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为减少探月返回飞船再入数值预测校正制导方法在跳跃段倾侧角的偏转频率、实现过载的有效抑制,采用搜索跳跃段的倾侧角偏转能量点和末段阻力加速度反馈补偿的方法,提出了改进的数值预测校正制导方法.首先,用割线法搜索倾侧角偏转能量点,使得飞船在跳跃段只进行一次偏转即可实现落点精度要求;然后,根据指数大气假设,得到阻力加速度的导数,并根据过载约束定义参考阻力加速度;最后,采用阻力加速度及其导数与参考阻力加速度及其导数的误差对倾侧角的大小进行反馈补偿,抑制末段轨迹的过载.实验结果表明,该方法倾侧角偏转次数少,过载抑制能力强,鲁棒性好,能够有效解决现有方法存在的跳跃段倾侧角偏转频率高,末段过载抑制能力差的问题.
In order to reduce the deflection frequency at the skip angle of the jump segment in order to reduce the spacecraft reentry numerical predictive correction guidance method and effectively suppress the overload, the method of using the tilting angle deflection energy point of the search jump segment and the final resistance acceleration feedback compensation is proposed An improved guidance method of numerical predictive correction is proposed.Firstly, the tangent method is used to search for the tilting energy point of the tilting angle, so that the spacecraft can only achieve the precision of falling point by only one deflection in the jumping section. Then, the derivative of the drag acceleration is obtained according to the exponential atmospheric assumption , And define the reference drag acceleration according to the overload constraint. Finally, the error of the drag acceleration, its derivative and the reference drag acceleration and its derivative are used to compensate the roll angle and suppress the overload of the last track. The experimental results show that this method tilts Less angle deflection, strong overload restraint ability and good robustness, and can effectively solve the problems that the prior art method has high deflection frequency of the dip angle of the jumping segment and poor suppression ability of the last segment.