Identification of Mass Characteristic Parameters for Spacecraft Based on Differential Evolution Algorithm

The accuracy of the spacecraft mass parameters is the important precondition for spacecraft precision attitude and orbit control, differential evolution (DE) algorithm is proposed for this to identify spacecraft mass characteristics. The object function of identification is obtained on the account of the spacecraft dynamics model, respectively using the flywheel and thruster as the acting force. Then, on-orbit spacecraft inertia parameters identification and one-time offline mass characteristic parameters identification are implemented by the DE method. The proposed method does not require the status of the spacecraft rigorously, needs less amount of sampling data, and has faster convergence speed and less time. Results of simulation demonstrate effectiveness of the proposed method.