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1.前言惯性制导系统的主要任务是根据最终速度和到达时间的要求,将运载火箭引向惯性空间内的某个预先确定的瞄准点。瞄准点的位置:对于弹道导弹是在地球表面;对于卫星的发射是在地面上空的某一点;对于拦截任务是在地球卫星的轨道中;或在任务要求所决定的任意点上。通常用控制速度矢量达到目标位置的能力来计算制导系统的精度。误差分析方法是用来定量计算系统的精度并使制导系统的设计最佳化。
I. INTRODUCTION The main task of an inertial guidance system is to direct the launch vehicle to a predetermined aiming point in inertial space, depending on the final speed and arrival time requirements. The location of the aiming point: for the ballistic missile is on the surface of the Earth; the launch of the satellite is at a point above the ground; in the orbit of the Earth satellites for interception missions; or at any point as determined by the mission requirements. The accuracy of the guidance system is usually calculated using the ability to control the speed vector to the target position. The error analysis method is used to quantitatively calculate the system’s accuracy and optimize the design of the guidance system.