运载火箭主动段自适应增广控制

Ascent Flight Adaptive Augmenting Control for Launch Vehicles

针对运载火箭上升段在复杂飞行环境、大不确定性干扰和振动等因素的影响下,传统PID控制方法难以满足高品质控制需求的问题,进行了自适应增广控制(AAC)方法研究,以实现对运载火箭姿态的精确控制。在深入分析自适应增广控制系统整体构架的基础上,通过标称PID控制器设计与基于粒子群优化(PSO)的数字滤波器设计实现了刚体控制及对弹性振动的抑制;继而针对大范围干扰、不确定性和由于滤波器切换产生的弹性振动影响,设计了在线调整算法自适应调节PID控制增益,并对其工作机理与参数设计原则进行研究;然后设计干扰补偿回路和主动减载回路以减小内外扰动、弹性振动和风载荷影响;最后在弹性振动、风干扰和参数不确定性等因素同时作用的状态下进行仿真分析,验证了自适应增广控制系统能够有效应对运载火箭主动段复杂飞行环境的影响,大幅度提升综合控制性能,具有理论研究意义与工程应用价值。

In order to solve the incompatibility between a traditional PID controllers and the high-quality control requirements from launch vehicles in ascent phase under the impact of complex environment,large uncertain disturbance,elastic vibration and so on,the adaptive augmenting control(AAC) is investigated. Firstly,a nominal PID controller integrated with a digital filter based on particle swarm optimization(PSO) is developed to control the rigid body and suppress the elastic vibration. Then,as a solution to the control problem originating from the large-scale disturbance,uncertainty and additional oscillation caused by the switched-filter,an adaptive gain adjustment algorithm is designed,of which the working and designing principle is investigated as well. For the improvement of the controller performance,a disturbance compensation loop and an active load-relief loop are introduced to further reduce the influence of the internalexternal perturbation,elastic vibration and wind-load. Finally,a simulation is carried out under the condition where all the above mentioned disturbances exist. The simulation results indicate that the flight performance is significantly improved with the proposed control system,which demonstrates that the controller is worthy of theoretical research and engineering application.