnson, S.
3
Jones, B.
13, 15
Jones, D.
1
Jones, J.
14
Junkins, J.
7
Kaplinger, B.
16
Karimi, R.
13
Kato, T.
10, 14, 15
Kawakatsu, Y. 5, 11, 14
Kim, Y.
1
Klesh, A.
22
Knutson, A.
18
Kolmanovsky, I.
17 ,19
Krishna, D.
10
Krishnan, S.
8
Lacy, S.
3
Lämmerzahl, C. 10, 14, 15
Session
Author
Landau, D.
8
Lang, T.
2
Lantukh, D.
8
Lara, M.
3, 15, 22
Lavagna, M.
5, 19, 21
Lebois, R.
10
Lee, D.
17
Lee, S.
6
Leve, F.
9
Li, B.
5
Li, J.
17
Lien, D.
11
Lim, T.
3
Linares, R.
2, 3
Liu, M.
9, 18, 22
Locke, T.
10
Long, A.
13
Longman, R.
5, 9
López, L.
15
Lovell, A.
1
Lovell, T.
6, 13, 20
Lubey, D.
2
Luu, K.
2
Macdonald, M.
20
Macomber, B.
18
Majii, M.
18
Mann, L.
1, 20
Marchese, J.
10
Marsella, B.
16
Martinusi, V.
8, 17
McElrath, T.
8
McInnes, C.
4, 8
McLaughlin, C.
10
McMahon, J.
15
Melosh, H.
14
Melton, R.
18
Merino, M.
19
Messerschmid, E.
11
Mimasu, Y.
14
Mingotti, G.
5
Misra, A.
4
Missel, J.
8
Mondelo, J.
4
Morinelli, P.
10
Morselli, A.
19
Mortari, D. 3, 6, 8, 13, 17
Munoz, J.
5, 9
Nakamiya, M.
5, 11
Nayak, M.
9, 10, 16, 18
Nicholson, A.
20
Nishimoto, D.
15
Noomen, R.
14
Ocampo, C.
17
Okano, Y.
14
Olson, C.
13
Author
Session
Ortigosa, D.
15
Owens, B.
10
Pankow, D.
10
Parsay, K.
1
Patel, H.
13
Patel, P.
16
Pelaez, J.
19, 22
Pelletier, F.
14
Peng, S.
22
Peterson, G.
2, 19
Petropoulos, A.
11
Phan, M.
5
Pitz, A.
4, 16
Policastri, L.
10
Poore, A.
7
Radice, G.
10
Rao, A.
17
Reddy, S.
7
Rievers, B.
10, 14, 15
Rock, S.
9
Roemer, T.
18
Rogers, A.
15
Russell, R.
8, 11, 13
Sabol, C.
2, 15
Samiei, E.
9, 18
San-Juan, J.
15
Sanjurjo-Rivo, M.
22
Schaub, H. 1, 6, 9, 18, 19
Scheeres, D. 2, 15, 16, 21
Schlei, W.
11
Schoenmaekers, J. 11, 14
Senent, J.
17
Seubert, C.
1, 19
Sherrill, R.
1, 6
Shi, P.
5
Shi, Y.
5, 9
Shimanjuntak, T.
5
Simo, J.
4
Sinclair, A.
1, 6, 13
Singh, N.
7
Smith, D.
12
Spencer, D.
2
Stanley, R.
15
Starek, J.
9
Stevenson, D.
1
Stiles, L.
1
Strange, N.
8, 22
Subbarao, K.
2
Sugimoto, Y.
5
Sun, J.
11
Sun, X.
20
Takahashi, Y.
16
Tanygin, S.
3, 18
Tasker, F.
3
Tewari, A.
7
22nd AAS/AIAA Space Flight Mechanics Meeting Author
Session
Thein, M.
18
Tichy, J.
1
Topputo, F.
5
Toscano, D.
17
Trumbauer, E.
5
Tsuda, Y.
14
Turnowicz, M.
21
Udrea, B.
16, 20
Urrutxua, H.
19, 22
Valery, T.
19
Vallado, D.
6
Valli, M.
21
van der Ha, J. 10, 14, 15
Vaquero, M.
14
Vardaxis, G.
4
Viane, D.
16
Villac, B.
4, 5
Vincent, M.
20
Vittaldev, V.
13
Wagner, S.
16
Wang, Y.
4
Wang, Z.
17
Watson, E.
20
Wawrzyniak, G.
12
Weisman, R.
21
Weiss, A.
19
Wetterer, C.
2
Whalley, S.
2
Wibben, D.
12
Wie, B.
4, 12, 16
Wiesel, W.
5
Wilcox, B.
22
Williams, J.
17
Williams, P.
2
Williams, T.
1, 20
Winkler, T.
16
Witzberger, K.
12
Woo, P.
4
Woodard, M.
10, 20
Wright, C.
13
Wu, P.
11
Xin, M.
21
Xiucong, S.
6
Xu, S.
4, 9, 18, 22
Yang, Z.
11
Yin, J.
1, 6
Yushan, Z.
22
Yutkin, E.
19
Zanetti, R.
3, 13
Zeng, X.
17
Zhang, H.
5
Zhao, Y.
5
Zhu, M.
9
Zimmer, A.
11
Page 68 Draft Version January 2, 2012 6:44:00 PM
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22nd AAS/AIAA Space Flight Mechanics Meeting
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22nd AAS/AIAA Space Flight Mechanics Meeting Page 72

Table of Contents - Space Flight Mechanics Committee

Transcription

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