Bipropellant Thrusters

4 N Model S4

10 N Model S10 - 01
10 N Model S10 - 02
10 N Details

22 N Model S22 - 2

200 N Model ATV

400 N Model S400-10
400 N Model S400-12
400 N Details

500 N Model EAM
500 N Details

400 N Bipropellant Apogee Engine

For apogee orbit injection of geostationary satellites and for trajectory and planetary orbit manoeuvres of deep space probes.

400 N Bipropellant Apogee Engines Models S400-12 and 15

For almost 35 years, Astrium's 400 N Bipropellant Apogee Engines have controlled over 70 international, scientific and commercial spacecraft. During that time, multiple refinements have been implemented to extend performance and reliability whilst maintaining low production costs. Further engines have been allocated for missions up to the year 2012.

Two models of 400 N Apogee Engine are available off-the-shelf with almost identical performance. The main criterion for selecting a particular model is the available volume in the spacecraft for accommodating the engine.

The difference between the two models is the size of the expansion nozzle. Model S400-15 is equipped with a larger nozzle and therefore operates at 1% higher efficiency than the smaller model S400-12.

Both models are available with propellant valves from either MOOG, USA, or from Astrium Space Transportation, France and Germany, depending on customer's requirements. When fitted with the Astrium valve, the engine becomes an all European product.

Trimming orifices upstream of the propellant valves provide for individual adjustment of the propellant flow, according to the system design pressure. The application of heaters and thermistors for thermal control is available if required.

 

400 N Bipropellant Apogee Engine - Model No S400

Characteristics Model S400-12 Model S400-15 Thrust, Nominal 420 N 425 N Thrust Range 340 - 440 N 340 - 440 N Specific Impulse at Nominal Point 318 s 321 s Flow Rate, Nominal 135 g/s   Flow Rate, Range 110 - 142 g/s   Mixture Ratio, Nominal 1.65   Mixture Ratio, Range 1.50 - 1.80   Chamber Pressure, Nominal 10 bar   Inlet Pressure Range 12.5 - 18.5 bar   Throat Diameter (inner) 16.4 mm   Nozzle End Diameter (inner) 244 mm 292 mm Nozzle Expansion Ratio (by area) 220 330 Mass Engine with Valve 3.60 kg 4.30 kg Qualified Single Burn Life 1.1 hours 1.85 hours Qualified Accumulated Burn Life 8.3 hours 8.5 hours planned Qualified Cycle Life 100 cycles 135 cycles planned Chamber/Throat Material Platinum Alloy Injector Type Double Cone Vortex Cooling Control Film and Radiative Propellants: - Fuel - Oxidiser MMH N2O4, MON-1, MON-3 Valve Solenoid single seat, double coil voltage 21 to 27 v. Power: 35 W per coil bi-stable, MOOG 53-216 Valve Supplier 1) MOOG, East Aurora, USA, or 2) Astrium Space Transportation. Mounting Interface to Spacecraft Valve flange with 4 feedthrough holes of 6.6 mm diameter Tubing Interface per MS 33656-4 Valve Lead Wires 24 AWG per MIL-W-81381 Thruster Heater and Thermal Sensor On request

Engine Module If required, an engine support structure and thermal heat shield is available for accommodating the engine.

Technical Brochure
		A 400 N bipropellant engine brochure is available where you will find more detailed information, including: Heritage Thermal capabilities. Performance reliability. Technical Characteristics. Engine operating range diagram. Duty cycle qualification diagrams. Steady state performance diagram. Structural interfaces and dimensioning. Random and sinusoidal vibration load diagrams.

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