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Volume 35 Issue 11
Nov.  2009
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Journal of Beijing University of Aeronautics and Astronautics  > 2009  >  35(11): 1315-1319.
Zhang Jing, Shen Gongzhang, Yang Lingyuet al. Design of flight control system based on inverse dynamics and center of gravity estimation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(11): 1315-1319. (in Chinese)
Citation: Zhang Jing, Shen Gongzhang, Yang Lingyuet al. Design of flight control system based on inverse dynamics and center of gravity estimation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(11): 1315-1319. (in Chinese)
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Design of flight control system based on inverse dynamics and center of gravity estimation

  • School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • Received Date: 28 Oct 2008
  • Publish Date: 30 Nov 2009
    Abstract
  • Due to the center of gravity varying over a specified range, the aircraft may deviate from its known dynamics, thus bringing special problems to the attitude control system. A synthesis approach based on in-flight estimation of center of gravity position and the inverse dynamics was proposed. First of all, a six degree-of-freedom flight dynamics model of aircraft with center of gravity offset was built. Based on the above model, the inverse dynamics in analytical form was obtained by deducting the dynamic equation. The estimation of center of gravity location could be obtained by the initial and updated weight data. As in-flight estimation of the center of gravity position could be utilized effectively, the simulation results demonstrate good control performance under various possible conditions of center of gravity offset. The proposed method is also clear and easy to implement.

     

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  • [1] Nguyen N, Krishnakumar K, Kaneshige J, et al. Dynamics and adaptive control for stability recovery of damaged asymmetric aircraft . AIAA-2006-6049, 2006 [2] Ostroff A J, Bacon B J.Force and moment approach for achievable dynamics using nonlinear dynamic inversion . AIAA-99-4001, 1999 [3] 柳嘉润,申功璋. 基于逆动力学和在线参数辨识的飞机姿态控制[J]. 北京航空航天大学学报, 2005, 31(2):111-115 Liu Jiarun, Shen Gongzhang. Attitude control based on inverse dynamics and online parameter identification[J].Journal of Beijing University of Aeronautics and Astronautics, 2005, 31(2):111-115 (in Chinese) [4] 吴森堂,费玉华. 飞行控制系统[M].北京:北京航空航天大学出版社, 2005:8-11 Wu Sentang, Fei Yuhua. Flight control system[M]. Beijing: Beijing University of Aeronautics and Astronautics Press, 2005: 8-11 (in Chinese) [5] Bacon B J,Gregory I M.General equations of motion for a damaged asymmetric aircraft . AIAA-2007-6306, 2007 [6] 飞机设计手册总编委会. 飞机设计手册第4册:军用飞机总体设计[M].北京:航空工业出版社, 2005:215-255 Aircraft Design Manual Committee. Aircraft design manual, part 4: Conceptual design of military aircraft[M]. Beijing: Aviation Industry Press, 2005:215-255 (in Chinese)
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