Transcript
10 N Bi-ProPellaNt thrusterReliable contRol of laRge spacecRaft
10 N
all the space you need
10 n bi-propellant thruster
Heritage
The 10 N thruster is a small rocket engine for attitude-, trajectory- and orbit-control of large satellites and deep space probes.
It can look back on more than 40 years use in space. Over three thousend units have controlled numerous international scientific and commercial spacecraft to date.
The thruster has experienced multiple improve-ments in the course of its 40 years life and the innovation for product improvement still continues.
The thrusters are equipped with propellant valves from either Astrium or foreign suppliers, depending on customer‘s request. The thruster is an All European Product when equipped with the Astrium valve.
10 n bi-propellant thruster
10 N Thruster in Space
Over 130 spacecraft were eqipped with Astrium‘s 10N thrusters since 1974. The table below starts with the year 1998. For earlier satellites please contact Astrium, Propulsion & Equipment. (* Spacecraft will be launched in the near future)
Spacecraft Launch
AFRISTAR 1998
AMC-5, GE-5 1998
EUTELSAT W2 1998
HOT BIRD 4 1998
HOT BIRD 5 1998
SINGASAT 1998
SINOSAT 1998
Arabsat 3A 1999
EUTELSAT W3 1999
ORION 2 1999
ASIASTAR 2000
ASTRA 2B 2000
CLUSTER II 2000
CLUSTER II 2000
EUTELSAT W4 2000
HISPASAT 1C 2000
NILESAT 2 2000
ARTEMIS 2001
Atlantic Bird 2 2001
EURASIASAT 2001
Eurobird 2001
SICRAL 2001
ASTRA 1K 2002
Atlantic Bird 1 2002
EUTELSAT W5 2002
HOT BIRD 6 2002
HOT BIRD 7 2002
MSG FM1 2002
Stellat 2002
Hispasat 1D 2002
STENTOR 2002
AMOS 2 2003
HELLAS SAT 2 2003
MARS EXPRESS 2003
AMC-9, GE-12 2003
Amazonas 2004
EUTELSAT W3A 2004
Intelsat 10-02 2004
ROSETTA 2004
Anik F1R 2005
Inmarsat4 FM1 2005
Inmarsat4 FM2 2005
MSG FM2 2005
GEi1 2005
GEi2 2005
Spacecraft Launch
Syrakus 3A 2005
Apstar 6 2005
Venus Express 2005
EUROSTAR 2013 2006
EUROSTAR 2014 2006
Hot Bird 8 2006
HB7A, APA2 2006
Syrakus 3B FM2 2006
Koreasat 5 2006
THAICOM 5 2006
Anik F3 2007
Star One C1 2007
Galaxy 17 2007
RC1 2007
Chinasat 6B 2007
Skynet 5A 2007
Skynet 5B 2007
AMOS 3 2008
Astra 1M 2008
EUROSTAR 2015 2008
Hot Bird 9 2008
Inmarsat4 FM3 2008
Nimiq-4 2008
Star One C2 2008
Turksat 3A 2008
CIEL2 2008
Chinasat 9 2008
Skynet 5C 2008
Amazonas-2 2009
Hot Bird 10 2009
MILSAT-A 2009
W2A 2009
W7 2009
Thor-6 2009
Palapa D 2009
SICRAL 1B 2009
Arabsat 5A 2010
Arabsat 5B 2010
Astra 3B 2010
COMS 2010
KA-SAT 2010
MILSAT-B 2010
Nilesat 201 2010
RASCOM-2 2010
W3B 2010
Spacecraft Launch
Arabsat 5C 2011
Astra 1N 2011
Atlantic Bird 7 2011
Ekspress AM4 2011
W3C 2011
YAHSAT 1A 2011
Alphasat PFM *AMERISTAR *AMOS 4 *ARSAT *ARSAT 2 *Astra 2E *Astra 2F *Astra 2G *Astra 5B *BepiColombo *CESASAT *DirecTV 15 *Ekspress-AM4R *Ekspress-AM7 *EUROSTAR3007-12 *Eutelsat 3B *Eutelsat 9B *ExoMars Orbiter *GAIA *INMARSAT2 *LISA-Pathfinder *MEASAT 3B *MSG FM3 *MSG FM4 *W6A *Yamal 402 *W3D *Sicral2 *AthenaFidus *Apstar7A *Apstar7B *SES-6 *SK5D *SmallGEO *TELECOM2 *W5A *WORLDSTAR 4 *YAHSAT 1B *
10 n bi-propellant thruster
Design Description
Three types of propellant flow control valves may be applied:
thruSterS10-21 with single seat, mono-stable, torque motor valve (foreign supplier)
thruSterS10-18 with dual seat valve, consisting of an upstream latch valve and a downstream mono-stable valve (foreign supplier)
thruSterS10-26 with dual seat valve, consisting of an upstream latch valve and a downstream mono-stable valve (Astrium)
The thruster performance is identical for all valves.
The 10 N bi-propellant thruster uses the storable propellants Monomethylhydra-zine MMH as fuel and pure Di-Nitro-
gen-Tetroxide N2O4, or Mixed Oxides of Nitrogen (MON-1, MON-3) as oxidizer. It is designed for both, long term steady state and pulse mode operation. It operates in a wide pressure range at regulated pres-sure as well as in system blow down mode.
Combustion chamber and nozzle are made of a Platinum alloy that does not need any surface coating. It allows operational temperatures up to 1,500° C (2,700° F) and thus maximum thruster performance.
The un-coated surface is absolutely resistant against oxidization and and thus it is invulnerable to mishandling, to application of test sensors and 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.
10 n
Thruster Model S 10-21
Thruster Model S 10-18 Thruster Model S 10-26
10 n bi-propellant thruster
Characteristics
characteriSticS MetricDiMenSionS iMperiaL/uSDiMenSionS
Thrust, Nominal 10 N 2.2 lb
Thrust Range 6.0 … 12.5 N 1.4 … 2.8 lb
Specific Impulse at Nominal Point 291 s
Flow Rate, Nominal 3.50 g/s
Flow Rate, Range 2.30 … 4.20 g/s
Mixture Ratio, Nominal 1.65
Mixture Ratio, Range 1.20 … 2.10
Chamber Pressure, Nominal 9 bar 130 psi
Inlet Pressure Range 10 … 23 bar 145 … 335 psi
Throat Diameter (inner) 2.85 mm 0.11 inch
Nozzle End Diameter (inner) 35 mm 1.38 inch
Nozzle Expansion Ratio (by area) 150
Mass, Thruster with single Seat Valve 350 g 0,8 lb
Mass, Thruster with dual Seat Valve 650 g 1,5 lb
Chamber-Nozzle Material Platinum/Rhodium
Injector Type Double Cone Vortex
Cooling Concept Film & Radiative
Propellants, Fuel MMH
Oxidizer N2O4, MON-1, MON-3
Valve, Single Seat Bi-propellant torque motor valve, mono-stable
Valve, Dual Seat a) Two in one bi-propellant torque motor valves
b) Two in one bi-propellant dual coil actuator valves
Mounting I/F to S/C Valve flange with 3 through-holes of 6.4 mm (1/4’’) diameter
Tubing I/F per SAE AS4395E02 or welded
Valve Lead Wires 24 AWG per MIL-W-81381
Thruster heater and Thermal Sensor On request
Qualified single burn life 15 hours
Qualified accumulated burn life 70 hours
Qualified cycle life 1,000,000 cycles
ranDoManDSinuSoDiaLVibration
The thrusters are qualified to withstand sinus and random vibration at the shown levels.
10 n bi-propellant thruster
Launch Vibration Loads
These loads represent both, launcher loads and amplification by the spacecraft. The loads are ap-plied at the thruster mounting flange.
ranDoM-axiaL ranDoM-LateraL
ranDoM-SinuSoDiaL
10 n bi-propellant thruster
Steady State Operation
SteaDyStateperforMance600thruSterS
The average specific impulse of the tested thrusters is 291 sec. The maximum deviation of individual thrusters to this average is 2 %. A min. Isp of 287 sec is contractually guaranteed.
thruSteroperationrange
The thruster operates reliably within a propellant pressure range from 10 to 22 bar at the valve inlets. The boundaries are given by stability and tempera-ture limits.
Each thruster is individually adapted to the propelllant feed system of its spacecraft. The actual thruster operation point during a mission may shift within the qualified range, depending on the actually occurring tank pressures. The thruster may be operated at both, regulated and blow down pressure mode.
SteaDyStateperforManceSpecificiMpuLSe
The specific impulse (Isp) is the measure for the thruster-efficiency. The higher the Isp, the better the thruster. Generally, the Isp of a thruster depends on various operational parameters, it is never constant for the entire operation range. The nominal Isp of 291 sec refers to the nominal thrust level of 10 N. The thruster achieves an Isp up to 298 sec when operated at maximum thrust.
DutycycLeQuaLification
The thruster qualification program includes extensive pulse mode testing at numerous combinations of Valve On and Valve Off times, ranging from milliseconds to seconds.
10 n bi-propellant thruster
Pulse Operation
puLSeMoDeperforMance,iMpuLSebit
The single impulse bits are nearly independent on Valve Off times. This is a consequence of the thruster’s low dribble volumes and of the totally optimized thruster design.
puLSeMoDeperforMance,SpecificiMpuLSe
Full thruster efficiency is achieved for pulse durations over 500 milliseconds. The efficiency is naturally lower as shorter the pulse, since start up and shut off time of the combustion are approaching the total pulse duration.
puLSeMoDeperforMance,iMpuLSebitrepeatabiLity
Impulse bit repeatability is of major importance for an efficient use of the thruster. Even under worst case conditions, namely minimum Valve On and maximum Valve Off times, the thruster shows excellent performance repeatability.
10 n bi-propellant thruster
Structure Interface
thruSterS10-21
Valve, Single Seat, Torque Motor
Dimensions
Structure Cut Out
Structure Cut Out
thruSterS10-18
Valve, Dual Seat, Dual Torque Motor
Dimensions
Structure Cut Out
thruSterS10-26
Valve, Dual Seat, Dual Coil Actuator
Dimensions
astriumProPulsioN & equiPmeNtD 81663 Munich, GermanyPhone: +49 (0) 89 607 32480 · Fax: +49 (0) 89 607 85480Hartwig.Ellerbrock@astrium.eads.netwww.space-propulsion.com · www.astrium.eads.net
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