Attitude Dynamics And Control Simulation For RVD Target-Spacecraft

Rendezvous and docking technology is essential in space-assembly, space-succor, outer space-exploration and so on, and is also a key technology of the second step of Chinese manned spaceflight. Building rendezvous and docking simulation system is the important way for studying rendezvous and docking technology.By employing the development of the RVD simulation system as the research background, the main work of this dissertation is to study the attitude controller design problem, to build the all-purpose simulation framework of the spacecraft attitude dynamics and control and to develop a RVD target-spacecraft simulation system. The main achievements obtained in this dissertation are as follows.1. The model of spacecraft attitude dynamics and the attitude control technology are generalized. The simple rigid body dynamics model, multi-body dynamics model and the related calculation models for RVD target-spacecraft are provided.2. The attitude controller design problems for spacecrafts with two types of actors including thrusters and reaction-wheels are studied. The phase-plane control parameters are designed for thruster actors and the practicability of the phase-plane controller is proved by the simulation results. The influence of the phase-plane controller parameters on attitude control is analyzed. Then the three PD wheel controllers are compared which are designed by three different methods: parameter estimation, parameter optimization and design by Matlab/Simulink NCD blocks.3. The optimal attitude maneuver problems are studied. Based on the existed control models, two optimization design problems of controller parameters are proposed, the one is time-optimal attitude maneuvers with continuous moment and the other is optimal on-off times attitude maneuvers with switch moment. And a simulated annealing algorithm is applied to solve this controller parameters optimization design problems. The results show that the optimal controllers have more advantages because the former optimal controller can effectively reduce the attitude maneuver time and the latter can greatly reduce the on-off times.4. Guided by object-oriented methodology, an all-purpose object-oriented simulation framework for spacecraft attitude dynamics and control is designed. The requirement of this framework is analyzed and the all-purpose simulation class library is built. Besides the object model, dynamic model and functional model of the framework are built.5. The prototype of RVD target-spacecraft simulation system is built up as ai application example of the object-oriented spacecraft attitude simulation framework. Th 6-DOF (6 Dimension-Of-Freedom) target-spacecraft simulation is executed by using th prototype system. Besides, the simulation task of attitude stabilization control and attitud maneuver control are completed respectively.The dissertation is an essential part of the enormous Chinese RVD ground simulatio system. And the results obtained in this dissertation can be used for the studies on attitud dynamics and control of other types of spacecrafts.