通过脉动压力风洞试验测量，对比分析了跨声速（马赫数介于0.75~1.2）不同锥角和锥长大小的级间段对锥柱外形飞行器局部脉动压力的影响规律。结果表明，肩部脉动压力主要由以低频为主导的激波振荡所致，能量集中在100 Hz左右的窄带区间，且表现为随着马赫数增加，脉动压力系数峰值先增大后减小，并随着肩部激波的后移而不断向后推移。此外，通过对比分析5种不同锥角模型（10°、12.7°、15.3°、20°、25°）的脉动压力系数最大值发现，随着锥角的增加，脉动压力表现出当锥角小于15°时先平缓增加，随着锥角增大脉动压力系数增加幅度进一步加大的趋势。对比分析不同锥长模型的结果发现，锥长对局部脉动压力的最大峰值几乎没有影响，影响的只是脉动压力在肩部作用区域的大小以及峰值出现的马赫数范围，且表现为锥柱级间段越长其作用范围越大，对应于峰值的马赫数区间越宽。
Variations of fluctuating pressure on different interstage sections at transonic speeds between Ma at 0.75 to 1.2 are investigated through wind tunnel measurement, and the effect laws of the pressure fluctuation on the flight vehicle with different cone angles and lengths are obtained. Results show that the strong fluctuating pressure is mainly caused by low-frequency shock wave oscillation, of which the power is largely located in the range of 100 Hz. Meanwhile, with the increase of Mach number, the maximum fluctuating pressure coefficient in shoulder region increases first and then decreases sharply for each configuration, and the peak value of the fluctuating pressure coefficient moves backward along the flow direction. Moreover, by comparing the maximum fluctuating pressure coefficient of five cone angle configurations, including 10°, 12.7°, 15.3°, 20°, and 25°, this paper finds that with the increase of cone angle, the pressure fluctuation increases gently when the cone angle is less than 15°, and the value increases sharply as the cone angle increases more. Furthermore, the comparison of different cone length configurations shows that while the cone length is of almost no effect on the peak value of the local fluctuating pressure, it impacts on the scale and range of Mach number at peak value. The longer the conical connector, the larger the effect area, and the wider the range of Mach number in which the peak of pressure fluctuation arises.
[1] ROBERTSON J E. Unsteady pressure phenomena for basic missile shapes at transonic speeds[C]//AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 1964.
[2] 徐立功, 刘振寰. 再入飞行器脉动压力环境的分析与预测[J]. 空气动力学学报, 1991, 9(4):457-464. XU L G, LIU Z H. Prediction of maneuvering reentry vehicles fluctuating pressure environments[J]. Acta Aerodynamica Sinica, 1991, 9(4):457-464(in Chinese).
[3] LANANELLI A L, WOLFER H F. Prediction of fluctuating pressure in attached and separated turbulent boundary-layer flow[J]. Journal of Aircraft, 1993, 30(6):962-970.
[4] 黄岬嵋, 王剑. 飞机加改装部件绕流脉动压力研究[J]. 航空学报, 2000, 21(4):326-329. HUANG J M, WANG J. Research on the fluctuating pressure of the flow around the aircraft component under modification[J]. Acta Aeronautica et Astronautica Sinica, 2000, 21(4):326-329(in Chinese).
[5] 孟德虹, 孙岩,王运涛,等. 战斗机垂尾脉动压力数值模拟[J]. 航空学报, 2016, 37(8):2472-2480. MENG D H, SUN Y, WANG Y T, et al. Numerical simulation of fluctuating pressure of fighter vertical tail[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8):2472-2480(in Chinese).
[6] 陈伟芳, 张志成,石于中,等. 再入体表面脉动压力环境的预测[J]. 国防科技大学学报, 2001, 23(6):20-23. CHEN W F, ZHANG Z C, SHI Y Z, et al. The prediction of fluctuating pressure on the surface reentry vehicles[J]. Journal of National University of Defense Technology, 2001, 23(6):20-23(in Chinese).
[7] KUMAR R, VISWANATH P R, PRABHU A. Mean and fluctuating pressure in boat-tail separated flows at transonic speeds[J]. Journal of Spacecraft and Rockets, 2002, 39(3):430-438.
[8] 龙万花, 陈伟芳,宋松和. 旋成体跨音速脉动压力环境分析与预测[J]. 国防科技大学学报, 2004, 26(1):17-20. LONG W H, CHEN W F, SONG S H. Analysis and prediction of the fluctuating pressure induced by rotated aircraft at transonic Mach numbers[J]. Journal of National University of Defense Technology, 2004, 26(1):17-20(in Chinese).
[9] 洪杰, 高金海,马艳红,等. 球头锥-柱再入飞行器的动力环境预示[J]. 北京航空航天大学学报, 2008, 34(8):878-882. HONG J, GAO J H, MA Y H, et al. Foreshowing study of dynamic environment on the sphere-cone-cylinder reentry vehicles[J]. Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(8):878-882(in Chinese).
[10] 王娜, 高超. 弹体脉动压力特征的实验研究[J]. 实验流体力学, 2010, 24(1):30-35. WANG N, GAO C. Experimental research of fluctuating pressure on surface for a certain missile configuration[J]. Journal of Experiment in Fluid Mechanics, 2010, 24(1):30-35(in Chinese).
[11] 操小龙, 罗金玲,周丹杰,等. 锥-柱体外形脉动压力及抖振载荷响应研究[J]. 战术导弹技术, 2010(1):67-72. CAO X L, LUO J L, ZHOU D J, et al. The research of fluctuating pressure and buffeting load on the cone-column body[J]. Tactical Missile Technology, 2010(1):67-72(in Chinese).
[12] 任淑杰, 张收运,闫桂荣. 基于RANS/NLAS的火箭跨声速脉动压力环境预示[J]. 固体火箭技术, 2011, 34(4):418-422. REN S J, ZHANG S Y, YAN G R. A prediction of fluctuation pressure conditions with transonic rocket by RANS/NLAS method[J]. Journal of Solid Rocket Technology, 2011, 34(4):418-422(in Chinese).
[13] DAVID J P, MARTIN K S, RUSS D R. Comparison of Ares I-X wind-tunnel derived buffet environment with flight data[C]//29th AIAA Applied Aerodynamics Conference. Reston, VA:AIAA, 2011.
[14] DAVID J P, MARTIN K S, RUSS D R, et al. Overview of the space launch system transonic buffet environment test program[C]//53rd AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2015.
[15] ANDREW J H, WILLIAM A C, DARREN K R. Overview of the space launch system ascent aeroacoustic environment test program[C]//54th AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2016.
[16] DAVID J P, MARTIN K S, RUSS R. Sensitivity of space launch system buffet forcing functions to buffet mitigation options[C]//54th AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2016.
[17] MARTIN K S, DAVID J P, RUSS R. Initial assessment of space launch system transonic unsteady pressure environment[C]//53rd AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2015.
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