The initial baseline concept of the storable bipropellant propulsion system of the Hermes spaceplane is discussed. The general architecture of the propulsion system is shown. The design features of the engines of the main propulsion system and of the thrusters of the auxiliary propulsion system are demonstrated. Operational requirements as safety, reliability, life, and maintainability are discussed. The initial baseline flow scheme of the Hermes propulsion system is described. The main propulsion system consists of 2 reusable pressure fed rocket engines with a nominal steady state thrust of 20 kN per engine in vacuum. An auxiliary system provides thrust for attitude maneuvers and small velocity changes along the vehicle axis. It consists of 28 thrusters (10 to 400 N) distributed forward and aft.
Hermes Propulsion System
1987
17 pages
Report
Keine Angabe
Englisch
Hermes propulsion system design
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