摘要
进行了高超声速飞行器多体系统分离过程中存在的气动力干扰试验研究.试验模型是某构型的可重复使用航天飞行器,由助推器以及再入体两部分组成.研究在FL-31风洞中进行,试验马赫数为Ma=6.97.试验结果表明:分离过程中助推器和再入体之间存在复杂的激波干扰现象,多体系统分离过程中的气动干扰本质上是激波干扰引发的.
Investigation on aerodynamic interference during stage separation of a hypersonic multi-body system was conducted in this paper.A typical reusable space vehicle was applied in this research,which is composed of a booster and a reentry part.The test was conducted in FL-31 wind tunnel with Mach number of 6.97.The results show that,complicated shock wave interference exists in the multi-body system and this aerodynamic interference during stage separation is essentially induced by shock wave interference.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第4期902-906,共5页
Journal of Aerospace Power
基金
空气动力学国家重点实验室基金(SKLA2009A0103)
863项目(2007AA702109)
国际科技合作项目(2007DFA70880)
关键词
高超声速
飞行器
风洞试验
多体干扰与分离
激波干扰
hypersonic
vehicle
wind tunnel test
multi-body interference and stage separation
shock wave interference
