Φ1m高超声速风洞小滚转力矩测量技术  

Measurement technique for micro rolling moments based on Φ1m hypersonic wind tunnel

作　　者：赵俊波[1] 梁彬[1] 付增良[1] 张旭[1] 张石玉[1] ZHAO Junbo;LIANG Bin;FU Zengliang;ZHANG Xu;ZHANG Shiyu(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2020年第2期260-267,共8页Acta Aerodynamica Sinica

摘　　要：为了满足再入飞行器的不断发展需求,准确测量再入过程中烧蚀作用所产生的小量级滚转力矩,本文在近年来小口径高超声速风洞中再入飞行器小滚转力矩测量技术研究工作基础上,创新改进以气浮轴承为核心建立的低阻尼自由滚转测量试验技术,利用传统试验数据处理方法结合飞行动力学仿真等多种设计和数据分析手段,最终实现大口径高超声速风洞高马赫数、大迎角条件下多个状态点的再入飞行器试验模型滚转气动力矩精细化测量。风洞试验结果表明,试验系统工作稳定可靠,试验数据完善、合理,能够为再入飞行器的相关设计工作提供重要依据。With the development of re-entry vehicle,accurately measuring the micro rolling moments generated by ablation is increasingly required.In this paper,a low damping free-rolling measurement technique based on gas bearing is presented.This technique which was applied to Φ1 mhypersonic wind tunnel based on the innovation and improvement of corresponding work in small-scale hypersonic wind tunnel.The micro rolling moments can be well deducted and analyzed with multiple test design and data processing method,including the traditional data processing method and flight dynamics simulation technology.The related re-entry vehicle model tests were conducted in Φ1 mhypersonic wind tunnel with series test conditions,especially at high angle of attack and high Mach number.The reasonable and reliable test results show the robustness of the proposed testing system,which can provide support for the related design work of re-entry vehicle.

关 键 词：再入飞行器 小滚转力矩 气浮轴承 测量技术 

分 类 号：V211.78[航空宇航科学与技术—航空宇航推进理论与工程]