| The method of ground testing for satellites’mass property parameters has some drawbacks such as high costs, low accuracy, and the inability for on-orbit changes of the parameters. On-orbit identification can solve the problems. The existing methods of on-orbit identification of satellites usually treat satellite as a rigid body, without considering the effects of the vibration of satellites’flexible appendages. With the flexible appendages becoming larger, the influence of the appendages’vibration on the identification is more distinguished. Therefore, the research of on-orbit identification of mass property parameters for satellites with flexible appendages is highly valuable, which not only can accurately give the mass property parameters of the satellites, but also provide a reference for satellites control system’s designing and adjusting.For the study of on-orbit identification of mass property parameters for satellites with flexible appendages, the main content of this paper includes the following sections:(1) The study of on-orbit identification of rigid body satellites’mass property parameters. It’s the foundation of identification of mass property parameters for satellites with flexible appendages. Using recursive least square algorithm and multiple concurrent recursive least square algorithms, single or multiple mass property parameters of rigid body satellites can be identified.(2) When the attitude angular velocity is low, the vibration of satellites’flexible appendages can affect the identification of mass property parameters, and the recursive algorithm of on-orbit identification of mass property parameters for satellites with flexible appendages is proposed. To begin with, based on the dynamic model of satellites with flexible appendages, the least square description of moment of inertia for parameters identification is proposed. Then, combined with Kalman filter algorithm for flexible appendages’vibration modal estimation, a concurrent recursive algorithm for identification of moments of inertia for satellites with flexible appendages is proposed in this paper. Finally, the simulation examples demonstrate the influence of inertia identification of the vibration of satellites’flexible appendages, and the recursive algorithm proposed in this paper is effective for identification of moments of inertia for satellites with flexible appendages.(3) When the attitude angular velocity is high, the algorithm of on-orbit identification of mass property parameters for satellites with flexible appendages is proposed. When the attitude angular velocity is high, the dynamic model of the satellite has nonlinear parts. The recursive algorithm proposed in the last paragraph is improper. Considering this situation, the identification algorithm based on extended Kalman filter is proposed. The simulation examples demonstrate the effectiveness of the algorithm based on extended Kalman filter. |
