The propulsion system for the lower stage of a two-stage-to-orbit (TSTO) transport system is presented with its major components: mixed compression air intake, two-spool-low-bypass turbo engine and single expansion ramp nozzle. Intake and nozzle have been analysed by Navier-Stokes-calculations. Based on performance analysis a real time simulation program is presented, which has been integrated into a flight simulator. At hypersonic speeds the effects of the propulsion system on flight-mechanical behaviour is substantial, especially at engine failures. In a realistic flight-mechanical analysis of hypersonic aircraft the steady state and dynamic propulsion system performance has to be considered not only with axial thrust and drag components, but also with its significant lift and resulting pitching moments and stabilising effects on the aircraft.
Propulsion/aircraft integration and dynamic performance of hypersonic TSTO-vehicles
Antrieb/Luftfahrzeug-Integration und dynamische Leistung von zweistufigen Hyperschall-Raumtransportsystemen
1995
16 Seiten, 17 Bilder, 19 Quellen
Conference paper
English
Raumfahrzeug , Umlauf , Hyperschallgeschwindigkeit , Leistung , Antriebsanlage , Luftfahrzeug , Stufenbauart , Luftverdichter , Lufteinlauf , Bypassturbine , Düse , Navier-Stokes-Gleichung , Simulationsprogramm , Echtzeitbetrieb , Flugsimulation , Flugmechanik , Axialschub , Strömungswiderstand , Auftrieb
Propulsion/Aircraft Integration and Dynamic Performance of Hypersonic TSTO Vehicles
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