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研究一种以最佳Q制导为基础的闭合回路控制逻辑.这种制导系统控制卫星运载火箭沿着二维或三维轨道飞行,以将有效载荷送入指定的圆周轨道.改进后的Q制导算法使用所需的最佳速度矢量,使火箭从现有位置经两次推进加速转移到最终轨道上所需要的总冲减少到最小.所需的速度矢量可以看作是,在经过第一次推进加速后火箭在假想的转移轨道上的瞬时速度.针对这种最佳转移轨道,推导出一种简单明了的Q矩阵表达法,并概要论述大周期和小周期制导算法及形成操纵指令的原理.
A closed-loop control logic based on the best Q-guidance is studied. This guidance system controls the satellite launch vehicle to fly along a two-dimensional or three-dimensional orbit to send payloads to a given orbit. The improved Q-guidance algorithm Use the required optimal velocity vector to minimize the total effort required to accelerate the rocket transfer from the existing position to the final orbit by two propulsions.The required velocity vector can be considered as, after the first propulsion The instantaneous velocity of the rocket in the imaginary transfer orbit after the acceleration is accelerated, a simple and straightforward Q-matrix method is deduced for this optimal transfer orbit, and the principle of large period and small period guidance and the formation of manipulation instructions are briefly discussed.