Hardware-in-the-loop simulation method and influence analysis of missiles considering body elasticity
-
摘要: 随着对导弹速度和精度等性能要求的提高,弹性特性已成为导弹动力学分析与设计中不可忽略的因素。弹性振动将对导弹的飞行特性和控制精度产生较大的影响。因此,在对弹性体导弹进行半物理仿真时,考虑弹体弹性振动所产生的影响,有利于提高仿真的真实度。本文发展了考虑弹体弹性的导弹飞行动力学数学仿真框架,建立了弹性体导弹半物理仿真系统各环节的数学模型,实现了半物理环节动力学模型在数学仿真框架中的集成与一体化仿真,并在此基础上分析了弹性振动和仿真设备在弹性体导弹半物理仿真中的影响,数值仿真结果表明,研究结果可以为考虑弹体弹性的导弹半物理仿真提供一定的理论基础。Abstract: With the increasing requirements of velocity and accuracy, the elasticity has been a non-ignorable factor in the dynamic analysis and design of missiles, which could evidently influence the flight performance and control accuracy. In this case, considering the elastic vibration of missiles would improve the precision while running a hardware-in-the-loop simulation of a flexible missile. A flight dynamic model considering the elasticity was developed, and the model of hardware-in-the-loop simulation system was established at the same time. The integrated simulation of math simulation model and hardware-in-the-loop simulation model was realized, based on which, the influences of the elastic vibration and the simulation equipment were analyzed. The results could provide a theoretical basis for the future hardware-in-the-loop simulation of missiles considering the elasticity.
-
[1] BEAL T R. Dynamic stability of a flexible missile under constant and pulsating thrusts[J].AIAA Journal,1965,3(3):486-494. [2] 王良明. 大长径比弹箭在飞行时的柔性变形特性分析[J].兵工学报,2000,21(2):108-111. WANG L M.An analysis on the flexibility in flight of projectiles or rockets having high L/D ratios[J].Acta Armamentarii,2000,21(2):108-111(in Chinese). [3] 杨超,吴志刚. 导弹气动伺服弹性稳定性分析[J].飞行力学,2000,18(4):1-5. YANG C,WU Z G.Aeroservoelastic stability of missile[J].Flight Dynamics,2000,18(4):1-5(in Chinese). [4] 臧涛成,胡焕性. 大长细比弹箭弹性效应研究综述[J].弹道学报,1999,11(3):89-93. ZANG T C,HU H X.A review of great slenderness ratio projectile elastic effect research[J].Journal of Ballistics,1999,11(3): 89-93(in Chinese). [5] 高强. 弹性体导弹振动主动控制研究[D].合肥:中国科学技术大学,2009:1-55. GAO Q.Active vibration control of flexible missiles[D].Hefei:University of Science and Technology of China,2009:1-55(in Chinese). [6] 李家文. 大型捆绑火箭姿态控制系统的建模、设计与分析[D].长沙:国防科学技术大学,2011:1-147. LI J W.Modeling, design and analysis of large strap-on launch vehicle's attitude control system[D].Changsha:National University of Defense Technology,2011:1-147(in Chinese). [7] DU W,WIE B, WHORTON M.Dynamic modeling and flight control simulation of a large flexible launch vehicle[C]//Proceedings of AIAA Guidance,Navigation and Control Conference and Exhibit,2008.Reston:AIAA,2008:AIAA-2008-6620. [8] 孟秀云. 导弹制导与控制系统原理[M].北京:北京理工大学出版社,2003:35-91. MENG X Y.Principle of missile guidance and control system[M].Beijing:Beijing Institute of Technology Press,2003:35-91(in Chinese). [9] WASZAK M R, SCHMIDT D K.Flight dynamics of aeroelastic vehicles[J].Journal of Aircraft,1988,25(6):563-571. [10] SCHMIDT D K, RANEY D L.Modeling and simulation of flexible flight vehicles[J].Journal of Guidance,Control and Dynamics,2001,24(3):530-546. [11] CHAE S, HODGES D H.Dynamics and aeroelastic analysis of missiles[C]//Proceedings of 44th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference.Reston:AIAA,2003:AIAA-2003-1968. [12] 李玉林,李晅, 杨树兴.过载自动驾驶仪分析研究[J].战术导弹技术,2008(5):63-68. LI Y L,LI X,YANG S X.Analysis of lateral acceleration autopilot[J].Tactical Missile Technology,2008(5):63-68(in Chinese). [13] 魏先利,夏群力, 祁载康.姿态及过载自动驾驶仪比例导引对比研究[J].弹箭与制导学报,2003,23(4):5-8. WEI X L,XIA Q L,QI Z K.Comparison study of proportional navigation guidance law of attitude and acceleration autopilot[J].Journal of Projectiles,Rockets,Missiles and Guidance,2003,23(4):5-8(in Chinese). [14] 单家元,孟秀云, 丁艳.半实物仿真[M].北京:国防工业出版社,2008:18. SHAN J Y,MENG X Y,DING Y.Hardware-in-the-loop simulation[M].Beijing:National Defense Industry Press,2008:18(in Chinese). [15] 毕业. 导弹半实物仿真系统误差分析[D].西安:西北工业大学,2006:19-20. BI Y.Error analysis of missile's hardware-in-the-loop simulation system[D].Xi'an:Northwestern Polytechnical University,2006:19-20(in Chinese).
点击查看大图
计量
- 文章访问数: 1047
- HTML全文浏览量: 90
- PDF下载量: 633
- 被引次数: 0