Measurement technique for micro rolling moments based on <i>Φ</i>1m hypersonic wind tunnel

ZHAO Junbo; LIANG Bin; FU Zengliang; ZHANG Xu; ZHANG Shiyu

doi:10.7638/kqdlxxb-2018.0089

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

更新时间：2026-05-28

- Measurement technique for micro rolling moments based on Φ1m hypersonic wind tunnel
- Vol. 38, Issue 2, Pages: 260-267(2020)
- 作者机构：
  
  中国航天空气动力技术研究院,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0089
  CLC： V211.78
- Published：2020
- 稿件说明：
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赵俊波, 梁彬, 付增良, 张旭, 张石玉. Φ1m高超声速风洞小滚转力矩测量技术[J]. 空气动力学学报, 2020, 38(2): 260-267.

ZHAO Junbo, LIANG Bin, FU Zengliang, et al. Measurement technique for micro rolling moments based on Φ1m hypersonic wind tunnel[J]. 2020, 38(2): 260-267. DOI: 10.7638/kqdlxxb-2018.0089.
赵俊波, 梁彬, 付增良, 张旭, 张石玉. Φ1m高超声速风洞小滚转力矩测量技术[J]. 空气动力学学报, 2020, 38(2): 260-267. DOI： 10.7638/kqdlxxb-2018.0089.

ZHAO Junbo, LIANG Bin, FU Zengliang, et al. Measurement technique for micro rolling moments based on Φ1m hypersonic wind tunnel[J]. 2020, 38(2): 260-267. DOI: 10.7638/kqdlxxb-2018.0089. DOI：

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。

Abstract

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

1 m hypersonic 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

1 m hypersonic wind tunnel with series test conditions

especially at high angl

e 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.

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references

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WILLIAMS E P. Experimental studies of ablation surface patterns and resulting roll torques[J]. AIAA Journal, 1971, 9(7):1315-1321.

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WANG Y, LIU W, XIE B, et al. Research on a micro-rolling-moment six-component strain gauge balance of composite structure[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(3):76-79.

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ZHAO J B, LIANG B, FU Z L, et al. Experimental technique for micro rolling aerodynamics of a maneuvering reentry body[J]. Acta Aerodynamica Sinica, 2016, 34(1):53-58.

ZHANG S Y, ZHAO J B, LIANG B, et al. Application of parameter identification technology in free-rolling wind tunnel tests of reentry body[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2016, 36(6):113-117.

TANG Z G, XU X B, YANG Y G, et al. Research progress on hypersonic wind tunnel aerodynamic testing techniques[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):86-97.

XIE F, GUO L T, ZHU T, et al. Research on the test technique of Reynolds number variety in a hypersonic wind tunnel[J]. Acta Aerodynamica Sinica, 2016, 34(3):398-403.

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

DOI：10.7638/kqdlxxb-2018.0089

摘要

Abstract

关键词

Keywords

references