战术导弹气动伺服弹性滑模控制技术  

Sliding Mode Control Technology of Aeroservoelasticity for Tactical Missiles

作　　者：张公平[1,2] 段朝阳 赵艳辉[1] 郑鹍鹏 ZHANG Gong-ping;DUAN Chao-yang;ZHAO Yan-hui;ZHENG Kun-peng(China Airborne Missile Academy, Luoyang 471099, China;Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons, Luoyang 471099, China)

机构地区：[1]中国空空导弹研究院,洛阳471099 [2]航空制导武器航空科技重点实验室,洛阳471099

出　　处：《导航定位与授时》2019年第2期52-57,共6页Navigation Positioning and Timing

基　　金：航空科学基金(20170153002)

摘　　要：为抑制弹体弹性振动引起的控制系统品质恶化,建立了高精度弹性动态模型,采用模态自适应结构滤波技术,在极点配置优化控制参数的基础上,设计了滑模变结构策略,对局部增益进行自适应切换,实现了弹性导弹全包线鲁棒稳定。通过开发弹性弹体非线性集成仿真系统,为导弹气动伺服弹性振荡及失稳现象提供了数字仿真预测与复现手段,以全面验证飞行控制系统的综合性能。高空弹道试验与数字仿真结果表明,开发的非线性仿真系统可信度较高,滑模变结构策略设计合理,控制系统鲁棒性较强,能够抑制包括弹性振动在内的多种不确定性影响。To restrain performance deterioration of the missile flight control system caused by elastic vibration of missile, a high precision elastic dynamical model of missile is deduced and based on the optimal control mode adaptive structural filter is used in design from the pole-assignment methodology. The sliding mode variable structure strategy is synthesized to adapted local gain to different flight conditions, and the robust stability of elastic missile is achieved in full envelop. The integrated nonlinear simulation frame is developed to provide digital simulation prediction and recurrence tool for missile aeroservoelastic oscillation and instability phenomenon so as to validate comprehensive properties of missile flight control system. High altitude ballistic testing and digital simulation results indicate that the proposed nonlinear simulation system is reliable, the sliding mode variable structure strategy is reasonably designed, the control system has better robustness and a variety of uncertainties including elastic vibration can be rejected.

关 键 词：战术导弹 极点配置 气动伺服弹性 滑模控制 结构滤波 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]