常规高超声速风洞级间动态分离装置设计与应用

对于采用助推级和巡航级串联布局方式的高超声速飞行器，需研制风洞模型级间动态分离装置，对助推级和巡航级级间分离运动过程开展研究。中国空气动力研究与发展中心超高速空气动力研究所针对某常规高超声速风洞的动态分离装置进行了详细设计与分析，主要包括动态分离支撑结构设计、动态分离支撑与释放装置设计。利用有限元分析方法得到了支撑结构固有频率，评估分析了支撑结构性能。利用视觉测量系统对动态分离支撑与释放装置性能进行了评估，得到了撑开到闭合的运动轨迹及运行时间。在某常规高超声速风洞上开展了风洞模型级间动态分离试验。计算及试验结果表明:支撑结构固有频率、动态分离支撑与释放装置运行时间（78 ms）满足风洞试验需求。针对不同风洞具体情况进行适应性改造，动态分离支撑与释放装置可广泛应用于常规高超声速风洞模型级间动态分离试验。

Design and application of the dynamic stage separation device in hypersonic wind tunnel

In order to study motion characteristics of the separation between the cruise stages and booster stages, it is needed to develop the device of the dynamic stage separation for the dynamic stage separation wind tunnel test. Hypervelocity aerodynamics institute of CARDC studied and developed the dynamic separation device aimed at application in routine hypersonic wind tunnels, which includes the support system of dynamic separation and the dynamic stage separation support and release device. In the design, the finite element analysis is used to evaluate the characteristics of the support structure. The analysis contains the inherent frequency analysis. The vision measurement system is used to measure the trajectory and the runtime of the dynamic stage separation support and release device. The runtime is 78 ms, which satisfies the requirement of the wind tunnel test. Finally a series of wind tunnel tests were conducted in the hypersonic wind tunnel. The results of computation and the wind tunnel test indicate that: the inherent frequency of the support structure, and the runtime of the dynamic stage separation support and release device, which is 78 ms, can satisfy the need of the wind tunnel. According to the different particular wind tunnel circumstances, the size of the dynamic separation device can be reformed, which can be applied to different hypersonic wind tunnels.