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Coning motion instability of spinning missiles induced by the delay of strap-down seeker

Chinese Journal of Aeronautics 2020年第12期33卷 3360-3368页

作者： Xiao HU Shuxing YANG School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Key Laboratory of Dynamics and Control of Flight Vehicle Ministry of EducationBeijing 100081China Xi'an Modern Control and Technology Institute Xi'an 710065China

The strap-down seeker,which combines the seeker's and the onboard gyro's measurements to obtain the target information,has been extensively applied by spinning missiles.The response delay of the strap-down seeker,a novel factor that could result in crosscoupling between the acceleration commands in the pitch and yaw channels and subsequently cause the significant deterioration in dynamic stability of the spinning missile equipped with a rate loop,is noted in this paper.The sufficient and necessary stability conditions are also analytically established based on the system equation with complex coefficient,which are further verified by numerical simulations.It could be indicated that the response delay of the strap-down seeker will greatly deteriorate the dynamic stability of the whole guidance system designed by the conventional method.It is also noticed from analysis that the stable region of the combined guidance coefficient is shrunken significantly with the increase of the spinning rate.

关键词： Coning motion Dynamic stability Proportional guidance system Spinning missiles strap-down seeker

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Integrated Guidance and Control for Missiles with strap-down seeker

Integrated Guidance and Control for Missiles with Strap-down...

引用

第36届中国控制会议

作者： Xingwei Li Bin Zhao Jun Zhou Zhenxin Feng Institute of Precision Guidance and Control Northwestern Polytechnical University

ISBN: (纸本)9781538629185

Due to the fact that the detection information of the strap-down seeker is coupled with missile attitude,the line-ofsight（LOS） decoupling and the field-of-view（FOV） limit for integrated guidance and control（IGC） design has became the core problem for the missile with strap-down seeker.A new IGC method with FOV limit was proposed.First,the state space model with strict feedback type for IGC design considering FOV limit was derived based on the line-of-sight decoupling model and the traditional IGC model;second,the IGC method with part state constraints was proposed based on the Barrier Lyapunov function（BLF） and the dynamic surface control（DSC） method,by which the extended state observer（ESO） was employed to observe the mismatched uncertainties and the bounded stability of the IGC system was proved based on the Babalat’s Lemma and the Lyapunov stability theory.The simulation results imply that the proposed IGC method considering FOV limits can not only ensure the LOS angular rate converges to zero but also satisfy the FOV limit conditions.

关键词： Integrated guidance and control strap-down seeker Barrier Lyapunov function field-of-view limit

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