基于Levenberg-Marquardt法的飞行器主动段轨道参数估计

The Orbital Parametric Estimation of the Propulsion Branch of Flying Vehicles Based on the Levenberg—Marquardt Method

空间飞行器，如弹道式导弹，侦察卫星等，有特定的轨道参数，怎样准确估计出其轨道参数，对于维护国家安全有重要意义。此文以2012年全国研究生数学建模竞赛为依托，针对飞行器轨道主动段的运动模型，运用Levenberg-Marquardt非线性最小二乘法，实现了对该二阶微分方程组相关参数的准确估计，仿真结果显示拟合残差在10m数量级左右。

Space vehicles, such as ballistic missiles, reconnaissance satellites, etc. , have specific orbital parameters.How to estimate these orbital parameters precisely is of great significance to safeguard national security. In this paper which is based on the 2012 GMCM,by using the nonlinear least squares method of Levenberg-Marquardt algorithm to analyze the movement model of the orbital propulsion branch of flying vehicles, an accurate estimation for the unknown parameters of the second order differential equations is realized. Simulation results show that the fitting effects are ideal.