| With the rapid development of space technology, Satellite system is showing the trend of large scale, low rigidity and flexibility, which makes the problem of the satellite attitude dynamics and control more and more complex. How to ensure the performance of the satellite control system through the simulation has become an issue in aerospace technology. This thesis studies on the problems of satellite attitude control, and its simulation method on ground.Firstly, the current development of attitude dynamic modeling and control was summarized, and the research results of simulation system on ground were analyzed. Based on the description form of quaternion and Euler angle, the attitude kinematic model of satellite is given. With Lagrange method, the attitude dynamic model of flexible-satellite with two solar panels is established.Secondly, according to the flexible satellite attitude dynamic model established, the problem of attitude control is studied. A PID controller is designed and simulated, which has achieved good performance. Based on this, taking the disturbance of flexible accessories such as solar panels for attitude control into consideration, a sliding mode controller is established. The simulation results prove that it has strong robustness as well as good performance. What’s more, considering the existence of sliding mode chattering, a fuzzy sliding mode controller is designed. The simulation results show that it can effectively reduce the control torque fluctuation.Thirdly, this paper studies the full-physical simulation system on ground, whose core component is the 3-axis air bearing table. The hardware and software platform as well as control algorithms of the attitude control simulation-in-loop system are designed in details. Based on this, simulation tests such as large angle maneuvering and attitude stability control of the instrument platform was designed and completed. Through these tests, not only the good performance of the hardware and software platform designed for the full-physical simulation system on ground, but also the effectiveness of control algorithms designed was verified.Finally, this thesis studies the quantitative analysis method of the full-physical simulation system. Based on the similarity theory, the five function modules of the satellite attitude control system were analyzed. Several simulation tests are designed to calculate and analyze the credibility of the full-physical simulation system, through comparing the simulation test data and the real on-orbit satellite data. |
