航天器环境工程2018，Vol.35Issue(3)：205-209,5.DOI:10.3969/j.issn.1673-1379.2018.03.001
可降低气动热效应的类凹腔外形优化设计
Optimized design of cavity-like structure under aerodynamic thermal constraints
刘芙群 1李波 2孙晓峰 1张亮3
作者信息
- 1. 中国运载火箭技术研究院,北京 100076
- 2. 陆军航空兵研究所,北京 101121
- 3. 中国航天空气动力技术研究院,北京 100074
- 折叠
摘要
Abstract
The three-dimension Navier-Stokes equations are solved to reveal the aerothermal behavior of the cavity-like structure of protuberance on the surface of flight vehicles. Based on the calculated supersonic flow field and the local heat flux, the aerothermodynamic mechanism of the cavity-like structure is discussed. It is indicated that the heat flux peak is at the front edge of the cavity. An optimized shape is designed for reducing the peak value of the heat flux injected to the front edge. It is shown that the heat-flux onto the front wall is reduced to only about 20 percent of the initial value with the original shape.关键词
气动热效应/类凹腔结构/N-S方程/外形优化设计Key words
aerodynamic heating/cavity-like structure/N-S equations/optimized profile design分类
航空航天引用本文复制引用
刘芙群,李波,孙晓峰,张亮..可降低气动热效应的类凹腔外形优化设计[J].航天器环境工程,2018,35(3):205-209,5.
