带边条翼导弹滚转稳定性分析
收稿日期: 2014-11-13
修回日期: 2014-12-30
网络出版日期: 2015-02-11
基金资助
江苏省普通高校研究生科研创新计划(CXLX12_0134); 中央高校基本科研业务费专项资金
Rolling stability analysis of missile with strake wing
Received date: 2014-11-13
Revised date: 2014-12-30
Online published: 2015-02-11
Supported by
Funding of Jiangsu Innovation Program for Graduate Education (CXLX12_0134); The Fundamental Research Funds for the Central Universities
为了分析带边条翼导弹模型的非线性自由滚转运动及滚转稳定特性,采用理论分析与动态测力试验、滚转自由度释放测量试验相结合的方式,对低速来流条件下模型0°~60°迎角范围内的滚转运动、滚转稳定特性随迎角变化的规律进行了研究。在10°迎角时,模型在4个"+"形位置是滚转静稳定的并且在"+"形位置上滚转运动保持平衡;迎角大于20°的范围内滚转静稳定的平衡位置变到4个"×"形位置上;并且迎角为20°时模型在"×"形位置滚转保持平衡,迎角大于30°后模型产生滚转极限环自激振荡运动,迎角达到60°时模型的滚转运动发散演变为高速旋转的形式。研究结果表明:模型滚转运动的形式决定于滚转力矩的静、动稳定特性。
耿玺 , 史志伟 , 程克明 , 龚正 , 刘超 . 带边条翼导弹滚转稳定性分析[J]. 航空学报, 2015 , 36(10) : 3241 -3248 . DOI: 10.7527/S1000-6893.2015.0006
In order to study the nonlinear free rolling motion and rolling stability of a missile mounted with strake wing, different methods are used including the theoretical method, the dynamic force tests and the free-to-roll measurement. The free rolling motion and the changing of the rolling stability have been studied from the angle of attack(AOA) from 0° to 60° under the low speed free stream condition. At AOA of 10° the rolling statically stable positions are where the model looks like "+" shape and the model can keep stable at these positions after being released rolling free. When the angle of attack is higher than 20°, the rolling statically stable positions have changed to where the model is "×" shaped. And at AOA of 20° the model can keep rolling stable at the position where the model is "×" shaped. When the AOA is higher than 30°, the model generates the limit cycle oscillation itself at the positions where the model is "×" shaped. When the AOA reaches 60°, the rolling motion becomes spinning after the limit cycle oscillation diverges. The results indicate that the rolling motions are determined by the static and dynamic stability of rolling moment.
[1] Herbst W B. Future fighter technologies[J]. Journal of Aircraft, 1980, 17(8): 561-566.
[2] Herbst W B. Dynamic of aircraf combat[J]. Journal of Aircraft, 1983, 20(7): 594-598.
[3] Wu T. More sharper fighting short sword[J]. Modern Weapons, 2006(11): 38-42 (in Chinese). 吴涛. 更锋利的格斗短刃世界第四代近距空空导弹评析.现代兵器, 2006(11): 38-42.
[4] Xing X L, Liu D J. Discussion of the key technology for the fourth generation close-in infrared air-to-air missiles[J]. Aero Weaponry, 2001(6): 37-40 (in Chinese). 邢晓岚, 刘代军. 第四代红外近距格斗空空导弹关键技术探讨[J]. 航空兵器, 2001(6): 37-40.
[5] Fan H T. Characteristics and key technologies of the fifth generation of air to air missiles[J]. Aeronautical Science & Technology, 2011(3): 1-5 (in Chinese). 樊会涛. 第五代空空导弹的特点及关键技术[J]. 航空科学技术, 2011(3):1-5.
[6] Ming B Y, Song J S, Xing X L. Japan's air-to-air missiles development and performance analysis[J]. Aerodynamic Missile Journal, 2013(9): 28-33 (in Chinese). 明宝印, 宋劲松, 邢晓岚. 日本空空导弹发展情况和性能分析[J]. 飞航导弹, 2013(9): 28-33.
[7] Nelson R C, Pelletier A. The unsteady aerodynamics of slender wings and aircraft undergoing large amplitude maneuvers[J]. Progress in Aerospace Sciences, 2003, 39(2-3): 185-248.
[8] Zhang H X, Liu W, Xie Y F. On the rocking motion and its dynamic evolution of a swept delta wing[J]. Acta Aerodynamica Sinica, 2006, 24(1): 5-9 (in Chinese). 张涵信, 刘伟, 谢昱飞. 后掠三角翼的摇滚及其动态演化问题[J]. 空气动力学学报, 2006, 24(1): 5-9.
[9] Xu K Z, Zhang Y F, Chen H X, et al. Numerical study of induced nonlinear rolling moment of finned missile at high angle of attack[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(1): 97-104 (in Chinese). 徐柯哲, 张宇飞, 陈海昕, 等. 导弹大迎角下非线性诱导滚转力矩数值研究[J]. 航空学报, 2014, 35(1): 97-104.
[10] Meyer J. Effects of the roll angle on cruciform wingbody configurations at high incidences[J]. Journal of Spacecraft and Rockets, 1994, 31(1): 113-122.
[11] Balasubramanian R, Shah V, Arora K, et al. Numerical investigations of lateral characteristics of an air-to-air missile[J]. Journal of Aircraft, 2013, 50(1): 87-95.
[12] Daniels P. A study of the nonlinear rolling motion of a four-finned missile[J]. Journal of Spacecraft and Rockets, 1970, 7(4): 510-512
[13] Cohen C J, Clare T A, Stevens F L. Analysis of the nonlinear rolling motion of finned missiles[J]. AIAA Journal, 1974, 12(3): 303-309.
[14] Da X Y, Zhao Z L, Tao Y, et al. Experimental investigation on free-to-roll motion of strake missile[J]. Journal of Experiment in Fluid Mechanics, 2012, 26(6): 40-43 (in Chinese). 达兴亚, 赵忠良, 陶洋, 等. 窄条翼导弹模型摇滚特性试验研究[J]. 实验流体力学, 2012, 26(6): 40-43.
[15] Da X Y, Tao Y, Zhao Z L. Numerical simulation of virtual flight based on prediction-correction coupling method and chimera grid [J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(6): 977-983 (in Chinese). 达兴亚, 陶洋, 赵忠良. 基于预估校正和嵌套网格的虚拟飞行数值模拟[J]. 航空学报, 2012, 33(6): 977-983.
[16] Dong B Y. Investigation of aerodynamic configuration and related technology for the new generation infrared air-to-air missile[J]. Aero Weaponry, 1996, 34(Z1): 18-22 (in Chinese). 董秉印. 新一代红外型空空导弹气动布局及其相关技术探讨[J]. 航空兵器, 1996, 34(Z1): 18-22.
[17] Shi Z W, Li L Y, Cheng K M, et al. Wind-tunnel high attack angle dynamic testing device based on hybrid mechanism: China, CN101929915B[P]. 2011-11-30 (in Chinese). 史志伟, 李鹭扬, 程克明, 等. 基于混联机构的风洞大攻角动态实验装置: 中国, CN101929915B[P]. 2011-11-30.
[18] Zhang H X, Yuan X Y, Xie Y F, et al. Research on the dynamic stability of an orbital reentry vehicle in pitching[J]. Acta Aerodynamica Sinica, 2002, 20(3): 247-259 (in Chinese). 张涵信, 袁先旭, 谢昱飞, 等. 飞船返回舱俯仰运动的动态稳定性研究[J]. 空气动力学学报, 2002, 20(3): 247-259.
[19] Zhang H X, Yuan X Y, Xie Y F, et al. Study of the dynamic stability of a pitching unfinned reentry capsule[J]. Acta Aerodynamica Sinica, 2004, 22(2): 130-134 (in Chinese). 张涵信, 袁先旭, 谢昱飞, 等. 不带稳定翼飞船返回舱俯仰动稳定性研究[J]. 空气动力学学报, 2004, 22(2): 130-134.
[20] Liu W, Zhang H X. Nonlinear dynamic analysis and simulation of wing rock for a slender wing[C]//Progress in Computational Fluid Dynamics—Proceeding of 12th China Computational Fluid Dynamics Conference. Beijing: Aerodynamic Society of China, 2004: 370-376 (in Chinese). 刘伟, 张涵信. 细长机翼摇滚的非线性动力学分析及数值模拟[C]//计算流体力学研究进展——第十二届全国计算流体力学会议论文集. 北京: 中国空气动力学会, 2004: 370-376.
[21] Zhang H X, Liu W, Xie Y F, et al. On the rocking motion and its dynamic evolution of a swept delta wing[J]. Acta Aerodynamica Sinica, 2006, 24(1): 5-9 (in Chinese). 张涵信, 刘伟, 谢昱飞, 等. 后掠三角翼的摇滚及其动态演化问题[J]. 空气动力学学报, 2006, 24(1): 5-9.
/
〈 | 〉 |