1n thruster
TRANSCRIPT
1 N MoNo-ProPellaNt thrusterReliable contRol of small and midsize spacecRaft
1 N
all the space you need
1 n mono-propellant thruster
Heritage
Astrium is engaged in the mono-propellant hydra-zine propusion technology since 1966. It can look back on longlasting experience in development and production of hydrazine thrusters and propulsion systems for numerous commercial, scientific and military spacecraft and for attitude control of Europes large launcher Ariane 5.
The family of monopropellant hydrazine thrusters ranges from 0,5 N to 400 N, most of them available with either straight or canted expansion nozzle.
The 1 N thruster is a small rocket engine for attitude-, trajectory- and orbit-control of small satellites and deep space probes.
The thruster was derived from a space proven 0,5 N thruster, of which some 165 units were flown on OTS-2, ECS, Marecs, Telecom-1, Skynet 4 and NATO-IV.
The thruster has experienced multiple improve-ments since the above mentioned applications, especially in view of minimum possible production cost. Today it may be called a low cost thruster.
The thrusters are equipped with propellant valves from either Astrium or foreign supplier depending on customer´s request. The thruster is an All European Product when euipped with the Astrium valve.
1 n mono-propellant thruster
1 N Thruster in Space
More than 500 units of the thruster´s first and second generation operate successfully in space to date, and further will follow. (* Spacecraft will be launched in the near future)
Spacecraft Launch
GLOBALSTAR 1998
Jason-1 (Proteus) 2001
Rocsat 2004
Calipso (Proteus) 2006
Corot (Proteus) 2006
CosmoSkymed-1 2007
CosmoSkymed-2 2007
Radarsat 2007
Terra-SAR 2007
CosmoSkymed-3 2008
GSTB-B 2008
Jason-2 (Proteus) 2008
Theos 2008
Herschel/Planck 2009
Spirale 1 (Myriade) 2009
Spacecraft Launch
Spirale 2 (Myriade) 2009
SMOS (Proteus) 2009
TANDEM-X 2010
Alsat 2A (Myriade) 2010
CosmoSkymed-4 2010
CosmoSkymed-4 2010
Elisa-1 (Myriade) 2011
Elisa-2 (Myriade) 2011
Elisa-3 Myriade) 2011
Elisa-4 (Myriade) 2011
Pleiades HR1 2011
SSOT (Myriade) 2011
Jason-3 2013
Alsat 2B (Myriade) *AstroTerra 1 *
Spacecraft Launch
AstroTerra 2 *CSO-1 *CSO-2 *CSO-3 *KRS *Pleiades HR2 *Sentinel-2 A *Sentinel-2 B *Sentinel-5P *SEOSAR *SEOSAT *Taranis (Myriade) *Vietnam-1 (Myriade) *Vietnam-1 (Myriade) *
1 n mono-propellant thruster
Design Description
The thruster valves are dual seat / dual coil solenoid types. The solenoids are mechanically and electri-cally decoupled from each other.
The thruster performance is identical for all valves.
The 1 N thruster uses the storable pro-pellant hydrazine N2O4. The propellant is decomposed when passing the catalyst.
It is designed for both, long term steady state and pulse mode operation. It operates in a wide pressure range and is thus an ideal thruster for blow down propulsion systems.
Combustion chamber and nozzle are made of Haynes 25. The thruster structure is designed also to serve as a heat barrier for protecting valve and S/C structure against improper high temperatures. The thruster is equipped with an internally redundant catalyst bed heater and with thermal insulation to guarantee for optimum start up. In addition, the thruster is qualified for multiple cold starts.
1 n
Thruster Model CHT-1N
1 n mono-propellant thruster
Characteristics
characteriSticS VaLueS
Thrust Nominal 1 N
Thrust Range 0.320 ... 1.1 N
Specific Impulse, Nominal 220 s
Pulse, Range 200 ... 223 s
Mass Flow, Nominal 0.44 g/s
Mass Flow, Range 0.142 ... 0.447 g/s
Inlet Pressure Range 5.5 ... 22 bar
Minimum Impulse Bit 0.01 ... 0.043 N
Nozzle Expansion Ratio (by area) 80
Mass, Thruster with valve 290 g
propeLLant Hydrazine (N2H4), High-Purity Grade
SuppLiedcomponentS
Catalyst Foreign Supplier
Catalyst Bed Heater Cartridge Heater with redundant heating elements, Power 6.4 W
Foreign Supplier
Valve, 16 V DC Dual Seat Dual Solenoid Valve, Power 6.5 W, foreign supplier
Valve, 28 V DC Dual Seat Dual Solenoid Valve, Power 9.5 W, foreign supplier
Valve, 28 V DC Dual Seat Dual Solenoid Valve, Power 9.5 W, Astrium
QuaLification
Total Impulse 112,000 kNs
Cycle Life 59,000 cycles
Propellant Throughput 52 kg
Single Burn Life 12 h
Accumulated Burn Life 50
No of Cold Starts bellow 100 C 10
Shock Loads, all axes 500 g for 0.5 ms
1 n mono-propellant thruster
Launch Vibration Loads
The thruster is qualified to withstand sinus and random vibration at the shown levels. These loads represent both, launcher loads and amplification by the spacecraft. The loads are applied at the thruster mounting flange.
1 n mono-propellant thruster
Structure interface
thruSterdimenSionS
Structurecutout
puLSemodeperformancedutycycLeQuaLification
The thruster qualification program includes extensive pulse mode testing at numerous combinations of valve ON- and valve OFF-times, ranging from milliseconds to seconds, at various propellant inlet pressures.
puLSemodeperformanceSpecificimpuLSe
Thruster efficiency for pulse mode firing is naturally lower than that of steady state operation, espe-cially the shorter the pulses. However, this thruster achieves already 80% to 90% of its steady state efficiency at 300 ms pulses.
puLSemodeperformanceimpuLSeBit
In analogy to the steady state thrust, the impulse bits are a nearly linear function of the feed pressure. Even at minimum feed pressure and pulse duration the I-Bit deviation from thruster to thruster is only ± 12 %.
1 n mono-propellant thruster
Puls Operation
SteadyStateperformancethruSt
The thruster can be operated in blow down mode over the entire inlet pressure range ( ratio of 4:1). The decomposition behaviour is insensitive to pressure variations, the thrust is a nearly linear function of the feed pressure.
SteadyStateperformanceSpecificimpuLSe
The Specific Impulse is a measure for the thruster efficiency. The higher the Isp, the better the thruster. The efficiency of this thruster is worlwide competitive.
SteadyStateperformance400thruSterS
Acceptance hot firing data of 400 thrusters demonstrate the performance reproducibility and thus the constantly high quality of the thruster production.
1 n mono-propellant thruster
Steady State Operation
astriuMProPulsioN & equiPMeNtD 81663 Munich, GermanyPhone: +49 (0) 89 607 32480 · Fax: +49 (0) 89 607 [email protected] · www.astrium.eads.net
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