Abstract:For the problem of not being able to calculate the error coefficient directly by using the remote outlier equation due to the lack of high-precision external measurement equipment when performing the continuous test of ground closed orbit and the seriousness of the complex covariance of the environment function matrix when separating, a method of error coefficient separation of the guidance tool based on the environment function of the relative position is proposed, in which the characteristic points in the trajectory can be extracted for the separation of error coefficients. First, the navigation solution is based on the differential equations in the earth coordinate system of the launch point. Second, the characteristic points in the navigation solution trajectory are extracted to establish the relative position domain environment function. Finally, the error coefficients are then estimated by combining the correlation and significance methods, and the error coefficients obtained from the separation are substituted into the accelerometer output for compensation, and the position error is reduced from 27m to about 1.7m, which is a good compensation effect. The method proposed in this paper can effectively separate the error coefficients of inertial guidance tools and has a certain application value.