This report presents application data for an advanced aerospike rocket engine utilizing LO2/LH2 propellants. The engine concept was applied to six different stage configurations defined by the Air Force to represent the diversity of potential applications; six vehicles were defined at 250K vacuum thrust level and six defined at a 350K level. A common engine module is defined for the six vehicle cases at each thrust level. (Author)
Applications Study for a High-Performance Cryogenic Aerospike Rocket Engine
1967
409 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Rocket Propellants , Liquid propellant rocket engines , Cryogenic propellants , Liquid rocket propellants , Liquid rocket oxidizers , Liquid rocket fuels , Liquefied gases , Hydrogen , Oxygen , Spikes , Thrust , Installation , Weight , Air , Design , Configuration , Feasibility studies , Aerodynamic spikes