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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 aerodynamic layout of the approaching space vehicle poses many problems to its aerodynamic characteristics, especially flight stability, which endangers flight safety. Therefore, aiming at the HTV-2 aircraft layout scheme, the aerodynamic characteristics during hypersonic flight are studied. The comparison between the numerical calculation and the experimental results shows that the two systems have good consistency, and at the same time, it is found that the aircraft has a high lift-drag ratio and the vertical and horizontal directions are statically stable, and the aerodynamic characteristics are given under different flight speeds and altitude conditions Under the dynamic test of two degrees of freedom coupled with wind tunnel test, it can be seen that the oscillating motion occurs during roll-over under forced pitch motion.