高超声速飞行器气动力/热参数辨识研究综述  

Review of aerodynamic and aero-thermodynamic parameter estimation research for hypersonic aircraft

作　　者：何开锋[1] 汪清[1] 钱炜祺[1] 和争春[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000

出　　处：《实验流体力学》2011年第5期99-104,共6页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金(10702076;11072258);空气动力学国家重点实验室基金(SKLA2009A0103)

摘　　要：飞行器气动力和气动热参数辨识是高超声速飞行器设计的关键技术之一。笔者对高超声速飞行器的气动力和气动热参数辨识技术进行了综述。介绍了飞行器气动力、气动热参数辨识的基本原理与主要方法,气动力、气动热参数辨识技术在高超声速飞行器研发中的应用情况与发展趋势。同时也简要介绍了中国空气动力研究与发展中心(CARDC)在气动力和气动热参数辨识研究方面的研究概况。Aerodynamic and aero-thermodynamic parameter estimation technique is crucial in the hypersonic aircraft design and development.In this paper,the aerodynamic and aero-thermodynamic parameter estimation technique for hypersonic aircraft is reviewed.In the first part,the basic principle and fundamental method of aerodynamic parameter estimation,its application and prospect in hypersonic aircraft engineering practice are introduced.In the second part,the basic principle and fundamental method of aero-thermodynamic parameter estimation,its application and prospect in hypersonic aircraft engineering practice are also reviewed.Simultaneously,the general advancements of aerodynamic and aero-thermodynamic parameter estimation technique for hypersonic aircraft carried out by China Aerodynamic Research and Development Center（CARDC） are briefly reported.

关 键 词：高超声速飞行器 气动力参数辨识 气动热参数辨识 

分 类 号：V211.22[航空宇航科学与技术—航空宇航推进理论与工程]