S400 (rocket engine)

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S400
Country of originGermany
First flight1974-12-19
DesignerArianeGroup
Applicationapogee engines
StatusOperational
Liquid-fuel engine
PropellantMON / MMH
Mixture ratio1.50 to 1.80
CyclePressure-fed engine
Configuration
Chamber1
Performance
Thrust (vac.)425 newtons (96 lbf)
Chamber pressure1 megapascal (150 psi)
Isp (vac.)321 seconds (3.15 km/s)
Burn time8.5 hours
Dimensions
Length669 millimetres (26.3 in)
Diameter316 millimetres (12.4 in)
Dry weight4.30 kilograms (9.5 lb)
Used in
Communications Satellite
References
References[1][2]

The S400 is a family of pressure fed liquid propelled rocket engines manufactured by ArianeGroup (former Airbus DS) at the Orbital Propulsion Centre [3] in Lampoldshausen, Germany.

They burn MMH and MON as propellant, have a thrust range between 340 newtons (76 lbf) and 450 newtons (100 lbf) and can vary the O/F ratio between 1.50 and 1.80. The chamber and throat are made of a platinum alloy, it uses double cone vortex injectors and uses both film and radiative cooling. The S400 engines are used as primary apogee engines for telecommunication satellite platforms such as the Spacebus of Thales Alenia Space as well as space exploration missions such as Venus Express, ExoMars Trace Gas Orbiter or Jupiter Icy Moons Explorer.[1]

The family has had an extensive history on the commercial telecommunication market. Its first launch was aboard the Symphonie 1 in 1974. This was the first commercial three-axis stabilized communications satellite in geostationary orbit with a bipropellant rocket propulsion system. It also was the first European communications satellite system. This family of engines have displayed a remarkable competitiveness, still winning many designs (for 2015, it is expected to fly on Sicral 2, ARSAT-2, Hispasat AG1 and MSG-4.[1][4]

References[edit]

  1. ^ a b c "400 N Bipropellant Apogee Motors". ArianeGroup. Retrieved 2017-08-03.
  2. ^ "Model No S400 - 15 Elevation Dimensions" (gif). Airbus Defense & Space. 2013. pp. 8–9. Retrieved 2015-06-15.
  3. ^ "Orbital Propulsion Centre, Lampoldshausen, Germany".
  4. ^ "CHEMICAL BI-PROPELLANT THRUSTER FAMILY" (pdf). Airbus Defense & Space. 2013. pp. 8–9. Retrieved 2015-06-15.