An aircraft-propulsion geometry/performance collaborative design method

摘要

High performance and economic gains are treated as the main target for future aerospace product design. An inward turning inlet equipped hypersonic vehicle parameterization procedure was devised for collaboration of wingbody and scramjet propulsion system modeling. Top design parameters (free-stream Mach number, flight altitude, mission requests, etc.) drive the overall collaborative system construction and both the scramjet engine geometry and wingbody profiles are conveniently generated using the NURBS toolbox and streamline tracing method within the programs developed in this paper. An accelerated digital real time hypersonic vehicle-propulsion integrated controlled plant was prepared for advanced controlling algorithm tests and further researches.