Volume 36 Issue 9
Sep.  2010
Turn off MathJax
Article Contents
Xi Shenghai, Xiang Jinwu. Simulation and flight test of trajectory in terminal guidance[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(9): 1048-1051. (in Chinese)
Citation: Xi Shenghai, Xiang Jinwu. Simulation and flight test of trajectory in terminal guidance[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(9): 1048-1051. (in Chinese)

Simulation and flight test of trajectory in terminal guidance

  • Received Date: 27 Jul 2009
  • Publish Date: 30 Sep 2010
  • A method of simulation and flight test for seeker-s particular trajectory in terminal guidance was presented. In the flight simulation of trajectory in terminal guidance, height decrease by the entry maneuver need to be achievably small, and precision request of tracking in the diving flight phase should be satisfied. A set of nonlinear 6-DOF equations was used, in which the coupling between longitude and lateral motion was considered. To keep precise tracking in the diving and flight security with large magnitude of flight speed, dive angle, height altering, 3 types of stick roll control were analyzed, and control scheme satisfies request of precision was given. In the entry phase, bank angle was firstly changed to 180°. After satisfying dive angle of the trajectory by elevator control, bank angle returned to 0°. Flight test project was accomplished to verify the reliability and availability of the control scheme. Results of flight simulation and test show that the method presented could improve flight test efficiency and the precision of aircraft tracking particular trajectory with guaranteed flight security.

     

  • loading
  • [1] 程国采.战术导弹导引方法[M].北京:国防工业出版社,1996 Cheng Guocai.Guidance methods for tactical missiles[M].Beijing:National Defense Industry Press,1996(in Chinese) [2] 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 Meng Xiuyun.Principle of missile guidance and control system[M].Beijing:Beijing Institute of Technology Press,2003(in Chinese) [3] Day R E.Coupling dynamics in aircraft:a historical perspective .NASA-SP-532,1997 [4] Mahale A,Ananthkrishnan N.Analytical criterion for onset of departure in inertia-coupled roll maneuvers of airplanes .AIAA-2006-6267,2006 [5] Roux C R,Cruciani I.Roll coupling effects on the stability margins for VEGA launcher .AIAA-2007-6630,2007 [6] Stevens B L,Lewis F L.Aircraft control and simulation[M].New York:Wiley,2003 [7] 肖业伦.航空航天器运动的建模:飞行动力学的理论基础[M]北京:北京航空航天大学出版社,2003 Xiao Yelun.Modeling of aerospace vehicles:foundation of flight dynamics[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2003(in Chinese) [8] 胡维多,张明廉,文传源.飞机急滚运动的解耦控制[J].航空学报,1994,15(7):841-846 Hu Weiduo,Zhang Minglian,Wen Chuanyuan.The decouping control for airplane in rapid roll[J].Acta Aeronautica et Astronautica Sinica,1994,15(7):841-846(in Chinese) [9] 许多生,陆启韶.飞机滚转时惯性耦合运动的分岔分析[J].航空学报,2001,22(2):144-147 Xu Duosheng,Lu Qishao.Bifurcation analysis of inertial cross coupling in aircraft rolling[J].Acta Aeronautica et Astronautica Sinica,2001,22 (2):144-147(in Chinese)
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views(3604) PDF downloads(980) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return