Simulation of Spacecraft Attitude and Orbit Dynamics

摘要

In this paper, the simulation model of satellite attitude and orbit dynamics is discussed. The satellite attitude model has been represented in term of a quaternion and a ordinary differential equation is used to describe the satellite orbital motion. The different actuators and sensors have been modeled with suitable faults and failures. The simulation model enables us to consider the satellite motion under different environmental perturbations (for example aerodynamic drag, external celestial body etc.) and failure in actuators and sensors. The simulation model is utilized in the development of attitude and orbit control algorithms or fault detection, isolation and recovery (FDIR) technologies. Simulation results are also given.