10 n bi-propellant thruster - · pdf filenilesat 101 1998 sinosat 1998 sing tel 1 1998 ... the...
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Reliable control of large spacecraft
10 N Bi-Propellant Thruster
All the space you need
10 N Thrusters in SpaceMore than 90 spacecraft are equipped with
EADS-ST’s 10 N thrusters. Most of them with either
12 or 14 units.
Symphonie 1 1974
Symphonie 2 1975
TV-Sat 1 1987
TDF-1 1988
Galileo 1989
Tele X 1989
DFS Kopernikus 1 1989
TV-Sat 2 1989
DFS Kopernikus 2 1990
TDF-2 1990
Eutelsat 2-F1 1990
Inmarsat IIF 1990
Telecom 2 A 1990
Eutelsat 2-F2 1991
Eutelsat 2-F3 1991
Arabsat 1C 1992
Telecom 2B 1992
Eutelsat 2-F4 1992
Hispasat 1A 1992
DFS Kopernikus 3 1992
Hispasat 1B 1993
Eutelsat 2-F5 1994
Türksat 1A 1994
Türksat 1AR 1994
Türksat 1B 1994
Telstar 11 1994
HotBird 1 1995
Telecom 2 C 1995
Amos 1 1996
Arabsat 2A 1996
Türksat 1C 1996
Telecom 2 D 1996
Arabsat 2B 1996
Hot Bird 2 1996
Nahuel 1A 1997
Thaicom 3 1997
Hot Bird 3 1997
Sirius 2 FM1 1997
Hot Bird 4 1998
Nilesat 101 1998
Sinosat 1998
Sing Tel 1 1998
Eutelsat W2 1998
Hot Bird 5 1998
Afristar 1998
GE 5 1998
Arabsat 3A 1999
Eutelsat W3 1999
Hispasat 1C 2000
Asiastar 2000
Eutelsat W4 2000
Cluster FM 6, FM 7 2000
Cluster FM 5, FM 8 2000
Nilesat 102 2000
Astra 2B 2000
Eurasiasat 2001
Sicral 2001
Eurobird 2001
Artemis 2001
Atlantic Bird 2 2001
Atlantic Bird 3 2002
Atlantic Bird 1 2002
HotBird 6 2002
Meteosat SG 1 2002
Hispasat 1D 2002
Eutelsat W5 2002
Mars Express 2003
AMC 9 2003
Amos 2 2003
Rosetta 2004
Eutelsat W3A 2004
Intelsat 10-02 2004
Amazonas 1 2004
Worldsat 2 2005
Apstar 6 2005
Inmarsat 4-F1 2005
Inmarsat 4-F2 2005
Meteosat SG 2 2005
Rascom 1 2005
Sicral B 2005
Syracuse 3A 2005
Venus Express 2005
Worldsat 3 2005
Galaxy 17 2006
Inmarsat 4-F3 2006
Star One C1 2006
Syracuse 3B 2006
Chinasat 9 2007
Hot Bird 7A 2007
Koreasat 5 2007
Star One C2 2007
Syracuse 3C 2007
MSG 3 2009
MSG 4 2012
Satellite Launch Satellite Launch Satellite Launch
Heritage
The thrusters are equipped with propellant valves
from either MOOG, USA, or from EADS Space
Transportation, France and Germany, depending on
customer's request. The thruster is an All European
Product when equipped with the EADS Space
Transportation valve.
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 35 years use in space.
Over thousend units have controlled numerous inter-
national scientific and commercial spacecraft to date.
The thruster has experienced multiple improvements
in the course of its 35 years life and the innovation for
further performance improvement and simultaneous
cost reduction still continues.
Design Description
Three types of propellant flow control valves may be
applied:
• 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
mono-stable valve (supplier MOOG, USA)
• Thruster S10-23 with dual seat valve, consisting of
an upstream latch valve and a downstream
mono-stable valve (supplier EADS Space
Transportation, Germany)
The thruster performance is identical for all valves.
The 10 N bi-propellant thruster uses the storable
propellants N2O4, MON-1 or MON-3 as oxidizer,
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.
Combustion chamber and nozzle are made of a
Platinum alloy that requires no surface coating.
It allows operational temperatures up to 1,500° C
(2,700° F) and thus maximum thruster performance.
The uncoated surface is absolutely resistant against
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 ther-
mal control is provided on request.
Thruster Model S 10-13Valve, Single Seat, MOOG
Thruster Model S 10-18Valve, Dual Seat, MOOG
Thruster Model S 10-23Valve, Dual Seat, EADS Space Transportation
Launch Vibration Loads
These loads represent both, launcher loads and
amplification by the spacecraft. The loads are
applied at the thruster mounting flange.
Random – Lateral
Random and Sinusodial VibrationThe thrusters are qualified to withstand sinus and
random vibration at the shown levels.
Random – Sinusodial
Random – Axial
Characteristics
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, 50 Volts, MOOG 51-131
Valve, Dual Seat 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
Valve Supplier MOOG, East Aurora, USA (Valve for thrusters S10-13 and S10-18)
EADS Space Transportation, Germany (Valve for thruster S10-23)
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
Characteristics Metric Dimensions Imperial / US Dimensions
Pulse Operation
Pulse Mode Performance, Impulse BitThe 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.
Pulse Mode Performance,Impulse Bit RepeatabilityImpulse 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.
Duty Cycle QualificationThe thruster qualification program includes extensi-
ve pulse mode testing at numerous combinations
of Valve On and Valve Off times, ranging from
milliseconds to seconds.
Pulse Mode Performance, Specific ImpulseFull 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.
Steady State Operation
Thruster Operation RangeThe thruster operates reliably within a propellant
pressure range from 10 to 22 bar at the valve inlets.
The boundaries are given by stability and
temperature limits.
Each thruster is individually adapted to the propell-
lant 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.
Steady State Performance 600 ThrustersThe average specific impulse of 600 tested thrusters
is 291 sec. The maximum deviation of individual
thrusters to this average is 2 %. A minimum Isp of
287 sec is contractually guaranteed.
Steady State Performance Specific ImpulseThe 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.
Structure Interface
Thruster S 10-13MOOG Valve, SingleSeat
Dimensions
Structure Cut out
Thruster S 10-23EADS Space Transportation Valve, DualSeat
Dimensions
Structure Cut out
Thruster S 10-18MOOG Valve, Dual Seat
Dimensions
Structure Cut out
Structure Interface
Thruster S 10-13MOOG Valve, SingleSeat
Dimensions
Structure Cut out
EADS Space TransportationPropulsion & EquipmentD 81663 Munich, GermanyPhone: +49-89-607 22148Fax: +49-89-607 [email protected]
www.space-propulsion.comwww.space.eads.netPr
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