一种临近空间飞行器静/动态气动特性研究  

Numerical and experimental investigation on aerodynamic characteristics for one typical near space vehicle

作　　者：李乾[1] 赵忠良[1] 叶友达[2] 陶洋[1] 马上[1] 李玉平[1] 王晓冰[1] 

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000 [2]空气动力学国家重点试验室中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2017年第4期504-509,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(91216203;11532016)

摘　　要：临近空间飞行器典型气动布局给其气动特性尤其是飞行稳定性带来诸多问题,危及飞行安全。为此,针对类HTV-2飞行器布局方案,开展了高超声速飞行时的气动特性研究。通过数值计算和试验结果的对比可见,两者具有较好的一致性,同时看出飞行器具有较高的升阻比,纵横向为静态稳定,并且给出了气动特性在不同飞行速度和高度条件下的变化规律;飞行器单自由度运动具有动态稳定性特性,但是通过风洞试验进行的两自由度耦合运动动态特性试验可以看出,在强迫俯仰运动下滚转出现振荡运动。The typical near space vehicle configuration causes many problems on aerodynamic characteristics especially the stability of the vehicle, which threatens the flight security. Therefore, the research was performed on an HTV-2 like configuration for hypersonic characteristics. The wind tunnel test and computational data were given and compared in this paper with a great coherence, which shows this vehicle could meet the design requirements with the fact that the vehicle has a relatively high ratio of lift to drag and owns satisfied static stability. For further study, the aerodynamic characteristics were also evaluated at broad speed and altitude range to study the regulation at different flight conditions. Besides, the wind tunnel test was conducted to study the effects of two-degree coupling motion on the dynamic characteristics. The results show that the forced pitching motion will cause oscillatory motion in roiling direction, although the vehicle is of one-degree dynamic stability.

关 键 词：临近空间 高超声速 升阻比 稳定性 

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]