This paper simulates a missile launch process by the computational fluid dynamics (CFD) method, through which the aerodynamic interference and rules of missile movement with and without consideration of the plume field are studied. A moving chimera grid approach is used coupled with an unsteady Euler flow solver, and a 6-DOF model is fully integrated into the CFD solution procedure to capture the time-dependent interference between the stationary and moving boundaries. Two thruster models are developed to account for the influence of thruster rockets on the flowfield. One model applies an equivalent massflux at the rocket nozzle exit in order to simulate the rocket plume effects. For the second model, the thrust vector exerted by the rockets is attached to the missile body for the duration of the run. And the paper presents the results obtained for a time-accurate missile launching from the quasi-"Global Hawk" unmanned aerial vehicle (UAV) by the developed numerical methods. All major trends of the trajectory are captured, including the displacements, angular orientations, pressure coefficient distribution on the plane in the captive position, and force coefficients histories during separation, which are then used for comparison. The results show that the effect of the plume field is significant on the missile dynamic characteristics and aerodynamic interference. The simulations may provide a tool for design verification and risk mitigation for the missile launch procedure.
XU Xiaoping, ZHU Xiaoping, ZHOU Zhou, WANG Junli
. Numerical Simulation of Missile Launching and Aerodynamic Interference with Plume Effects[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(4)
: 580
-588
.
DOI: CNKI:11-1929/V.20101221.0956.057
[1] Meakin R L. Computations of the unsteady flow about a generic wing/pylon/finned-store configuration. AIAA-1992-4568, 1992.
[2] Coleman L A, Jolly B A, Chesser B L, Jr, et al. Numerical simulation of a store separation event from an F-15E aircraft. AIAA-1996-3385, 1996.
[3] 车竞, 唐硕, 谢长强. 空射导弹发射初始弹道数值仿真[J]. 空气动力学学报, 2006, 24(2): 205-208. Che Jing, Tang Shuo, Xie Changqiang. The initial trajectory numerical simulation of air launched missile[J]. Acta Aerodynamic Sinica, 2006, 24(2): 205-208. (in Chinese)
[4] 王正裕, 李孝伟. 基于动态嵌套网格技术的飞行器导弹发射的数值模拟[J]. 上海大学学报: 自然科学版, 2008, 14(2): 174-176. Wang Zhengyu, Li Xiaowei. Simulation of air launched missile based on moving chimera grid[J]. Journal of Shanghai University: Natural Science, 2008, 14(2): 174-176. (in Chinese)
[5] 沈琼, 余雄庆. 无人机机载导弹分离轨迹的数值仿真[J]. 弹箭与制导学报, 2009, 29(5): 99-102. Shen Qiong, Yu Xiongqing. Numerical simulation of trajectory of missile separated from UAV[J]. Journal of Projectiles, Rockets, Missile and Guidance, 2009, 29(5): 99-102. (in Chinese)
[6] 杨明智, 桂业伟, 刘刚, 等. 导弹投放分离的数值模拟[J]. 空气动力学学报, 2006, 24(2): 261-264. Yang Mingzhi, Gui Yewei, Liu Gang, et al. Numerical simulation of missile separation[J]. Acta Aerodynamic Sinica, 2006, 24(2): 261-264. (in Chinese)
[7] 傅德彬, 姜毅. 用动网格方法模拟导弹发射过程中的燃气射流流场[J]. 宇航学报, 2007, 28(2): 423-426. Fu Debin, Jiang Yi. Simulation of jet flow during missile launching with dynamic mesh[J]. Journal of Astronautics, 2007, 28(2): 423-426. (in Chinese)
[8] Lijewski L E, Suhs N E. Time-accurate computational fluid dynamics approach to transonic store separation tra-jectory prediction[J]. Journal of Aircraft, 1994, 31(4): 886-891.
[9] Tarhan E, Kavsaoglu M S. Parallel overset-grid Euler solution of generic wing pylon and finned store[J]. Journal of Aircraft, 2005, 42(5): 1337-1339.
[10] 韩忠华. 旋翼绕流的高效数值计算方法及主动流动控制研究. 西安: 西北工业大学, 2007. Han Zhonghua. Efficient method for simulation of viscous flows past helicopter rotors and active flow control.Xi’an: Northwestern Polytechnical University, 2007. (in Chinese)
[11] Landon R H. NACA 0012 oscillatory and transient pitching. Compendium of Unsteady Aerodynamic Measurements, AGARD-R-702, 1982.
[12] Murman S M, Aftosmis M J, Berger M J. Simulations of 6-DOF motion with a cartesian method. AIAA-2003-1246, 2003.
[13] Roger R P, Chan S C, Heisler R R. Aerodynamic coefficient differences between power-on and power-off for a maneuverable boosting missile. AIAA-2006-3865, 2006.
[14] Gleissl R, Deslandes R M. Simulation of missile plumes for aircraft store compatibility assessments. AIAA-2005-54, 2005.
[15] York B J, Sinha N, Dash S M, et al. Complete analysis of steady and transient missile aerodynamic-propulsive-plume flowfield interactions. AIAA-1992-3603, 1992.
[16] Hall L H, Parthasarathy V. Validation of an automated chimera 6-DOF methodology for multiple moving body problems. AIAA-1998-753, 1998.
[17] Ahmad J U, Shanks S P, Buning P G. Aerodynamics of powered missile separation from F/A-18 aircraft. AIAA-1993-766, 1993.
[18] 苗瑞生, 居贤铭. 火箭气体动力学[M]. 北京: 国防工业出版社, 1985: 302-311. Miao Ruisheng, Ju Xianming. Gas dynamics for rocket[M]. Beijing: National Defense Industry Press, 1985: 302-311. (in Chinese)
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