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

作　　者：刘芙群[1] 李波 孙晓峰[1] 张亮[3] LIU Fuqun;LI Bo;SUN Xiaofeng;ZHANG Liang(China Academy of Launch Vehicle Technology,Beijing 100076,China;Army Aviation Research Institute,Beijing 101121,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[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

出　　处：《航天器环境工程》2018年第3期205-209,共5页Spacecraft Environment Engineering

摘　　要：针对飞行器上由凸起物形成的类凹腔气动加热问题,采用数值方法求解三维N-S方程,研究了类凹腔外形结构的高超声速气动加热规律,获得了三维高超声速流场和局部热流分布,并详细分析了局部的流场结构和气动加热机理。针对凹腔前壁面热流密度过高的问题,提出并验证了一种降低前壁面边缘热流密度的优化外形,将前壁面的热流密度降低至优化前的20%左右。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 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]