Research on the force measuring system of hypersonic vehicle in the impulse wind tunnel
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摘要: 吸气式高超声速飞行器具有各系统高度耦合的特点，现阶段的主要研究手段是在脉冲燃烧风洞中开展一体化飞行器带动力试验。针对脉冲燃烧风洞的特点，发展了一体化飞行器风洞试验快速测力方法。对试验模型和天平组成的测力系统进行了建模，获得了测力系统结构设计准则；采用数值仿真和锤击法获得了测力系统的模态，对试验过程中模型振动信号进行分析研究。结果表明：测力系统的振动频率满足测力要求，且其振动形式与锤击法测定模态一致。在脉冲燃烧风洞中开展的飞行器带动力试验结果表明：测力系统满足脉冲燃烧风洞测力要求，能够获得大尺度高超声速一体化飞行器气动力载荷，且满足精度要求，证明了在脉冲燃烧风洞中开展大尺度高超声速一体化飞行器技术研究的可行性。Abstract: Strong coupling is the salient feature of the hypersonic airbreathing vehicle. Currently the most important research method is the powered experiment of the full system vehicle in impulse combustion wind-tunnel. Firstly, based on the characteristics of the impulse wind tunnel, a fast measurement method of an integrated vehicle wind-tunnel experiment was developed in this paper. The dynamic equation of the force measurement system consisting of the test model and the balance was derived and a structural designation rule was obtained by analyzing the equation. Then, the mode analysis of the force measurement system was conducted through the simulation and the hammering test, and also the vibration signal was monitored by the acceleration sensor. The results show that the frequency of the model system meets the request of the force measurement and the vibration shape is in consistent with hammering test mode. Finally, the impulse combustion wind-tunnel experiment of the powered vehicle was carried out and the result proves that the designed model could meet the request of the impulse combustion wind-tunnel and could acquire the accurate aerodynamic load of the large-scale hypersonic integrated vehicle. All the above investigation proves that it is practical to do the research of the large-scale hypersonic integrated vehicle in the impulse combustion wind-tunnel.
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表 1 天平模态测试参数
Table 1. Mode test parameters of balance
阶数 频率/Hz 阻尼/% 振型描述 1 176.980 0.098 固定框x-z平面弯曲 2 311.370 0.270 z向平动 3 320.420 0.041 x-y平面弯曲 4 388.788 0.823 绕x轴扭转 5 529.550 0.158 绕y轴扭转 6 548.662 0.362 y-z平面弯曲 
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表 2 试验模型模态计算结果
Table 2. Mode analysis result of test model
阶数 频率/Hz 振型描述 1 30.949 绕y轴扭转 2 41.277 绕z轴扭转 3 49.269 绕x轴扭转 4 76.382 横侧向平动 5 83.766 x-y平面弯曲
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表 3 试验模型模态测量结果
Table 3. Mode test result of test model
阶数 频率/Hz 阻尼/% 振型描述 1 26.180 2.583% 绕y轴扭转 2 39.465 3.232% x-y平面弯曲 3 46.530 6.083% x-z平面弯曲 4 65.429 3.257% 绕x轴扭转 5 102.627 1.205% 前体x-y平面弯曲
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[1] 乐嘉陵, 刘伟雄, 贺伟, 等.脉冲燃烧风洞及其在火箭和超燃发动机研究中的应用[J].实验流体力学, 2005, 19(1):1-10. doi: 10.3969/j.issn.1672-9897.2005.01.001Le J L, Liu W X, He W, et al. Impulse combustion wind tunnel and its application in rocket and scramjet research[J]. Journal of Experiments in Fluid Mechanics, 2005, 19(1):1-10. doi: 10.3969/j.issn.1672-9897.2005.01.001 [2] 唐志共, 许晓斌, 杨彦广, 等.高超声速风洞气动力试验技术进展[J].航空学报, 2015, 36(1):86-97. http://d.old.wanfangdata.com.cn/Periodical/hkxb201501008Tang 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. http://d.old.wanfangdata.com.cn/Periodical/hkxb201501008 [3] Tanno H, Kodera M, Komuro T, et al, Aerodynamic force measurement on a large-scale model in a short duration test facility[J]. Review of Scientific Instruments, 2005, 76(3):035107. doi: 10.1063/1.1865815 [4] Tanno H, Komuro T, Sato K, et al, Aerodynamic force mea-surement technique with accelerometers in the impulsive facility HIEST[M]//Shock Waves. Springer Berlin Heidelberg, 2009. [5] Tanno H, Komuro T, Takahashi M, et al, Unsteady force measurement technique in shock tubes[J]. Review of Scientific Instruments, 2004, 75(2):532-536. doi: 10.1063/1.1641156 [6] Singh P, Menezes V, Irimpan K J, et al, Impulse force balance for ultrashort duration hypersonic test facilities[J]. Shock and Vibration, 2015:803253. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=Doaj000004229441 [7] Naumann K W, Ende H, Mathieu G, et al, Millisecond aerodynamic force measurement with side-jet model in the ISL shock tunnel[J]. AIAA Journal, 1993, 31(6):1068-1074. doi: 10.2514/3.11730 [8] Robinson M, Hannemann K. Short duration force measurements in impulse facilities[R]. AIAA-2006-3439, 2006. [9] Smith A L, Mee D J, Daniel W J T, et al, Design, modelling and analysis of a six component force balance for hypervelocity wind tunnel testing[J]. Computer and Structures, 2001, 79(11):1077-1088. doi: 10.1016/S0045-7949(01)00005-0 [10] Sahoo N, Suryavamshi K, Reddy K P J, et al. Dynamic force balances for short-duration hypersonic testing facilities[J]. Experiments in Fluids, 2005, 38(5):606-614. doi: 10.1007/s00348-005-0932-5 [11] Laurence S J, Hornung H G, Image-based force measurement in hypersonic facilities[J]. Experiments in Fluids, 2009, 46(2):343-353. doi: 10.1007/s00348-008-0565-6 [12] Laurence S J, Karl S, An improved visualization-based force-measurement technique for short-duration hypersonic facilities[J]. Experiments in Fluids, 2010, 48(6):949-965. doi: 10.1007/s00348-009-0780-9 [13] Pieterse F F, Bidgood P M. An experimental four-component optical fibre balance[R]. AIAA-2015-1564, 2015. [14] Collopy A, Lee S, Marineau E C. Development of dynamic force measurement capabilities at AEDC tunnel 9[R]. AIAA-2014-0983, 2014. [15] 张小庆, 杨富荣, 鲍伟义, 等.直连式脉冲燃烧风洞起动过程研究[J].实验流体力学, 2009, 23(2):63-67. doi: 10.3969/j.issn.1672-9897.2009.02.014Zhang X Q, Yang F R, Bao W Y, et al. Investigation on the starting process of the direct impulse combustion wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2009, 23(2):63-67. doi: 10.3969/j.issn.1672-9897.2009.02.014 [16] 姜宗林, 李进平, 赵伟, 等.长试验时间爆轰驱动激波风洞技术研究[J].力学学报, 2012, 44(5):824-831. http://d.old.wanfangdata.com.cn/Conference/7714651Jiang Z L, Li J P, Zhao W, et al. Approaches to extend the test time for detonation-driven shock tunnel[J]. Chinese Journal of Theoretical and Applied Mechanics, 2012, 44(5):824-831. http://d.old.wanfangdata.com.cn/Conference/7714651 [17] Wang Y P, Liu Y F, Luo C T, et al. Force measurement using strain-gauge balance in a shock tunnel with long test duration[J]. Review of Scientific Instruments, 2016, 87(5):055108. doi: 10.1063/1.4950781 [18] Wang Y P, Liu Y F, Jiang Z L, et al, Design of a pulse-type strain gauge balance for a long-test-duration hypersonic shock tunnel[J]. Shock Waves, 2016, 26(6):835-844. doi: 10.1007/s00193-015-0616-x [19] 汪运鹏, 刘云峰, 苑朝凯, 等.长试验时间激波风洞测力技术研究[J].力学学报, 2016, 48(3):545-556. http://d.old.wanfangdata.com.cn/Periodical/lxxb201603004Wang Y P, Liu Y F, Yuan C K, et al. Study on force measurement in long-test duration shock tunnel[J]. Chinese Journal of Theoretical and Applied Mechanics, 2016, 48(3):545-556. http://d.old.wanfangdata.com.cn/Periodical/lxxb201603004 [20] 贺伟, 童泽润, 李宏斌.单模块超燃发动机推力测量天平研制[J].航空动力学报, 2010, 25(10):2285-2289. http://d.old.wanfangdata.com.cn/Conference/6202133He W, Tong Z R, Li H B. Investigation of thrust balance for the single module scramjet[J]. Journal of Aerospace Power, 2010, 25(10):2285-2289. http://d.old.wanfangdata.com.cn/Conference/6202133 [21] 王锋, 贺伟, 毛鹏飞, 等.脉冲风洞测力系统建模与载荷辨识方法研究[J].振动与冲击, 2015, 34(1):94-103. http://d.old.wanfangdata.com.cn/Periodical/zdycj201501020Wang F, He W, Mao P F, et al. Dynamic modeling of testing system in impulse facilities and load identification method[J]. Journal of Vibration and Shock, 2015, 34(1):94-103. http://d.old.wanfangdata.com.cn/Periodical/zdycj201501020 -
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