docData sheet 10N bi-propellant thruster
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Data sheet 10N bi-propellant thruster
10 N Bi-Propellant Thruster Reliable control of large spacecraft All the space you need Heritage The 10 N thruster is a small rocket engine for attitude, The thrusters are equipped with propellant valves 10 N Thrusters in Space trajectory and orbit control of large satellites and from either MOOG, USA, or from EADS Space More than 90 spacecraft are equipped with deep space probes. Transportation, France and Germany, depending on EADS-ST’s 10 N thrusters. Most of them with either customer's request. The thruster is an All European 12 or 14 units. It can look back on more than 35 years use in space. Product when equipped with the EADS Space Over thousend units have controlled numerous inter- Transportation valve. Satellite Launch Satellite Launch Satellite Launch national scientific and commercial spacecraft to date. Symphonie 1 Symphonie 2 1974 1975 Arabsat 2B Hot Bird 2 1996 1996 Hispasat 1D Eutelsat W5 2002 2002 The thruster has experienced multiple improvements TV-Sat 1 TDF-1 Galileo 1987 1988 1989 Nahuel 1A Thaicom 3 Hot Bird 3 1997 1997 1997 Mars Express AMC 9 Amos 2 2003 2003 2003 Tele X DFS Kopernikus 1 TV-Sat 2 DFS Kopernikus 2 1989 1989 1989 1990 Sirius 2 FM1 Hot Bird 4 Nilesat 101 Sinosat 1997 1998 1998 1998 Rosetta Eutelsat W3A Intelsat 10-02 Amazonas 1 2004 2004 2004 2004 TDF-2 Eutelsat 2-F1 1990 1990 Sing Tel 1 Eutelsat W2 1998 1998 Worldsat 2 Apstar 6 2005 2005 Inmarsat IIF Telecom 2 A Eutelsat 2-F2 Eutelsat 2-F3 1990 1990 1991 1991 Hot Bird 5 Afristar GE 5 Arabsat 3A 1998 1998 1998 1999 Inmarsat 4-F1 Inmarsat 4-F2 Meteosat SG 2 Rascom 1 2005 2005 2005 2005 Arabsat 1C Telecom 2B 1992 1992 Eutelsat W3 Hispasat 1C 1999 2000 Sicral B Syracuse 3A 2005 2005 Eutelsat 2-F4 Hispasat 1A DFS Kopernikus 3 Hispasat 1B Eutelsat 2-F5 1992 1992 1992 1993 1994 Asiastar Eutelsat W4 Cluster FM 6, FM 7 Cluster FM 5, FM 8 Nilesat 102 2000 2000 2000 2000 2000 Venus Express Worldsat 3 Galaxy 17 Inmarsat 4-F3 Star One C1 2005 2005 2006 2006 2006 Türksat 1A Türksat 1AR 1994 1994 Astra 2B Eurasiasat 2000 2001 Syracuse 3B Chinasat 9 2006 2007 Türksat 1B Telstar 11 HotBird 1 Telecom 2 C 1994 1994 1995 1995 Sicral Eurobird Artemis Atlantic Bird 2 2001 2001 2001 2001 Hot Bird 7A Koreasat 5 Star One C2 Syracuse 3C 2007 2007 2007 2007 Amos 1 Arabsat 2A 1996 1996 Atlantic Bird 3 Atlantic Bird 1 2002 2002 MSG 3 MSG 4 2009 2012 Türksat 1C Telecom 2 D 1996 1996 HotBird 6 Meteosat SG 1 2002 2002 in the course of its 35 years life and the innovation for further performance improvement and simultaneous cost reduction still continues. Design Description The 10 N bi-propellant thruster uses the storable Three types of propellant flow control valves may be propellants N2O4, MON-1 or MON-3 as oxidizer, applied: and MMH as fuel. It is designed for both, long term steady state and pulse mode operation. It operates in a wide pressure range at regulated pressure as well as in system blow down mode. • Thruster S10-13 with single seat, mono-stable, torque motor valve (supplier MOOG, USA) • Thruster S10-18 with dual seat valve, consisting of an upstream latch valve and a downstream Combustion chamber and nozzle are made of a Platinum alloy that requires no surface coating. mono-stable valve (supplier MOOG, USA) • Thruster S10-23 with dual seat valve, consisting of an upstream latch valve and a downstream It allows operational temperatures up to 1,500° C mono-stable valve (supplier EADS Space (2,700° F) and thus maximum thruster performance. Transportation, Germany) The uncoated surface is absolutely resistant against The thruster performance is identical for all valves. oxidization and thus invulnerable to mishandling, to application of test sensors, to millions of pulse cycles. Trimming orifices between valve and injector provide for individual adjustment of the propellant flow, according to the designed system pressure. The application of heaters and thermistors for thermal control is provided on request. Thruster Model S 10-13 Valve, Single Seat, MOOG Thruster Model S 10-18 Valve, Dual Seat, MOOG Thruster Model S 10-23 Valve, Dual Seat, EADS Space Transportation Characteristics Launch Vibration Loads Random and Sinusodial Vibration The thrusters are qualified to withstand sinus and These loads represent both, launcher loads and random vibration at the shown levels. amplification by the spacecraft. The loads are applied at the thruster mounting flange. Characteristics Metric Dimensions Imperial / US Dimensions Thrust, Nominal 10 N 2.2 lb Thrust Range Specific Impulse at Nominal Point 6.0 … 12.5 N 291 s 1.4 … 2.8 lb Flow Rate, Nominal Flow Rate, Range Mixture Ratio, Nominal Mixture Ratio, Range Chamber Pressure, Nominal 3.50 g/s 2.30 … 4.20 g/s 1.65 1.20 … 2.10 9 bar 130 psi Inlet Pressure Range Throat Diameter (inner) 10 … 23 bar 2.85 mm 145 … 335 psi 0.11 inch Nozzle End Diameter (inner) Nozzle Expansion Ratio (by area) Mass, Thruster with single Seat Valve 35 mm 150 350 g 1.38 inch Mass, Thruster with dual Seat Valve Chamber-Nozzle Material Injector Type 650 g Platinum/Rhodium Double Cone Vortex Cooling Concept Propellants, Fuel Oxidizer Film & Radiative MMH N2O4, MON-1, MON-3 0,8 lb 1,5 lb Valve, Single Seat Bi-propellant torque motor valve, mono-stable, 50 Volts, MOOG 51-131 Valve, Dual Seat Mounting I/F to S/C a) Two in one bi-propellant torque motor valves, 50 Volts, MOOG 51-215 b) Two in one bi-propellant dual coil actuator valves, 40 to 50 Volts, EADS Space Transportation MOOG, East Aurora, USA (Valve for thrusters S10-13 and S10-18) EADS Space Transportation, Germany (Valve for thruster S10-23) Valve flange with 3 through-holes of 6.4 mm (1/4’’) diameter Tubing I/F per SAE AS4395E02 or welded Valve Lead Wires Thruster heater and Thermal Sensor Qualified single burn life Qualified accumulated burn life Qualified cycle life 24 AWG per MIL-W-81381 On request 15 hours 70 hours 1,000,000 cycles Valve Supplier Random – Sinusodial Random – Axial Random – Lateral Steady State Operation Pulse Operation Steady State Performance 600 Thrusters Thruster Operation Range Duty Cycle Qualification Pulse Mode Performance, Impulse Bit The average specific impulse of 600 tested thrusters The thruster operates reliably within a propellant The thruster qualification program includes extensi- The single impulse bits are nearly independent on is 291 sec. The maximum deviation of individual pressure range from 10 to 22 bar at the valve inlets. ve pulse mode testing at numerous combinations Valve Off times. This is a consequence of the thrusters to this average is 2 %. A minimum Isp of The boundaries are given by stability and of Valve On and Valve Off times, ranging from thruster’s low dribble volumes and of the totally 287 sec is contractually guaranteed. temperature limits. milliseconds to seconds. optimized thruster design. Pulse Mode Performance, Specific Impulse Pulse Mode Performance, Impulse Bit Repeatability Steady State Performance Specific Impulse The specific impulse (Isp) is the measure for the Full thruster efficiency is achieved for pulse Impulse bit repeatability is of major importance for thruster-efficiency. The higher the Isp, the better the Each thruster is individually adapted to the propell- durations over 500 milliseconds. The efficiency is an efficient use of the thruster. Even under worst thruster. Generally, the Isp of a thruster depends on lant feed system of its spacecraft. The actual thruster naturally lower as shorter the pulse, since start up case conditions, namely minimum Valve On and various operational parameters, it is never constant operation point during a mission may shift within the and shut off time of the combustion are approaching maximum Valve Off times, the thruster shows for the entire operation range. The nominal Isp of qualified range, depending on the actually occurring the total pulse duration. excellent performance repeatability. 291 sec refers to the nominal thrust level of 10 N. tank pressures. The thruster may be operated at The thruster achieves an Isp up to 298 sec when both, regulated and blow down pressure mode. operated at maximum thrust. Structure Interface Thruster S 10-13 MOOG Valve, SingleSeat Dimensions Structure Cut out Structure Interface Thruster S 10-13 Thruster S 10-18 Thruster S 10-23 MOOG Valve, SingleSeat MOOG Valve, Dual Seat EADS Space Transportation Valve, DualSeat Dimensions Dimensions Dimensions Structure Cut out Structure Cut out Structure Cut out Printed in Germany. © 2005 EADS Space Transportation. Photos and Images: EADS Space Transportation, EADS Astrium, DLR, ESA. EADS Space Transportation Propulsion & Equipment D 81663 Munich, Germany Phone: +49-89-607 22148 Fax: +49-89-607 85148 Henning.vonBassewitz@space.eads.net www.space-propulsion.com www.space.eads.net
