窄条翼布局导弹摇滚特性及流动机理

doi:10.7527/S1000-6893.2016.0252

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

窄条翼布局导弹摇滚特性及流动机理

冯黎明, 达兴亚, 吴军强, 赵忠良

中国空气动力研究与发展中心高速空气动力研究所, 绵阳 621000

收稿日期:2016-05-09 修回日期:2016-08-24 出版日期:2017-04-15 发布日期:2016-09-26
通讯作者: 冯黎明 E-mail:fenglm8201@163.com
基金资助:
国家自然科学基金（11372336，91216203，11532016）

Rock motion and flow mechanism of missile configuration with strake wings

FENG Liming, DA Xingya, WU Junqiang, ZHAO Zhongliang

High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2016-05-09 Revised:2016-08-24 Online:2017-04-15 Published:2016-09-26
Supported by:
National Natural Science Foundation of China (11372336, 91216203, 11532016)

摘要/Abstract

摘要：

钝头体窄条翼布局导弹在大攻角下拥有极为优异的纵向气动特性，但横向容易失稳，做快速机动时容易诱发非指令的横向不稳定运动。通过开展高速风洞自由摇滚试验和数值模拟，研究了窄条翼导弹自由摇滚特性和流动机理，试验与计算吻合较好。研究发现：较大迎角时，窄条翼面积中心距离尾舵前缘根部5~6倍直径时，模型会进入极限环摇滚，窄条翼位置对模型稳定性有显著的影响，去掉窄条翼或尾舵时，模型均不会进入摇滚；模型空间流场特性表明，气流经过窄条翼时形成的片涡，对背风舵产生强烈的干扰，抑制了尾舵涡的形成和发展，使背风舵动态失稳，导致模型进入极限环摇滚。

关键词: 窄条翼, 导弹, 极限环摇滚, 动态, 流动干扰

Abstract:

Blunt forebody missile configuration with strake wings has excellent longitudinal aerodynamic characteristics, but has serious problems in lateral stability to induce uncommanded motion in unsteadily lateral direction when the missile maneuvers rapidly. Free-to-roll aerodynamics and flow mechanism of missile with strake wings are studied through high speed wind turnel free-to-roll tests and numerical simulation. Results of simulations agree well with wind tunnel test results. Study shows that model enters into limit cycle rock when the distance between the center of the area of strake wings and leading edge of tail fins is 5 to 6 diameters. Position of strake wings has significant effect on the stability of model. The model will not enter into limit-cycle rock when strakes or tail fins are removed. Spacial flow characteristics show that the wing vortices generated by strake wings can strongly interfere leeward fins to affect the formation and development of fin vortices. This leads to the loss of dynamic stability of leeward fins, and model thus enters limit-cycle rock.

Key words: strake wing, missile, limit-cycle rock, dynamic, flow interference

中图分类号:

V211.3

冯黎明, 达兴亚, 吴军强, 赵忠良. 窄条翼布局导弹摇滚特性及流动机理[J]. 航空学报, 2017, 38(4): 120410-120410.

FENG Liming, DA Xingya, WU Junqiang, ZHAO Zhongliang. Rock motion and flow mechanism of missile configuration with strake wings[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(4): 120410-120410.

参考文献

[1] NGUYEN L T, YIP L P, CHAMBERS J R. Self induced wing rock of slender delta wings:AIAA-1981-1883[R]. Reston:AIAA, 1981.
[2] DIMITRIADIS G, COOPER J E. Limit cycle oscillation control and suppression[J]. Aeronautical Journal, 1999, 103(1023):257-263.
[3] NELSON H C, ANDREW S A. Experimental investigation of wing rock of slender wings and aircraft configurations, fluid dynamics of high angle of attack[M]. Berlin:Springer-verlag,1992:413-422.
[4] ANANTHKRISHNAN N, SUDHAKAR K. Characterization of periodic motions in aircraft lateral dyanmics[J]. Journal of Guidance, Control, and Dynamics, 1996, 19(3):680-685.
[5] PLANEAUX J B, BECK J A, BAUMANN D D. Bifurcation analysis of a model fighter aircraft with control augmentation:AIAA-1990-2836[R]. Reston:AIAA, 1990.
[6] EVANS C. An investigation of large amplitude wing-rock[J]. The Aeronautical Journal, 1984, 38(873):55-57.
[7] CHADERJIAN N M. Navier-Stokes prediction of large-amplitude delta-wing roll oscillations[J]. Journal of Aircraft, 1994, 31(6):1333-1340.
[8] NELSON R C, ARENA A S, THOMPSON S A. Aerodynamic and flow field hysteresis of slender wing aircraft undergoing large-amplitude motions:AGARD CP-498[R]. Neuilly:AGARD,1992.
[9] BRANDON J M, NGUYEN L T. Experimental study of effects of forebody geometry on high angle of attack static and dynamic stability:AIAA-1986-331[R]. Reston:AIAA, 1986.
[10] ROSS A J. Investigation of nonlinear motion experienced on a slender-wing research aircraft[J]. Journal of Aircraft, 1972, 9(9):625-631.
[11] LIEBST B S. The dynamics, predicition, and control of wing rock in high-performance aircraft[J]. Philosophical Transactions of Royal Society, 1998, 356(1745):2257-2276.
[12] ORLIKRUCKEMANN K J. Aerodynamic aspects of aircraft dynamics at high angles of attack[J].Journal of Aircraft, 1983, 20(9):737-752.
[13] ERICSSON L E. Various sources of wing rock[J]. Journal of Aircraft, 1990, 27(6):488-494.
[14] 姜浴标, 孙海生, 张钧, 等. 不同部件对机翼摇滚特性影响的风洞试验研究[J]. 飞行力学, 2002, 20(4):39-43. JIANG Y B, SUN H S, ZHANG J, et al. Investigation on wing rock in a low speed wind tunnel for fighter with different configurations[J]. Flight Dynamics, 2002, 20(4):39-43 (in Chinese).
[15] 刘伟, 刘小亮, 张涵信, 等. 大攻角运动时的机翼摇滚问题综述[J]. 力学进展, 2008, 38(2):214-228. LIU W, LIU X L, ZHANG H X, et al. A review on investigations of wing rock problems under high angles of attack[J]. Advances in Mechanics, 2008, 38(2):214-228 (in Chinese).
[16] ALLEN J M. Aerodynamics of an axisymmetric missile concept having cruciform strakes and in-line rail fins form Mach 0.60 to 4.63:NASA/TM-2005-213541[R]. Washington, D.C.:NASA, 2005.
[17] 阎超. 计算流体力学方法及应用[M]. 北京:北京航空航天大学出版社, 2006:18-23. YAN C. CFD method and applications[M]. Beijing:Beihang University Press, 2006:18-23 (in Chinese).
[18] 钱杏芳, 林瑞雄, 赵亚男. 导弹飞行力学[M]. 北京:北京理工大学出版社, 2008:36-41. QIAN X F, LIN R X, ZHAO Y N. Missile flight mechanics[M]. Beijing:Beijing Institute of Technology Press, 2008:36-41 (in Chinese).
[19] DUBUC L, CANTARITI F, WOODGATE M, et al. Solution of the unsteady Euler equations using an implicit dual-time method[J]. AIAA Journal, 1998, 36(8):1417-1424.
[20] ROE P. Approximate Riemann solvers, parameter vectors, and different schemes[J]. Journal of Computational Physics, 1981, 43(2):357-372.
[21] 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. DA X Y, TAO Y, ZHAO Z L. Numerical simulation of virtual flight based on prediction-correction method and chimera grid[J]. Acta Aeronautica et Astronatica Sinica, 2012, 33(6):977-983 (in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

窄条翼布局导弹摇滚特性及流动机理

Rock motion and flow mechanism of missile configuration with strake wings

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	仇钰清, 李俨, 郎金溪, 刘育衔, 王重. 高速直升机过渡模态鲁棒自适应姿态控制[J]. 航空学报, 2024, 45(9): 529927-529927.
[2]	赵春晖, 刘安萌, 吕洋, 潘泉. 无人机韧性自主定位技术综述[J]. 航空学报, 2024, 45(8): 28839-028839.
[3]	周洪淼, 于剑桥, 于勇. 敏捷转弯伞弹系统动力学建模与分岔特性分析[J]. 航空学报, 2024, 45(7): 229012-229012.
[4]	尹洪玉, 吴宇, 梁天骄. 固定翼无人机巡逻覆盖协同路径规划方法[J]. 航空学报, 2024, 45(6): 328944-328944.
[5]	姚博清, 陈嘉宇, 谷长超, 陆钦华, 王旭航, 葛红娟. 基于分层安全控制结构的导弹装备任务安全性动态评价方法[J]. 航空学报, 2024, 45(6): 228858-228858.
[6]	王祝, 张梦通, 张振鹏, 徐广通. 基于多指标动态优先级的无人机协同路径规划[J]. 航空学报, 2024, 45(4): 328816-328816.
[7]	李国强, 宋奎辉, 覃晨, 赵光银, 吴霖鑫, 杨永东. 基于后缘小翼的翼型动态失速主动控制试验[J]. 航空学报, 2024, 45(3): 128699-128699.
[8]	付佳伟, 杨泽斐, 蔡亚辉, 聂祥樊, 齐乐华. 基于高速冲击异质惯性场的金属各向异性动态力学属性虚场表征法[J]. 航空学报, 2024, 45(10): 229221-229221.
[9]	肖冰, 张海朝. 航天器姿态稳定强化学习鲁棒最优控制方法[J]. 航空学报, 2024, 45(1): 628890-628890.
[10]	杨庶. 具有边界保护性能的直升机飞-发一体化控制律[J]. 航空学报, 2023, 44(S1): 727560-727560.
[11]	刘晨阳, 吴大伟, 郭一泽, 吕欣赛, 周佳妮, 邵书义. 不确定强耦合下四旋翼姿态鲁棒自适应控制[J]. 航空学报, 2023, 44(S1): 727645-727645.
[12]	董彦钊, 周延, 邹继贤, 王信, 李晓冬, 崔洪帅. 试车台供气压缩机组并网控制方法[J]. 航空学报, 2023, 44(9): 327221-327221.
[13]	李政, 于剑桥, 赵新运. 空空导弹敏捷转弯固定时间收敛滑模控制[J]. 航空学报, 2023, 44(8): 327262-327262.
[14]	刘远贺, 黎克波, 何绍溟, 梁彦刚. 基于最优误差动力学的变速导弹飞行路程控制制导律[J]. 航空学报, 2023, 44(7): 326909-326909.
[15]	高琦翔, 张丁为, 杨立军, 富庆飞. 反压条件下离心喷嘴动态特性实验[J]. 航空学报, 2023, 44(7): 127130-127130.