The airframe-propulsion system integration of hypersonic vehicles is discussed considering the influences and problems of each of the contributing factors: inlet integration, combustion integration, nozzle integration, thermal management, and control system integration. It is noted that very high levels of efficiency in inlet, combustor and nozzle performance are required to assure net positive propulsive force in the integrated system. The higher the flight Mach number, the more difficult this integration task becomes. The inlet and nozzle integration requirements are evaluated for performance, stability and control influence on the flight vehicle. Combustor performance, fuel flow requirements and cooling loads are coupled by flight vehicle thermal management constraints. Low volumetric efficiency of the high energy density cryogenic fuels impacts the vehicle configuration due to the large fuel tank size. Thus the highly integrated hypersonic flight vehicle configuration is dominated by the propulsion system.
Propulsion Integration
1993
11 pages
Report
No indication
English
Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Combustion chambers , Control systems design , Engine airframe integration , Hypersonic vehicles , Inlet airframe configurations , Nozzle design , Propulsion system configurations , Propulsive efficiency , Temperature control , Air breathing engines , Combustion control , Cooling systems , Fuel flow , Hypersonic inlets , Spacecraft propulsion , Systems integration
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