摘要
研究了时间最优姿态机动的控制器参数优化设计问题。基于一类采用拟欧拉角和绝对角速度为反馈信号的姿态机动控制模型,以其控制器参数为优化变量,机动时间为优化指标,建立了时间最优的姿态机动控制器参数优化模型。采用一类全局收敛的连续模拟退火算法完成了控制器参数的优化设计。仿真结果表明:(1)控制器参数优化可以有效地缩减姿态机动时间,经过优化的控制器参数减少了16.5%的机动时间;(2)模拟退火算法保证了控制器参数优化的全局最优性;(3)机动时间的减小是以增大最大控制力矩为代价的。
The optimization design problem of controller parameters of time-optimal attitude maneuvers with continuous moment is investigated in this paper. The parameters optimization design model of the time-optimal attitude maneuver controller is proposed, which is based on a control model with the quasi Euler angle and absolute angular velocity as the feedback. The controller parameters are chosen as the optimization variables, and the maneuver time is chosen as the optimization objective function .A continuous simulated annealing algorithm with global convergence ability is applied to solve this controller parameters optimization design problem. The simulation results show that: (1) the optimization of the controller parameter can effectively reduce the attitude maneuver time, and a 16.4% reduction is got ; (2) the simulated annealing algorithm guarantees to solve the controller parameters with global solutions; (3) the descent of maneuver time is at the price of the ascent of the maximal control moment.
出处
《弹箭与制导学报》
CSCD
北大核心
2004年第4期1-3,7,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
"863"课题(2002AA001006)
关键词
姿态机动控制器
时间最优控制
模拟退火算法
飞行器
角速度
attitude maneuver
time-optimal control
optimization design of controller parameters
simulated annealing
