On-orbit identification of flexible parameters of spacecraft

Abstract

This paper studies the on-orbit identification of flexible parameters of spacecraft using a typical spacecraft as research object. First, the coupled dynamic equation of the system is established with the Lagrange method and the model order of the solar array is reduced using the inertia complete criterion. Then, the particle swarm optimization is adopted to determine the optimal positions of acceleration sensors on the solar array. Finally, the observer/Kalman filter identification and eigensystem realization algorithm are applied to identify the flexible parameters of the system. In the simulations, three types of external excitations, including white noise, sine and impulse, are considered as system input, respectively. Simulation results indicate that the presented method in this paper is effective in identifying the flexible parameters of the spacecraft.