utsi piper navajo airborne science experimenter`s handbook

UTSI PIPER NAVAJO
AIRBORNE SCIENCE
EXPERIMENTER’S HANDBOOK
AVIATION SYSTEMS PROGRAM
UNIVERSITY OF TENNESSEE SPACE INSTITUTE
TULLAHOMA, TENNESSEE
1 DECEMBER 2011
1
LIST OF REVISIONS
Rev
Date
Change
Originator
0
04 FEB 09
Original
Martos & Corda
1
17 FEB 09
Formatting
Corda
2
1 DEC 11
Update, add Appendix (Spec Sheets)
Simmons
2
Preamble ........................................................................................................................................ 5
List of Acronyms ........................................................................................................................... 6
Chapter 1 Aircraft Description ................................................................................................... 7
1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 Introduction .............................................................................................................................................. 7 Basic Dimensions ................................................................................................................................. 10 Weights .................................................................................................................................................... 10 Power Plant ............................................................................................................................................ 10 Production Air Data System .............................................................................................................. 10 Selected Performance Data and Charts .......................................................................................... 11 Aircraft Deck Angle ............................................................................................................................ 14 Cockpit Layout and Seating Arrangement .................................................................................... 15 Chapter 2 Interior Dimensions .................................................................................................. 17
2.1 2.2 General Dimensions ............................................................................................................................ 17 Fuselage Access .................................................................................................................................... 18 Chapter 3 Communication and Navigation.............................................................................. 19
3.1 3.2 3.3 Very High Frequency (VHF) Radio................................................................................................ 19 Global Positioning System Unit ....................................................................................................... 19 Cockpit and Cabin Video System .................................................................................................... 19 Chapter 4 Electrical Power ........................................................................................................ 20
4.1 4.2 General Description ............................................................................................................................. 20 Power Interface ..................................................................................................................................... 21 Chapter 5 Data Acquisition and Baseline Instrumentation .................................................... 22
5.1 General Data Acquisition System (DAS) Information .............................................................. 22 5.1.1 Dedicated Data Acquisition for Airborne Science Research .................................... 24 5.2 DAS Interface ........................................................................................................................................ 25 5.2.1 DAS Signals Overview ........................................................................................................ 25 5.2.2
Analog Signal Interface ....................................................................................................... 26 5.2.3
Thermocouple Signal Interface ......................................................................................... 27 5.3 Research Air Data System ................................................................................................................. 28 5.4 Equipment Rack .................................................................................................................................... 29 Chapter 6 Experiment Locations .............................................................................................. 30
6.1 6.2 6.3 6.4 6.5 General Description ............................................................................................................................. 30 Breadboard Table ................................................................................................................................. 31 Radome .................................................................................................................................................... 35 Engine Nacelle Locker Boxes........................................................................................................... 36 Rear Baggage Compartment ............................................................................................................. 37 3
Chapter 7 Experiment Design and Integration ........................................................................ 38
7.1 Construction Guidelines ..................................................................................................................... 38 7.1.1 Electrical Wiring ................................................................................................................... 38 7.1.2 Assembly ................................................................................................................................. 38 7.1.3 Load Factor ............................................................................................................................. 38 7.1.4 Hazardous Materials ............................................................................................................. 38 Chapter 8 Flight Clearance Process .......................................................................................... 39
8.1 Flight Safety Process ........................................................................................................................... 39 Chapter 9 Flight Operations ...................................................................................................... 40
Appendix I Contact Information ............................................................................................... 41
Appendix II Instrumentation List ............................................................................................. 42
Appendix III Flight Operations Safety Manual ....................................................................... 44
Appendix IV Equipment Specifications .................................................................................... 45
4
PREAMBLE
The UTSI Piper Navajo Airborne Science Experimenter’s Handbook provides information to
prospective users for integration and flight test of airborne science sensors, equipment, and
experiments. The information contained in this handbook represents general guidance and
standard practices that will assist users in their system design, integration, and flight testing. The
UTSI Aviation Systems and Flight Research Program will work closely with each user, including
identifying any special requirements or deviations from the guidance provided in this handbook.
5
LIST OF ACRONYMS
AC
Advisory Circular (issued by the Federal Aviation Administration)
AHRS
Attitude and Heading Reference Sensor
DAQ
Data Acquisition
DAS
Data Acquisition System
FS
Fuselage Station
GNS
Global Navigation System
GPS
Global Positioning System
ILS
Instrument Landing System
PB
Precision Barometer
PPT
Precision Pressure Transducer
SEPS
Supplementary Electrical Power System
UDP
Universal Datagram Packet
UPS
Uninterruptible Power Supply
UTSI
University of Tennessee Space Institute
VOR
Very High Frequency Omni-Directional Radio Range
WAAS
Wide Area Augmentation System
6
CHAPTER 1 AIRCRAFT DESCRIPTION
1.1
Introduction
The PA-31 Navajo (Figure 1) is a cabin-class, twin-engine aircraft designed and built by Piper
Aircraft, Vero Beach, Florida for the general aviation market. The aircraft has a wingspan of
40.67 ft (12.40 m), fuselage length of 32.625 ft (9.944 m), and a maximum gross weight of 6,500
lbs (2,948 kg). The UTSI Navajo can carry a maximum crew of six, nominally two pilots in the
cockpit and four aircrew or passengers in the main cabin.
The Navajo is powered by two turbocharged Lycoming TIO-540-A series, six cylinder, fuel
injected engines rated at 310 horsepower each. An oxygen system provides supplementary
oxygen for crew and passengers. The aircraft has a service ceiling of 26,300 ft (8,016.2 m).
7
Figure 1. Piper Navajo three-view drawing
8
8
Figure 2. Equipment integration locations
1.
2.
3.
4.
5.
6.
7.
8.
Right engine nacelle wing locker
Rear baggage compartment
Aft fuselage 19-inch rack
Fuselage breadboard table
Main cabin area
Left engine nacelle wing locker
Nose radome bay
Belly Pod
9
1.2
Basic Dimensions
Wing Span, ft (m)
Wing Area, sq ft (sq m)
Length, ft (m)
Height, ft (m)
Wing Loading, lbs per sq ft (kg per sq m)
Power Loading, lbs per HP (kg per watt)
Propeller Diameter, in (m)
Turning Radius (Nose Wheel), ft (m)
1.3
6,536
6,500
6,200
4,387
2,113
(2,965)
(2,948)
(2,812)
(1,990)
(958)
Power Plant
Engine Type
Rated Horsepower, HP (Watts)
Rated Speed (rpm)
Bore, inches (m)
Stroke, inches (m)
Displacement, cubic inches (cubic m)
Compression Ratio
Dry Weight, lbs (kg)
1.5
(12.39)
(21.3)
(9.946)
(3.962)
(139)
(0.00639)
(2.0)
(8.5)
Weights
Ramp Weight, lbs (kg)
Gross Weight, Takeoff, lbs (kg)
Gross Weight, Landing Max
Empty Weight (standard, six-place), lbs (kg)
Useful Load (standard, six-place), lbs (kg)
1.4
40.67
229
32.63
13.00
28.4
10.5
80
28
Lycoming TIO-540-A
310
(231,167)
2,575
5.125 (0.1301)
4.375 (0.1111)
541.5 (0.008873)
7.3:1
535.0 (242.67)
Production Air Data System
The production air data system consists of one pitot tube and four static pressure ports.
The pitot tube is mounted on the lower surface of the aircraft nose, forward of the nose
landing gear doors. The static ports are flush mounted on the aft fuselage, forward of the
horizontal stabilizer, two ports each on the left and right side fuselage, respectively. The
two left and right side ports are plumbed to the left and right cockpit instruments,
respectively.
10
1.6
Selected Performance Data and Charts
All figures in this section are for the standard PA-31 airplane, flown at maximum gross
weight under standard conditions at sea level unless otherwise stated.
Take-off Run, ft (m)
Take-off Distance over 50-ft barrier, ft (m)
Minimum Controllable Single Engine Speed, mph (km/hr)
Best Rate of Climb Speed, mph (km/hr)
Best Rate of Climb, ft/min (m/min)
Best Angle of Climb Speed, mph (km/hr)
Best Single Engine Rate of Climb Speed, mph (km/hr)
Best Single Engine Rate of Climb, ft/min (m/min)
Best Single Engine Angle of Climb Speed, mph (km/hr)
Service Ceiling, ft (m)
Absolute Ceiling, ft (m)
Single Engine Service Ceiling, ft (m)
Single Engine Absolute Ceiling, ft (m)
Top Speed at 15,500 feet, mph (km/hr)
Cruising Speed (75% power at sea level), mph (km/hr)
Cruising Speed (75% power at 23,500), mph (km/hr)
Optimum Cruising Speed (65% power at 24,000), mph (km/hr)
Stalling Speed (gear and full flaps) (power off), mph (km/hr)
Stalling Speed (gear and flaps up) (power off), mph (km/hr)
Fuel Consumption (75% power) (both engines), gph (lph)
Fuel Consumption (65% power) (both engines), gph (lph)
Cruising Range (75% power at 23,500 ft), mi (km)
Cruising Range (65% power at 24,000 ft), mi (km)
Cruising Range (45% power at 24,000 ft), mi (km)
1730 (527.3)
2,280 (694.9)
85
(137)
110
(177)
1395 (425.2)
95
(153)
110
(177)
245
(74.7)
106
(171)
26,300 (8,016.2)
27,300 (8,321.0)
15,800 (4,815.8)
16,400 (4,998.7)
260
(418)
201
(323)
247 (398)
231
(372)
73
(117)
80
(129)
35.6 (135)
27.8 (105)
1,300 (2,092)*
1,120 (1,802)**
1,560 (2,511)*
1,390 (2,237)**
1,685 (2,712)*
1,550 (2,494)**
* 190 gals usable fuel
**45 min reserve
11
Figure 3. Cruise range versus density altitude
12
Figure 4. Multi-engine climb performance
13
1.7
Aircraft Deck Angle
The aircraft deck angle, defined as the angle of the fuselage reference line with respect to the
horizon or “flat” earth, is a function of the aircraft angle-of-attack and hence the aircraft
airspeed. The deck angle is given as a function of airspeed in Figure 5 for the “clean” (landing
gear up and flaps up) and power approach (landing gear down and flaps full down) aircraft
configurations.
Figure 5. Aircraft deck angle versus airspeed
14
The fuselage belly may be assumed to be parallel to the fuselage reference line, therefore the
deck angle should be considered if it is critical for experiments, mounted on the aircraft belly, to
be parallel to the horizon in flight. It may be required to mount experiments such that the deck
angle is cancelled at a specified airspeed or range of airspeeds.
1.8
Cockpit Layout and Seating Arrangement
The aircraft cockpit provides side-by-side seating for a pilot and co-pilot (Figure 6). The
cockpit has full dual flight controls and full dual flight instruments for the pilot and copilot. The throttle, propeller, and mixture controls are located between the pilot and copilot seats.
Figure 6. Cockpit layout
The aircraft main cabin provides space for passenger seating and/or cargo (Figure 7). A
maximum of four seats can be installed in the main cabin, two on the left and two on the
right side of the cabin. The individual seats can be installed facing forward or aft. Cabin
ventilation, heating, and overhead lighting are provided at each seat location.
15
Figure 7. Main cabin seating arrangement (view looking forward)
16
CHAPTER 2 INTERIOR DIMENSIONS
2.1
General Dimensions
The cabin is approximately 174 inches (4.4196 m) long (FS 100-274), 30 inches (0.762 m) wide,
and has a height of approximately 46 inches (1.1684 m). Fuselage station numbers are given in
Figure 7.
Figure 8. Fuselage station number diagram
17
2.2
Fuselage Access
Entry to the aircraft is through the aft cabin door (located between FS 209.5 and FS 244). The
door opening is 26 inches (0.6604 m) wide by 45 inches (1.143 m) high (Figure 8).
Figure 9. Fuselage access
18
CHAPTER 3 COMMUNICATION AND NAVIGATION
3.1
Very High Frequency (VHF) Radio
The aircraft is equipped with a Bendix / King KY-196 communications radio mounted in the
cockpit instrumentation panel. The radio has a 16 watts minimum power output.
3.2
Global Positioning System Unit
The aircraft is equipped with a Garmin GNS 530W mounted in the cockpit instrumentation
panel. The unit is an all-in-one GPS/Nav/Comm with a WAAS-certified GPS, 200-channel
ILS/VOR with localizer and glide slope, and a 2,280-channel capacity radio.
3.3
Cockpit and Cabin Video System
The aircraft cockpit has an onboard, closed-circuit camera system. The camera can be positioned
to record the pilot, co-pilot, or aft-cabin flight crew.
19
CHAPTER 4 ELECTRICAL POWER
4.1
General Description
The electrical system includes a 24 volt, 17 ampere hour battery enclosed in a sealed stainless
battery box located in the nose of the aircraft. Two 28 volt, 70 ampere alternators are installed.
The alternators operate in parallel by use of one voltage regulator to control field voltage for both
units. An over voltage relay is also incorporated in the system. Its function is to open and remove
field voltage to the unregulated alternators in the event of a failure of the voltage regulator, thus
preventing an over voltage condition that could damage electrical equipment.
An external power receptacle is installed in the lower left fuselage nose section. This allows the
utilization of electrical power from external sources such as 24 volt generators or battery carts to
aid in starting or to provide external power for operation of electrical systems without
discharging the onboard battery.
An instrumentation bus isolates research systems from the production aircraft systems. The bus
is capable of supporting 20 amps and has a current baseline load of 10 amps. This bus feeds the
DAS Power Distribution Panel and powers the core instrumentation on the airplane. DC-DC
converters provide +5 VDC and +15 VDC are provided through the instrumentation bus. A 120
VAC, 5.1 amp AC inverter runs off this bus. . An Uninterruptible Power Supply (UPS) can also
be added as required.
A second bus provides power to the Experiment Power Panel. This isolates experiment power
from the production aircraft systems and the instrumentation bus. The Experiment Power Panel
is supplied 30 amps at 28 volts. A 120 VAC, 9.5 amp inverter runs off this bus to provide AC
experiment power.
A Supplementary Electrical Power System (SEPS) is available if required. The SEPS provides
55 amp hours at 24 volts DC. The SEPS power is independent of the aircraft power, although it
is controlled by a relay that is powered by the Experiment Power Panel. In flight, the pilot can
control the SEPS through the Experiment Power Switch.
20
4.2
Power Interface
21
Figure 10. Instrumentation system power interface
CHAPTER 5 DATA ACQUISITION AND BASELINE INSTRUMENTATION
5.1
General Data Acquisition System (DAS) Information
The aircraft has significant data acquisition capabilities and commercial off the shelf interfaces
for supporting airborne science. As shown in Figure 11, there are several ways that airborne
science instruments can interface to the DAS. The DAS can host a scientific instrument
completely within its capabilities or the system can act as a data source for airborne science
instruments. As a data source, the DAS provides aircraft parameters relevant to airborne science
missions either directly to the instruments or to the recording systems over commercial off the
shelf interfaces such as Universal Datagram Packets (UDP).
Thermocouples
GPS
Serial Port
Ethernet
AHRS
LAN 1
Static
Pressure
Ethernet
DAS
Dynamic
Pressure
Analog
Sensors,
Radiometers &
Digital RPM
LAN 2
Ethernet
LAN 3
USB 1
USB 2
USB 3
USB 4
Hygrometer
Tablet
Aircraft
PC
Audio
Pyrometer
RS-232
Core
Analog, Digital
Serial
& Counter Channels
Airborne Science
Figure 11. DAS functional diagram
22
The primary data acquisition computer is a National Instruments (NI) PXI-8104 with a Celeron
M 1.83 GHz controller running Windows XP and LabVIEW software. The DAS records over 80
parameters at 10 samples per second with the exception of the GPS signal which is logged at 1
sample per second. Increased sample rates can be obtained with a decreased number of
parameters.
LabVIEW software applications are available in the DAS computer to perform data acquisition
tasks. Sensors can be connected directly to the DAS channels or to a user provided instrument
over USB connections.
Please refer to Appendix II for a list of recorded parameters. The most commonly requested
include the following.






GPS position (latitude, longitude, altitude)
Air data (airspeed, altitude and outside air temperature)
Aircraft angle of attack and angle of sideslip
Aircraft attitudes (pitch, roll, and yaw angles)
Aircraft linear accelerations (normal, longitudinal and lateral accelerations)
Aircraft angular rates (pitch, roll, and yaw rates)
The GPS position is obtained from the onboard GPS unit. The air data is obtained from the
aircraft research air pitot-static system and temperature sensor. The angle of attack and angle of
sideslip are obtained from the aircraft flow angle sensors. The aircraft attitudes, linear
accelerations, and angular rates are obtained from the onboard Attitude Heading Reference
System (AHRS).
The DAS offers the following connectivity.




3 ethernet 100 Mbps base T (Cat 5E) ports
1 RS-232 serial port
4 USB 2.0 ports where any of the following devices are available
 RS-232 serial converter for serial data acquisition
 NI USB 6218 data acquisition unit with 16 differential and 32 single ended analog
measurements
 CD/DVD writer
 Solid state memory stick
An additional 10 thermocouple, 10 single ended analogs, and 32 discrete inputs are
available
The aircraft audio transmissions (VHF communications and intercom) are recorded and stored in
a time stamped file.
23
One tablet PC and 4 Ultra Mobile PC’s are available for data logging and visualization. Ethernet,
serial, and USB ports are available on these units. The software interface of each unit is fully
configurable for individual user needs. User provided personal computers, either desktop or
laptop, can also be added to the network.
5.1.1
Dedicated Data Acquisition for Airborne Science Research
A National Instruments NI USB-6218 DAQ card is available for the experimenter to
connect sensors directly to the onboard data acquisition system or to an independent
computer, e.g. a standard laptop computer, tablet PC, or UltraMobile PC.
Serial I/O is expanded by an external NI-USB-232 USB 2.0 Serial I/O. It can be
connected directly to the DAS or to another computer.
The following channels are available on the DAQ card.






32 analog inputs (16-bit, 250 kS/s)
2 analog outputs (16-bit, 250 kS/s)
8 digital inputs
8 digital outputs
Two 80 Mhz 32-bit counters
60 V CAT I isolation for improved accuracy, safety, and built-in signal
connectivity
24
5.2
DAS Interface
5.2.1
DAS Signals Overview
Figure 12. DAS signals overview
25
5.2.2 Analog Signal Interface
Figure 13. Analog signal interface schematic
26
5.2.3 Thermocouple Signal Interface
Figure 14. Thermocouple signal interface schematic
27
5.3
Research Air Data System
The research air data system is independent of the production air data system. The systems
include a Kiel probe, a standard total pressure probe, a static pressure mast, and a total
temperature probe. The probes are mounted on the left fuselage, forward of the wing and aft of
the nose baggage compartment door.
Figure 15. Research air data system probes
28
5.4
Equipment Rack
A standard 19-inch equipment rack is located in the aft section of the main cabin. The rack
houses the DAS, two inverters, network switch, two NI DAQs and a power strip. Somerack
space is available for mounting user equipment.
Figure 16. Standard 19-inch equipment rack in main cabin
29
CHAPTER 6 EXPERIMENT LOCATIONS
6.1
General Description
The aircraft main cabin provides a large area for both passengers and equipment. Seating for a
maximum of six passengers is available. With the passenger seats removed, there are 82 inches
(2.08 m) of space between the forward cabin divider (main wing spar location) and the aft cabin
instrumentation rack (FS 140-222). This cabin area has a volume of 110 cubic feet (3.11 cubic
meters). The main cabin is accessible through the aft cabin door on the left fuselage.
There are two large baggage compartments in the Navajo, the forward, nose radome
compartment and the rear baggage compartment in the aft cabin. The Navajo is also equipped
with wing lockers on each engine nacelle.
Figure 17. Main cabin with seating removed
30
6.2
Breadboard Table
A 24 inch (0.6096 m) long by 18 inch (0,4572 m) wide breadboard table (Figure 17) is located in
the main cabin. The table mounts into the existing seat mounting rails along the left and right
cabin floor. The table may be positioned anywhere along these rails, from the forward cabin
divider to the aft instrumentation rack (Figure 18). This allows for positioning of the table next to
any of the existing man cabin windows. Details of the aft cabin window curvature are provided
in Figure 19.
31
Figure 18. THORLABS breadboard table
32
Figure 19. Cabin and table position dimensions
33
Y (in)
X (in)
0
0
1
0
2
0
3
0
4
0.03125
5
0.0625
6
0.109375
7
0.15625
8
0.25
9
0.34375
10
0.46875
11
0.625
12
0.84375
13
1.0625
14
1.3125
15
1.65625
16
2
16.90625
2.34375
Figure 20. Main cabin, aft window curvature
34
6.3
Radome
The nose radome compartment (Figure 20) provides 14 cubic feet (0.396 cubic meters) of space
that is accessible through a large baggage door. The rectangular door measures 25 inches (0.635
m) by 28 inches (0.7112 m) and is located on the left side of the fuselage nose section. The
compartment has a maximum weight capacity of 150 lbs (68.04 kg).
Figure 21. Nose radome compartment
35
6.4
Engine Nacelle Locker Boxes
The Navajo is equipped with wing locker boxes in each engine nacelle (Figure 21). Each locker
box has a volume of 6 cubic feet (0.17 cubic meters). The volume is accessible via a 30 inch
(0.762 m) long by 21 inch (0.5334 m) wide access door on top of the locker box. The maximum
weight capacity of each locker box is 150 lbs (68.04 kg).
Figure 22. Engine nacelle locker box (view looking forward)
36
6.5
Rear Baggage Compartment
The rear baggage compartment is located aft of the standard 19-inch equipment rack (Figure 22).
The compartment has a length of 29 inches (0.737 m) and a volume of 22 cubic feet (0.623 cubic
meters). The compartment is accessible through the aft cabin door. The maximum weight
capacity of the area is 200 lbs (90.7 kg).
Figure 23. Rear baggage compartment
37
CHAPTER 7 EXPERIMENT DESIGN AND INTEGRATION
7.1
Construction Guidelines
The following sections provide some of the general guidelines and information for experiment
design and integration. In general, aviation industry standards and accepted practices should be
applied in experiment design and integration. The UTSI Aviation Systems and Flight Research
Program will work closely with each experimenter to ensure flight worthy design and efficient
integration of experiments.
7.1.1
Electrical Wiring
Electrical wiring should conform to aviation industry standards and accepted practices, as
found in FAA AC 43.13-1B, Chapter 11.
7.1.2 Assembly
Assembly should conform to aviation industry standards and accepted practices, as found
in FAA AC 43.13-1B and AC 43.13-2B. If assembly or disassembly will be required by
UTSI personnel, specific, written instructions and procedures should be provided. All
experiment equipment must be properly secured in the aircraft. UTSI may require final
inspection of experiment hardware.
7.1.3
Load Factor
Experiment hardware should conform to the load factors limits defined in FAA AC
43.13-2B, Chapter 1.
7.1.4
Hazardous Materials
A list of any hazardous materials to be carried onboard the aircraft must be provided to
UTSI. Material Safety Data Sheets (MSDS) should be provided as appropriate. Hazard
risks and mitigations should be identified as appropriate. The carriage of corrosive,
flammable, and toxic materials onboard the aircraft is discouraged.
38
CHAPTER 8 FLIGHT CLEARANCE PROCESS
All flight research experiments flown on UTSI aircraft are reviewed and cleared for flight using
the UTSI Aviation Systems Safety and Airworthiness Review process. Upon satisfactory
completion of this process, a Flight Permit will be issued for the flight activity.
Appendix III, “Flight Operations Safety Manual” provides information and requirements
concerning the Safety and Airworthiness process.
8.1
Flight Safety Process
Experimenters are expected to provide preliminary Hazard Reports for their experiment. These
Hazard Reports will be reviewed and revised as appropriate during the flight clearance process
with input from UTSI and the experimenter.
All areas of potential risk and/or hazard should be identified. These areas include failure modes
of equipment, hazards associated with these failures, and mitigations used to reduce the risks
and/or hazards. In general, it is preferable to accomplish risk and/or hazard mitigation through
experiment design rather than through procedures.
39
CHAPTER 9 FLIGHT OPERATIONS
(To be provided.)
40
APPENDIX I CONTACT INFORMATION
Point of Contact
Dr. Stephen Corda
Program Chairman, Aviation Systems
(931) 393-7413
scorda@utsi.edu
Mailing Address:
Aviation Systems and Flight Research
411 B.H. Goethert Parkway, MS 20
Tullahoma, TN 37388-9700
FAX
(931) 393-7533 or 7409
41
APPENDIX II INSTRUMENTATION LIST
UNITS
1=Navajo
2=Saratoga
3=Extra
4 =Navion
SAMPLE
RATE
PARAMETER ID
SENSOR
aircraft id
time
elapsed time
maneuver counter
sequential id
dynamic pressure
indicated airspeed
static pressure
altitude
vertical velocity
roll
pitch
heading
roll rate
pitch rate
yaw rate
normal acceleration
lateral acceleration
longitudinal
acceleration
GPS altitude
GPS latitude
GPS longitude
GPS track
GPS groundspeed
GPS distance to
waypoint
GPS crosstrack error
GPS desired track
GPS dest
GPS brg dest
GPS mag var
GPS nav flag
computer
computer
computer
computer
maneuver #
PPT
computer
PB
computer
computer
AHRS
AHRS
AHRS
AHRS
AHRS
AHRS
AHRS
AHRS
in H2O
knots
in Hg
ft
fpm
deg
deg
deg
deg/sec
deg/sec
deg/sec
g's
g's
10
10
10
10
10
2
2
2
2
2
10
10
10
10
10
10
10
10
AHRS
GPS
GPS
GPS
GPS
GPS
g's
ft
deg N = +
deg E = +
deg
knots
10
1
1
1
1
1
GPS
GPS
GPS
GPS
GPS
GPS
GPS
nm
1
1
1
1
1
1
1
deg
RANGE
Min
Max
0
4
0
0
0
0
0
0
0
0
-100
-100
-100
-3
-3
4000
250
35.83
20000
20000
360
360
360
100
100
100
3
3
-3
3
0
360
42
PARAMETER ID
GPS warning
GPS dist waypoint
elevator position
rudder position
r aileron position
l aileron position
aileron force
elevator force
rudder pedal force
aileron yoke position
elevator yoke position
rudder pedal position
angle of attack
angle of sideslip
cal channels 5, 18-31
OAT
left engine inlet temp
right engine inlet temp
PXI fan outlet temp
left engine rpm
right engine rpm
l eng manifold pressure
r eng manifold pressure
yaw rate - analog
pitch rate - analog
roll rate - analog
roll attitude - analog
pitch attitude - analog
lateral accel - analog
normal accel - analog
PXI data enabled
dynamic pressure enabled
static pressure enabled
GPS enabled
AHRS enabled
thermocouple enabled
rpm counters enabled
SENSOR
GPS
GPS
das analog
das analog
das analog
n/a
das analog
das analog
das analog
n/a
n/a
n/a
das analog
das analog
das analog
thermocouple
thermocouple
thermocouple
thermocouple
das digital
das digital
das analog
das analog
das analog
das analog
das analog
das analog
das analog
das analog
das analog
computer
computer
computer
computer
computer
computer
computer
UNITS
deg += TEU
deg += TER
deg += TEU
deg += TEU
lbs
lbs
lbs
deg
deg
deg
deg
deg
volts
deg C
deg C
deg C
deg C
rpm
rpm
in Hg
in Hg
deg
deg
deg/sec
deg/sec
deg/sec
g's
g's
SAMPLE
RATE
1
1
10
10
10
10
10
10
10
10
10
10
10
10
10
2
2
2
2
2
2
10
10
not used
not used
not used
not used
not used
not used
not used
10
10
10
10
10
10
10
RANGE
Min
Max
-30
-40
-30
30
40
20
-80
-60
-250
80
60
250
0
-10
-10
-30
-30
-30
-30
0
0
10
10
30
10
10
100
100
100
100
3000
3000
51
51
0
0
0
0
0
0
0
1
1
1
1
1
1
1
43
APPENDIX III FLIGHT OPERATIONS SAFETY MANUAL
(Separate Attachment)
44
APPENDIX IV EQUIPMENT SPECIFICATIONS
Brief technical specifications of core instrumentation are supplied in this appendix. Links to
manuals are also supplied in absence of a manufacturer provided technical data sheets.
Specifications are listed alphabetically by manufacturer.
Table of Contents
Axis Communications – Network Camera ............................................................... 46
Buck Research – Hygrometer ................................................................................... 48
Cisco Systems – Linksys Network Switch ............................................................... 49
EXCLTECH
XP 600 Inverter .................................................................................................... 50
XP 1100 Inverter .................................................................................................. 50
Heitronics – Pyrometer ............................................................................................. 53
Honeywell
Precision Barometer ............................................................................................. 54
Precision Pressure Transducer ............................................................................. 56
Kipp and Zonen
PAR Quantum Sensor .......................................................................................... 58
SP Lite Pyranometer ............................................................................................ 60
Moog Crossbow – GPS/IMU .................................................................................... 62
National Instruments
PXI Chassis .......................................................................................................... 64
PXI GPS Timing and Synchronization ................................................................ 64
Signal Conditioning Board .................................................................................. 64
Thermocouple Amplifier ..................................................................................... 64
Omega – Infrared Thermometer ............................................................................... 65
Riegl – Laser Altimeter............................................................................................. 69
45
46
47
48
Cisco Systems Linksys Network Switch
For specifications see:
http://www.cisco.com/en/US/docs/switches/lan/csbms/srw2008/administration/guide/SRW2008_
V10_UG_B-WEB.pdf
49
50
51
52
Heitronics Pyrometer
53
54
55
56
57
58
59
60
61
62
63
National Instruments
For specifications see:
PXI Chassis PXI-1042
http://sine.ni.com/ds/app/doc/p/id/ds-256/lang/en
PXI GPS Timing and Synchronization PXI-6682
http://www.ni.com/pdf/manuals/372292b.pdf
Signal Conditioning Box SCB-68
http://www.ni.com/pdf/manuals/372551a.pdf
Thermocouple Amplifier TC-2190
http://www.ni.com/pdf/manuals/321674c.pdf
64
65
66
67
68
69
70
71
72
73
74