高超声速风洞双体同步分离捕获轨迹试验技术  

Dual-body synchronous captive trajectory test technique in hypersonic wind tunnel

作　　者：林敬周[1] 解福田[1] 钟俊[1] 邹东阳 皮阳军[2] LIN Jingzhou;XIE Futian;ZHONG Jun;ZOU Dongyang;PI Yangjun(Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China;State Key Laboratory of Mechanical Transmission,Chongqing University,Chongqing 400044,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [2]重庆大学机械传动国家重点实验室,重庆400044

出　　处：《空气动力学学报》2023年第5期77-86,76,I0002,共12页Acta Aerodynamica Sinica

基　　金：国家数值风洞工程(NNW)。

摘　　要：为了更准确地模拟质量与体积相当的高超声速飞行器多体分离过程,在国内首次研发了高超声速风洞双体同步捕获轨迹试验技术。通过将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、实时气动及动力学解算、上/下机构联动组合控制、上/下机构运动分配四项关键功能融为一体的设计方式,建立了Φ1 m高超声速风洞双体同步分离试验平台。结合两级入轨空天飞行器标模的多体分离特性研究,开展了马赫数6条件下典型状态的双体CTS(captive trajectory system)试验验证。验证结果表明建立的高超声速风洞双体同步捕获轨迹试验技术较好地获得了飞行器两级分离轨迹及气动特性,纵向气动力试验精度优于4.8%、力矩优于6.2%,纵向捕获轨迹预测精度优于8.7%,可以满足高超声速飞行器两级分离过程中均有较大位姿变化的多体分离模拟。In order to accurately simulate the multi-body separation process of hypersonic vehicle with equivalent mass and volume,a dual-body synchronous captive trajectory test technique in the hypersonic wind tunnel is developed for the first time.Based on this technique,the dual-body synchronous separation test platform of the hypersonic wind tunnels is established in the four-in-one design mode,which combines four key functionalities together,i.e.,data acquisition of the total pressure and total temperature of the wind tunnel settling chamber,the forces from the balance mounted on the models,etc.,real-time aerodynamic and dynamic calculations,linkage combination control of the upper/lower mechanism,and motion distribution of the upper/lower mechanism.Taking advantages of the standard model of TSTO(Two-Stage-to-Orbit),the test verification of typical states of the dual-body CTS(Captive Trajectory System)at Mach 6 is carried out in theΦ1m hypersonic wind tunnel.The verification results show that the established dual-body synchronous separation test technique in the hypersonic wind tunnel can well obtain the two-stage separation trajectory and the aerodynamic characteristics of the hypersonic aircraft.The test accuracy is better than 4.8%for the aerodynamic forces in the longitudinal direction,higher than 6.2%for the moments,and more than 8.7%for the longitudinal captive trajectory.The new test technique can meet the requirement of multi-body separation simulations with large position and attitude changes during the two-stage separation process of hypersonic aircraft.

关 键 词：高超声速风洞 多体分离 双体同步捕获轨迹 并联分离 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程] V411.7