Micro Rolling Moment Measurements for Asymmetric-Wing Standard Model and Dynamic Characteristics of Air Bearing
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摘要:
基于气浮轴承的自由滚转实验技术是测量再入飞行器小不对称滚转气动力的重要方法.文章研究中对偏翼标模进行了小滚转力矩测量，并针对实验系统的特点，对气浮轴承进行了无风实验标定和真空实验标定，给出了其动态特性结果.进一步分析了气浮轴承动态特性、原始数据采集测量误差和参数辨识误差对实验结果的影响，并给出了综合误差分析结果，说明了主要误差来源.结果显示：滚转力矩系数和滚转阻尼导数测量综合误差分别约为10-7和10-4量级，实验中可根据实际情况进行误差处理.研究结果对气浮轴承自由滚转实验精度提高、方案设计和设备研制等具有重要的实际意义.
Abstract:The free-rolling measurement technique based on air bearing is an important method to measure small rolling aerodynamics of slightly asymmetric re-entry vehicle. In this paper, micro rolling moments of asymmetric-wing standard model were measured, and the air bearing was calibrated under windless or vacuum conditions. The effects of air-bearing dynamic characteristics, measurement error in original data acquisition, and parameter identification error were analyzed in allusion to characteristics of testing system. The results of comprehensive error and dominating error were identified for standard model test. The analysis results show the comprehensive errors of rolling moment coefficient and roll damping derivative approximate 10-7 and 10-4 respectively. There are different treatments of error in various tests. The research results have importantly practical significances to improving the accuracy, designing projects and instruments of free-rolling testing system based on air bearing.
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Key words:
- air bearing /
- asymmetric-wing standard model /
- calibration /
- dynamic characteristics /
- error analysis
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表 1 附加滚转力矩无风实验标定结果
Table 1. Calibration results of additional rolling moment under windless conditions
ID P/(r/min) δL0, a/(mN·m) 1 300~200 6.61×10-2 2 300~100 1.36×10-2 3 600~200 1.74×10-1 4 600~400 1.94×10-1 5 400~300 5.48×10-2 avg. 400~100 4.48×10-2 
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表 2 附加滚转阻尼力矩无风和真空实验标定结果
Table 2. Calibration results of additional roll damping moment under windless and vacuum conditions
ID δLp, a(windless)/(mN·m·s) δLp, a(vacuum)/(mN·m·s) 1 -1.74×10-2 -1.30×10-2 2 -2.04×10-2 -1.29×10-2 3 -2.08×10-2 -1.30×10-2 4 -1.73×10-2 -1.23×10-2 5 — -1.34×10-2 6 — -1.26×10-2 7 — -1.18×10-2 8 — -1.19×10-2 avg. -1.90×10-2 -1.26×10-2
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表 3 标模实验结果
Table 3. Experimental results of standard model
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表 4 拉偏参数辨识结果
Table 4. Parameter identification results of deflection
parameters δCl0, d δClp, d I ±3.00×10-7 ±2.36×10-5 P, $\dot P$ ±3.04×10-7 ±4.40×10-10 all ±6.04×10-7 ±2.36×10-5
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表 5 参数辨识中各系数
Table 5. Coefficients in parameter identification
R Sk Sd δCl0, i δClp, i 0.856 2.83×10-5 6.48×10-4 5.18×10-8 1.23×10-5
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表 6 结果汇总
Table 6. Review of results
types Cl0 Clp standard model 1.43×10-4 -1.12×10-2 ablation model 1×10-6~8×10-5 (-2~-6)×10-3 calibration results 5.77×10-7 -8.82×10-4 measurement error ±6.04×10-7 ±2.36×10-5 parameter identi-fication error 5.18×10-8 1.23×10-5
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[1] Glover L S, Hagen J C. The motion of ballistic missiles[R]. AD731662, 1971. [2] 蔡金狮, 董能力. 再入弹头滚转共振概率估算[J]. 宇航学报, 1995, 16(1): 1-7, 95. https://www.cnki.com.cn/Article/CJFDTOTAL-YHXB501.000.htmCai J S, Dong N L. Roll resonance probability prediction for re-entry vehicle[J]. Journal of Astronautics, 1995, 16(1): 1-7, 95(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-YHXB501.000.htm [3] 和争春, 车竞, 肖涵山, 等. MF-1弹道设计与蒙特卡罗飞行仿真[J]. 空气动力学学报, 2019, 37(2): 201-206. doi: 10.7638/kqdlxxb-2018.0062He Z C, Che J, Xiao H S, et al. Trajectory design and Monte Carlo flight simulation for MF-1[J]. Acta Aerodynamica Sinica, 2019, 37(2): 201-206(in Chinese). doi: 10.7638/kqdlxxb-2018.0062 [4] 刘明霞, 田锋, 杨辉. 带五分量抑制机构的高精度滚转力矩测量技术[J]. 实验流体力学, 2013, 27(5): 71-74. https://www.cnki.com.cn/Article/CJFDTOTAL-LTLC201305013.htmLiu M X, Tian F, Yang H. A high-precision rolling moment measuring technique of five components restraining system[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(5): 71-74(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LTLC201305013.htm [5] 于卫青, 刘高计, 袁先士, 等. 微量滚转力矩天平测量技术研究[J]. 弹箭与制导学报, 2015, 35(1): 107-110, 117. https://www.cnki.com.cn/Article/CJFDTOTAL-DJZD201501027.htmYu W Q, Liu G J, Yuan X S, et al. The study of measurement technology of micro-scale roll moment balance[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2015, 35(1): 107-110, 117(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-DJZD201501027.htm [6] Wang Y H, 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, 98. http://www.syltlx.com/CN/article/downloadArticleFile.do?attachType=PDF&id=10847 [7] 白葵, 冯明溪, 付光明. 小不对称再入体滚转气动力测量技术[J]. 流体力学实验与测量, 2002, 16(3): 63-67, 72. https://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200203011.htmBai K, Feng M X, Fu G M. Experimental technique for rolling aerodynamic of slight asymmetric re-entry body[J]. Experiments and Measurements in Fluid Mechanics, 2002, 16(3): 63-67, 72(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LTLC200203011.htm [8] 赵俊波, 梁彬, 付增良, 等. 机动式再入弹头小滚转气动力风洞试验技术[J]. 空气动力学学报, 2016, 34(1): 53-58. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201601011.htmZhao J B, Liang B, Fu Z L, et al. Experimental technique for micro rolling aerodynamics of a maneuvering re-entry body[J]. Acta Aerodynamica Sinica, 2016, 34(1): 53-58(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201601011.htm [9] 赵俊波, 梁彬, 付增良, 等. Φ1米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. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX202002007.htmZhao J B, Liang B, Fu Z L, et al. Measurement technique for micro rolling moments based on Φ1 m hypersonic wind tunnel[J]. Acta Aerodynamica Sinica, 2020, 38(2): 260-267(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX202002007.htm [10] 张石玉, 赵俊波, 梁彬, 等. 参数辨识技术在再入弹头自由滚转风洞试验中的应用[J]. 弹箭与制导学报, 2016, 36(6): 113-117. https://www.cnki.com.cn/Article/CJFDTOTAL-DJZD201606030.htmZhang 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(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-DJZD201606030.htm [11] 付光明, 冯明溪. 小不对称弹头滚转气动阻尼试验[R]. 北京: 北京空气动力研究所, 1996.Fu G M, Feng M X. Experiment for rolling aerodynamic damping of slight asymmetric re-entry body[R]. Beijing: Beijing Institute of Aerodynamics, 1996(in Chinese). [12] 武颖丽, 李平舟. 扭摆法测量刚体转动惯量的误差分析[J]. 大学物理实验, 2015, 28(3): 101-103. https://www.cnki.com.cn/Article/CJFDTOTAL-DWSL201503029.htmWu Y L, Li P Z. Error of the inertia moment using torsion pendulum method[J]. Physical Experiment of College, 2015, 28(3): 101-103(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-DWSL201503029.htm [13] 龚振雄. 普通物理实验中的数据处理[M]. 西安: 西北电讯工程学院出版社, 1985: 1-4. [14] 傅建明, 李欣益, 唐海敏, 等. 基于Chebyshev-Taylor-Fourier混合级数模型函数的多源气动数据融合方法[J]. 气体物理, 2021, 6(1): 45-51. http://qtwl.cbpt.cnki.net/WKD/WebPublication/paperDigest.aspx?paperID=59befb2b-3919-4b35-b033-6b445966d875Fu J M, Li X Y, Tang H M, et al. A fusion method for multi-source aerodynamic data based on Chebyshev-Taylor-Fourier combined series model function[J]. Physics of Gases, 2021, 6(1): 45-51(in Chinese). http://qtwl.cbpt.cnki.net/WKD/WebPublication/paperDigest.aspx?paperID=59befb2b-3919-4b35-b033-6b445966d875 -
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