基于Nussbaum增益滑模自适应控制的导弹制导控制一体化设计  

Integrated guidance and control of missile based on Nussbaum gain adaptive sliding mode control method

作　　者：齐辉[1] 张泽 许江涛[1] 韩鹏鑫[2] 张德伟[1] 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,哈尔滨150001 [2]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《控制与决策》2017年第1期93-99,共7页Control and Decision

基　　金：国家自然科学基金面上项目(11372080);哈尔滨市科技局青年创新人才基金项目(2014RFQXJ121)

摘　　要：采用Nussbaum增益滑模自适应控制方法解决导弹制导控制一体化设计问题.充分考虑一体化模型具有通道间耦合、气动建模不确定性、气动参数摄动和目标机动引起的干扰等特点,基于自适应控制对未知量的辨识能力和滑模控制的抗干扰能力,以及Nussbaum增益控制对系数不确定系统所具有的较好的控制能力,设计Nussbaum增益滑模自适应控制律,并证明系统的稳定性.仿真结果验证了所提出方法的有效性.Aiming at the problem of missile integrated guidance and control design, the Nussbaum gain adaptive sliding mode control method is proposed. Fully considering that the model of integrated guidance and control has the features of the channel coupling, the uncertainty of aerodynamic modeling, and the interference caused by the target maneuver and pneumatic parameters perturbation, based on the strong ability of adaptive control to identify unknown quantities, the ability of the sliding-mode control law to resist interference, and the control ability of the Nussbaum gain adaptive control to the system with uncertain coefficients, the Nussbaum gain adaptive sliding-mode control law is designed, and the stability of the system is proved. The simulation results show the effectiveness of the proposed method.

关 键 词：制导控制一体化 Nussbaum增益控制 自适应滑模控制 模型不确定性 

分 类 号：V448[航空宇航科学与技术—飞行器设计]