摘要
针对具有过程约束和终端状态约束的大气层内空天飞行器上升段制导问题,给出了一种基于伪谱法的固定采样非线性实时最优制导算法,通过连续在线计算开环最优控制的方式提供闭环反馈。针对闭环最优制导过程中首次轨迹优化时的初始猜测问题,提出了采用运载火箭真空段飞行最优上升轨迹作为大气层内最优上升轨迹的初始猜测,改进了初次轨迹优化的初始猜测过程中,直接采用伪谱法进行计算导致的计算速度过慢的缺点。仿真结果表明,该实时最优制导算法能有效地抑制飞行过程中不确定性和扰动的影响。
For the optimal ascent guidance problems under process constraints and terminal states constraints,a nonlinear real-time optimal guidance algorithm is proposed. A closed-loop feedback method is designed by successively generating real-time open-loop optimal controls. Then,combining the vacuum rapid initial guess trajectory from the optimal ascent trajectory of rocket,the atmosphere optimal ascent trajectory is found. Using this method,the computing time of trajectory optimization is reduced obviously,and nonlinear optimal control problems with constraints are solved on-line by using GPOPS. Simulation results show strong robustness and high precision.
出处
《战术导弹技术》
北大核心
2017年第4期57-65,共9页
Tactical Missile Technology
关键词
上升段
非线性
闭环制导
伪谱法
初始猜测
空天飞行器
ascent
nonlinear
closed-loop guidance
pseudo-spectral method
initial guess
aerospace vehicle
