摘要
再入飞行器需要大阻力减速而采取钝锥外形,这种气动布局外形的飞行器动稳定风洞试验结果易受到质心位置、尾迹干扰和极限环运动等因素的影响。通过风洞试验研究了不同质心位置、不同支撑方式下尾迹干扰对返回舱配平角和动稳定性的影响,以及不同稳定模态下,试验方法对试验结果的影响。指出了在动稳定风洞试验中必须精确模拟返回舱质心位置,在大攻角状态下采取弯支杆支撑方式减少尾迹干扰,并针对极限环运动,采取轴承-滑块大振幅自由振动试验,才能得到正确的返回舱动稳定特性。
The blunt conical configuration has been considered for entry vehicles because of their high-drag characteristics. There have many parameters, such as center-of-gravity location, wake interference and limit cycles which influence the dynamic stability of reentry capsule in general. In this paper, the effects of different centroid positions, and wake interference in different support modes on dynamic stability and alignment angle of the return capsule are investigated. To get correct dynamic stability results in wind-tunnel test, it is necessary to simulate the centroid position accurately, use an angledsting to reduce wake interference, and introduce bearing-stem arrangement in the limit cycles vibration mode.
出处
《航天返回与遥感》
2013年第5期14-19,共6页
Spacecraft Recovery & Remote Sensing
关键词
返回舱
动导数风洞试验
质心位置
尾迹干扰
reentry capsule
dynamic stability characteristics
center-of-gravity location
wake interference
