The Orbital Sciences Corporation X-34 vehicle demonstrates technologies and operations key to future reusable launch vehicles. The general flight performance goal of this unmanned rocket plane is Mach 8 flight at an altitude of 250,000 feet. The Main Propulsion System supplies liquid propellants to the main engine, which provides the primary thrust for attaining mission goals. Major NMS design and operational goals are aircraft-like ground operations, quick turnaround between missions, and low initial/operational costs. This paper reviews major design and analysis aspects of the X-34 propellant feed subsystem of the X-34 Main Propulsion System. Topics include system requirements, system design, the integration of flight and feed system performance, propellant acquisition at engine start, and propellant tank terminal drain.
Propellant Feed Subsystem for the X-34 Main Propulsion System
1998
11 pages
Report
Keine Angabe
Englisch
Space Technology , X-34 reusable launch vehicle , Reusable launch vehicles , Flight characteristics , Hypersonic speed , Liquid rocket propellants , Propulsion system configurations , Propulsion system performance , Systems engineering , Rocket planes , Design analysis , Propellant tanks , Propellants , Propulsive efficiency , Propulsion
Propellant Feed Subsystem for the X-34 Main Propulsion System
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