超燃冲压发动机二维进气道优化设计方法研究

推进技术 ›› 2001, Vol. 22 ›› Issue (6): 468-472.

超燃冲压发动机二维进气道优化设计方法研究

徐旭,蔡国飙

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15

Design and optimization method for two dimensional scramjet inlet

School of Astronautics,Beijing Univ.of Aeronautics and Astronautics, Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics, Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 建立了超燃冲压发动机二维进气道的优化设计模型 ,运用优化设计方法对三楔角外压和二楔角内压的混压式进气道进行了不同约束条件下的一维优化设计。运用数值方法对进气道的优化设计进行了二维验算 ,验证了优化设计模型及设计方法的正确性。在此基础上将数值计算方法应用于进气道的二维优化设计 ,进一步提高了进气道的性能。该方法可进一步推广应用于包含三维、真实气体流动的进气道优化设计当中。

关键词: 超燃冲压发动机;高超声速进气道;混合压缩式进气道;最优化设计;数值计算

Abstract: An optimization model was established for three wedge external compression and two wedge internal compression scramjet inlet. Optimum designs subject to different constraints were obtained using the method of successive quadratic programming. The computational fluid dynamics method was employed in two dimensional inlet optimum design using the one dimensional solution as an initial condition. The solution of two dimensional optimum design shows more performance improvements over the one dimensional design. This method can be improved to take the 3 D and real gas effects into account with only a modification of the CFD model.

Key words: Supersonic combustion ramjet engine;Hypersonic inlet;Mixed compression inlet;Optimum design;Numerical calcualtion

徐旭,蔡国飙. 超燃冲压发动机二维进气道优化设计方法研究[J]. 推进技术, 2001, 22(6): 468-472.