The range of thrust variation necessary was deduced from some mission examples. To find the optimal flight path of satellite launchers, a diagram was made. Systems for determining the injector element sprays droplet diameter distributions and evaporation efficiency are explained. Suggestions are made for improving the predictability of mixing efficiencies of elements. An injector type and its performance are discussed. Effects of thrust control on the expansion process are dealt with. Test results from a CH2/LOX-throttleable rocket engine are presented and compared with theoretical results of the process study. (Author)
Research on the Energy Conversion in Liquid Rockets in Connection with Thrust Control
1975
234 pages
Report
No indication
English
Rocket Propellants , Energy conversion , Hydrogen oxygen engines , Liquid rocket propellants , Thrust control , Bibliographies , Flight paths , Fuel injection , Nozzle geometry , Particle size distribution , Payloads , Propellant combustion , Propellant evaporation , Spacecraft launching , Translations
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