Being considered are the selection problems of rational thermodynamic parameters and control laws for hydrogen and hydrogen-oxyen aero-turbo-rocket (ATR) engines designed for horizontal take-off and landing Single-Stage-to-Orbit (SSTO) vehicles acceleration up to Mach 6. Three types of ATR-engines were studied: gas generator, expander, gas generator with H2 preheating. Computation allows for thermodynamic features of cryogenic-fuelled engines, operating within a wideflight speed envelope. Construction materials performance corresponded to world practice 2005-2010 years forecast. Relative payload mass was used for estimation of different type ATR-engines effectiveness for SSTO.
Rational schemes and performances of the ATR-engines
Kriterien für die Entwicklung und Leistung von ATR-Raketentriebwerken (Aero-Turbo-Rocket)
SAE-Papers ; Apr ; 1-8
1990
8 Seiten, 10 Bilder, 10 Quellen
Aufsatz (Konferenz)
Englisch
Rational Schemes and Performances of the ATR-Engines
SAE Technical Papers | 1990
|HIGH SPEED ENGINES - New engines and uprated performances
Online Contents | 2006
Next generation ion engines: mission performances
NTRS | 2003
|A Rational Basis for Comparing Diesel-Engine Performances
SAE Technical Papers | 1935
|Analysis of performances of some diesel propelling engines
Engineering Index Backfile | 1937
|