为了从比力观测值中分离出所需要的导航定位信息，需要对惯导系统进行重力补偿。
So gravity compensation is necessary to separate the carrier acceleration and the gravitational acceleration.
本文给出了导弹与目标的相对运动方程，并推倒出选取比例系数和过重力补偿系数所依据的公式。
This paper offers relative movement equation of missile and target, deducing a formula that is a basis of picking out proportional coefficient and gravity over compensation coefficient.
因而研究新的重力补偿方案，提高惯性导航定位精度，对于扩大惯导系统的应用领域有极大的意义。
To improve the accuracy of INS, a new gravity compensation method should be studied. It is significative to expand the application of INS.
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