高超声速多体分离问题是航天多体飞行器研发中的关键技术问题，基于分离过程中高速流动的复杂性，对高速多体分离的风洞试验研究极具挑战性，特别是激波风洞分离试验。激波风洞具有高速、高焓试验气流特点，更准确评估高超声速分离气动力/热特性，但是其有效试验时间短（ms量级），进行主动式动态级间分离试验极其困难。提出一种应用于激波风洞主动式多体分离试验的高速气动发射系统（High-speed Pneumatic Ejection to Launch Vehicle Model System, HPELS），使得模型在短试验时间内完成主动分离测试，详细介绍了HPELS延迟时间、模型分离时间等精确的时间标定以及时序控制方法。针对分离过程中模型的运动轨迹以及气动力参数的高性能评估，发展了基于纹影图像的非接触式分离运动轨迹捕获以及气动力参数测量技术。两级入轨（Two Stage to Orbit, TSTO）飞行器的安全级间分离是典型的高速多体分离问题，设计了并联式TSTO飞行器并针对作者提出的纵向分离方案，在JF-12复现飞行条件激波风洞验证了高速动态多体分离试验技术应用的有效性，同时首次在激波风洞对TSTO纵向分离方案进行了原理性验证。初步对比结果显示，试验结果与数值计算结果具有良好的一致性。

The multi-body separation problem in hypersonic flow is a key technical issue in the research and development of aerospace multibody vehicles. Due to the complexity of high-speed flow during separation, the wind tunnel test study is extremely challenging, particularly the shock tunnel separation test.  The test flow of the shock tunnel has the characteristics of high flow speed and high enthalpy, which can simulate the flow characteristics with gas effect at high temperature and duplicate the reliable aerodynamic and thermal characteristics of hypersonic multibody separation. However, its effective test time is short in order of milliseconds; therefore it is difficult to conduct dynamic tests of separation.  In this study, a high-speed pneumatic ejection to launch vehicle model system (HPELS) applied to the shock tunnel is proposed, which enables the model to actively complete the separation within the short test time. The precise time calibration and timing control methods of HPELS delay time and separation time are introduced in detail. For the high-performance evaluation of the separation trajectory and aerodynamic pa-rameters during separation, a non-contact separation motion trajectory capture and aerodynamic parameter measurement technology based on schlieren images is developed. The safety stage separation of two stages to orbit (TSTO) vehicle is a typical high-speed separation problem. In view of the longitudinal separation scheme and parallel-staged TSTO vehicle proposed by the author, the effectiveness of the application of the high-speed dynamic multi-body separation test technology is verified in the JF-12 duplicated flight conditions shock tunnel. Meanwhile, the principle of the parallel-staged TSTO safety longitudinal stage separation scheme is verified in the shock tunnel for the first time. Comparison of the experimental results with the numerical results shows good agreement.