S400 (rocket engine)

S400
Country of origin Germany
First flight 1974-12-19
Designer Airbus
Application apogee engines
Status Operational
Liquid-fuel engine
Propellant MON / MMH
Mixture ratio 1.50 to 1.80
Cycle Pressure-fed engine
Configuration
Chamber 1
Performance
Thrust (vac.) 425 newtons (96 lbf)
Chamber pressure 1 megapascal (150 psi)
Isp (vac.) 321 seconds (3.15 km/s)
Burn time 8.5 hours
Dimensions
Length 669 millimetres (26.3 in)
Diameter 316 millimetres (12.4 in)
Dry weight 4.30 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 Airbus. They burn MMH and MON as propellant, have a thrust range between 340420 newtons (94 lbf) and 450420 newtons (94 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 have been used as primary apogee engines for telecommunications satellites such as the Thales Alenia Space Spacebus as well as deep space missions such as Venus Express.[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][3]

References

  1. 1 2 3 "400 N Bipropellant Apogee Motors". Airbus Defense & Space. Retrieved 2015-06-15.
  2. ↑ "Model No S400 - 15 Elevation Dimensions" (gif). Airbus Defense & Space. 2013. pp. 8–9. Retrieved 2015-06-15.
  3. ↑ "CHEMICAL BI-PROPELLANT THRUSTER FAMILY" (pdf). Airbus Defense & Space. 2013. pp. 8–9. Retrieved 2015-06-15.


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