An Aircraft-Propulsion Geometry/Performance Collaborative Design Method
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.
collaborative design modelin simulation hypersonic vehicle scramjet Taylor-MacColl Equation NURBS
Chao TIAN Guanghong GONG
Advanced Simulation Laboratory, School of Automation Science and Electronic EngineeringBeijing Unive Advanced Simulation Laboratory, School of Automation Science and Electronic Engineering Beijing Univ
国际会议
IEEE 10th International Conference on Industrial Informatics(第十届IEEE工业信息学国际学术会议 INDIN2012)
北京
英文
103-108
2012-07-25（万方平台首次上网日期，不代表论文的发表时间）