Abstract: In order to provide an effective wind tunnel test prediction for multi-body separation security assessment of high Mach number vehicles, the key problems and their solutions of multi-body separation test system in Φ1m hypersonic wind tunnel were presented. Multi-body separation trajectory captive test technique platform of Φ1m hypersonic wind tunnel were developed by the ‘three-in-one’ design method, including the data acquisition of total pressure and total temperature of wind tunnel settling chamber and force from balance mounted in the models etc., the calculation of aerodynamics and dynamics, and the mechanism motion control. Experimental verifications were carried out with certain high Mach number vehicle model at Mach number 5 by doing grid test and captive trajectory system (CTS) test. The test results show that satisfactory separation trajectory and aerodynamic characteristics are obtained by the multi-body separation test system mentioned above, which meets the functional needs of high Mach number multi-body separation experiment to realize grid force measuring and trajectory capturing. In the case of capturing 35 trajectory points at a running, continuous trajectory control mode can save less 42.5% running time than position control mode, as improves the test efficiency.

Key words: High Mach number;Multi-body separation;Captive trajectory;Test technique;Wind tunnel test

摘要： 为了给高马赫数飞行器多体分离安全评估提供有效的风洞试验预测手段，提出了Φ1m高超声速风洞多体分离试验系统研制的关键技术及解决办法。通过“风洞前室总温总压信号及模型天平测力信号等的数据采集、气动及动力学解算、机构运动控制”三位一体的设计方式，建立了Φ1m高超声速风洞多体分离轨迹捕获试验技术平台。结合高马赫数飞行器开展了马赫数5条件下的网格测力试验和典型状态的捕获轨迹系统（Captive trajectory system，CTS）试验验证。验证结果表明，研制的Φ1m高超声速风洞多体分离试验系统较好地获得了飞行器分离轨迹及气动特性，可以满足高马赫数多体分离试验的网格测力、捕获轨迹等功能需求，且在一次吹风捕获35个轨迹点的情况下，连续轨迹控制模式相较位置控制模式节约了42.5%的风洞运行时间，提高了试验效率。

关键词: 高马赫数;多体分离;捕获轨迹;试验技术;风洞试验