速度匹配加机动辅助的滚转弹滚转角空中对准法

针对卫星与惯性速度匹配法对滚转角的空中对准精度不高这一问题，提出一种卫星与惯性速度匹配加机动辅助的方法。在卫星与惯性组合制导方式下，以可观测性分析为基础，机动辅助采取纵向比例导引加重力补偿制导律形式，结合卡尔曼滤波完成滚转角的空中对准，并分析机动辅助策略在不同导航比、重力补偿系数下对滚转角对准效果的影响，以及弹体名义转速拉偏、惯性组件误差拉偏对机动辅助策略的影响。仿真结果表明：在考虑卫星定速及惯性组件误差情况下，该方法能够在全弹道内实现滚转角的精对准,误差在2°以内，收敛时间10 s；可通过调节重力补偿系数改变对准的速度、精度，导航比用来保证制导稳定。卫星与惯性速度匹配加机动辅助的方法相比于卫星与惯性速度匹配法，对准效果更好；在弹体名义转速以及惯性组件误差存在拉偏情况下，对准效果受影响较小，抗干扰性较强。

An Air Alignment Method for the Roll Angle of Rolling Missiles with Velocity Matching and Maneuvering Assistance

A method of satellite/inertial velocity matching and maneuvering assistance is proposed to solve the problem of low accuracy of aligning the roll angle by a satellite/inertial velocity matching method. In the satellite/inertial integrated guidance mode, on the basis of observability analysis, a longitudinal proportional guidance law with gravity compensation is used in the maneuvering assistance, and Kalman filter is used to complete the air alignment of roll angle. The influences of maneuvering assistance strategy on the aligning effect of roll angle are analyzed in the case of different navigation ratios and gravity compensation coefficients, and the influences of nominal rotating speed deviation and inertial system error deviation on maneuvering assistance strategy are also analyzed. Simulated results show that the proposed method can be used to realize the precision alignment of roll angle in the whole trajectory with the error of less than 2° and the convergence time of 10 s under the condition of satellite and inertial system errors, and the speed and precision of alignment can be changed by adjusting the gravity compensation coefficient. The navigation ratio is used to ensure the stability of guidance loop. Moreover, under the condition that the deviations exist in the nominal rotating speed and the inertial system errors, the alignment effect is less affected and the anti-interference ability is stronger.