Analysis on the force measurement accuracy of the integrated vehicle in the impulse wind tunnel
-
摘要: 为评估脉冲风洞一体化飞行器的测力精度,根据脉冲风洞测力系统特点,对其进行简化,建立其动力学方程,并获得其动态脉冲响应衰减函数;分析测力系统输出信号变化规律,对其进行傅里叶变换,获得系统振动主频,并运用神经网络、梯度下降法对天平信号进行准确拟合,预测了测力信号的趋势值;对多次试验结果进行了信号拟合和趋势预测,获得了天平测力的精度。结果表明:该方法能够准确预测天平稳定输出结果,且当天平输出信号达到4个周期时,测力精度能够达到97%以上。Abstract: To evaluate the force measurement accuracy of the integrated vehicle in the impulse combination wind tunnel, some actions were taken. Firstly, the force-measurement system was simplified and the dynamic equation was built according to its structural characteristics. Then, the impulse response attenuation function was deducted. Secondly, the time-dependent changing rule of the output signal of the force-measurement system was analyzed and the dominant frequency of was acquired through fast Fourier transformation (FFT) method. Next, the neural network algorithm and gradient descent algorithm were used to fit the signal of force balance and to predict the trend value of the force-measurement signal. Finally, the signal fitting and trend prediction of a number of tests data were conducted and the measurement accuracies were acquired. The result prove that this method can truly predict the stable output result, meanwhile, the measurement accuracy can reach over 97% when the output signal of force-measurement system includes 4 cycles.
-
[1] 姜宗林,俞鸿儒.高超声速激波风洞研究进展[J].力学进展,2009,39(6):766-776.JIANG Zonglin,YU Hongru.Progress of the research on hypersonic shock tunnels[J].Advance in Mechanics,2009,39(6):766-776.(in Chinese) [2] ROBINSON M J.Three-component force measurements on a large scramjet in a shock tunnel[J].Journal of Spacecraft and Rockets,2004,41(3):416-425. [3] SCHULTZI A.Hypersonic scramjet testing via diode laser absorption in a reflected shock tunnel[J].Journal of Propulsion and Power,2014,30(6):1586-1594. [4] 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):035107.1-035107.5. [5] TANNO H,KOMURO T,SATO K,et al.Aerodynamic force measurement technique with accelerometers in the impulsive facility HIEST[J].Shock Waves,2009,18(6):471-476. [6] 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. [7] SINGH P,MENEZES V,IRIMPAN K J,et al.Impulse force balance for ultrashort duration hypersonic test facilities[J].Shock and Vibration,2015,2015:803253.1-803253.8. [8] SINGH P,TRIVEDI S,MENEZES V,et al.Dynamic calibration and validation of an accelerometer force balance for hypersonic lifting models[J].The Scientific World Journal,2014,2014(6):813759. [9] NAUMANN K W.Millisecond aerodynamic force measurement with side-jet model in the ISL shock tunnel[J].AIAA Journal,1993,31(6):1068-1074. [10] SARAVANAN S,JAGADEESH G,REDDY K P J.Aerodynamic force measurement using 3-component accelerometer force balance system in a hypersonic shock tunnel[J].Shock Waves,2009,18(2):425-435. [11] ROBINSON M,HANNEMANN K.Short duration force measurements in impulse facilities[R].AIAA-2006-3439,2006. [12] SMITHA L.Design,modelling and analysis of a six component force balance for hypervelocity wind tunnel testing[J].Computer and Structures,2001,79(11):1077-1088. [13] 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. [14] LAURENCE S J.Image-based force and moment measurement in hypersonic facilities[J].Experiments in Fluids,2009,46(2):343-353. [15] 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. [16] PIETERSE F F,BIDGOOD P M.An experimental four-component optical fiber balance[R].AIAA-2015-1564,2015. [17] COLLOPY A,LEE S,MARINEAU E C.Development of dynamic force measurement capabilities at AEDC tunnel 9[R].AIAA-2014-0983,2014. [18] 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.ZHANG Xiaoqing,YANG Furong,BAO Weiyi,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.(in Chinese) [19] 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.JIANG Zongli,LI Jinping,ZHAO Wei,et al.Investigating into techniques for extending the test-duration of detonation-driven shock tunnels[J].Chinese Journal of Theoretical and Applied Mechanics,2012,44(5):824-834.(in Chinese) [20] WANG Yunpeng,LIU Yunfeng,LUO Changtong,et al.Force measurement using strain-gauge balance in a shock tunnel with long test duration[J].Review of Scientific Instruments,2016,87(5):055108.1-055108.9. [21] WANG Yunpeng,LIU Yunfeng,JIANG Zonglin.Design of a pulse type strain gauge balance for a long-test-duration hypersonic shock tunnel[J].Shock Waves,2016,26(6):835-844. [22] 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.WANG Yunpeng,LIU Yunfeng,YUAN Chaokai,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.(in Chinese) [23] 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.HE Wei,TONG Zerun,LI Hongbin.Investigation of thrust balance for the single module scramjet[J].Journal of Aerospace Power,2010,25(10):2285-2289.(in Chinese)
点击查看大图
计量
- 文章访问数: 577
- HTML浏览量: 2
- PDF量: 526
- 被引次数: 0