On-Orbit Identification of Inertia Tensor of Spacecraft with Structural Mutation
Aiming at unexpected the sudden change in inertia parameters of spacecraft on-orbit servicing,real-time identification methods of inertial parameters based on on-orbit attitude and control information are proposed,and recursive least squares(RLS)and extended Kalman filter(EKF)identification algorithms are designed.Adaptive forgetting factors are introduced into the RLS algorithm,which assign weights of prior data and current data during each iteration process to ensure the identification value tracking in time.In the EKF algorithm,the influence of parameter variation on the prior prediction covariance is defined,and it is substituted to update the prediction covariance matrix to solve the mutation of inertia parameters.Under consideration of the mutation in inertia parameters,the simulation results show that the identification accuracy of RLS and EKF can reach 1.5％and 1％,and the identification time is better than 30 s and 40 s respectively;In the scenario of time-varying inertia,both methods can achieve on-orbit identification of iner-tia parameters,and the identification accuracy fulfills the requirements of the attitude control system.
Spacecraft with structural mutationAdaptive recursive least squareExtended Kalman filterOn-orbit identification
NETL
NSTL
万方数据
