导弹鲁棒高阶滑模制导控制一体化研究
收稿日期: 2012-11-28
修回日期: 2013-01-10
网络出版日期: 2013-01-15
基金资助
航空科学基金(20110196005)
Research of Integrated Robust High Order Sliding Mode Guidance and Control for Missiles
Received date: 2012-11-28
Revised date: 2013-01-10
Online published: 2013-01-15
Supported by
Aeronautical Science Foundation of China (20110196005)
董飞垚 , 雷虎民 , 周池军 , 李炯 , 邵雷 . 导弹鲁棒高阶滑模制导控制一体化研究[J]. 航空学报, 2013 , 34(9) : 2212 -2218 . DOI: 10.7527/S1000-6893.2013.0054
Aiming at the disadvantages of traditional two-loop guidance and control system against high speed and maneuverable targets, an integrated sliding mode guidance and control is derived in this paper. Through combining the intercept geometry with missile dynamics and basing on the principle of zeroing the line of sight (LOS) rate, a guidance and control problem is transformed to that of stabilization of a third integral chain system. Based on geometric homogeneity, a global finite-time stabilization control law for nominal systems is proposed. For the uncertainty of the system caused by target maneuverability and missile aerodynamic parameter perturbation, a compensating control law is provided using the super twisting algorithm (STA). Simulation results show that the proposed integrated guidance and control algorithm possesses the advantages of smaller miss distance and smoother variations in missile attitude and elevators over the conventional two-loop design.
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