有翼高超声速再入飞行器气动设计难点问题  

Difficulties in aerodynamic design problems of the winged hypersonic reentry vehicle

作　　者：杨勇[1] 张辉[1] 郑宏涛[1] 

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《航空学报》2015年第1期49-57,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国防基础科研项目(JCKY2013601B)~~

摘　　要：有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。The winged hypersonic reentry vehicle has been a hot research topic in recent years and aerodynamic design is the key of aircraft design. In this paper the development, advantages and the overall mission profile of the winged hypersonic reentry vehicles are introducted for understanding the difficulties more clearly. Detailed introduction of the difficulties problems are conducted from five aspects in the aerodynamic design of the aircraft, including multi-constraint complex plane symmetry aerodynamic configuration design, effects of the real gas on aerodynamic characteristics, difference conversion method between flight and ground, reaction control system （FICS） jet interference effects on aerodynamic characteristics and the uncertainties of aerodynamic data. Moreover this paper also expounds the significance of these difficulties problems on the overall design and gives the preliminary solution, which could provide some references for the winged hypersonic reentry vehicles on the aerodynamic design.

关 键 词：有翼再入 高超声速 气动设计 真实气体效应 RCS喷流干扰 天地换算 气动数据不确定度 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] V212.1