摘要
航天器动力学模型的精确建立,对于成功完成空间任务来说必不可少,而单独考虑轨道或姿态的模型无法满足任务高精度要求,因此从相对轨道动力学方程和修正罗德里格斯参数(MRP)表示的姿态运动学方程出发,建立了航天器六自由度的相对耦合动力学方程。为了给出姿轨运动的基准,分别设计了航天器理想姿态和椭圆加指数接近轨道。针对航天器参数不确定问题设计了自适应同步控制律,并通过Lyapunov直接法证明闭环系统的全局渐近稳定性。从仿真结果可以看出,自适应同步控制算法能使轨道和姿态误差逐步趋于零。
Sections 1,2 and 3 explain is an improvement over previous ones. the adaptive synchronization control mentioned in the title, which we believe Their core consists of： ＂Precise dynamic model of spacecraft is essential for space missions to be completed successfully. Nevertheless, the independent orbit or attitude dynamic models can not meet the requirements of high precision tasks. We developed a 6-DOF relative coupling dynamic model based upon the relative motion dynamics equations and attitude kinematics equations described by MRP （Modified Rodrigues Parameters）. In order to give the benchmarks of attitude and orbit motion respectively, the ideal spacecraft attitude and the elliptical plus exponent track orbit were given. Nonlinear synchronization control law was designed for the uncertainties of spacecraft parameters, whose close-loop system was proved to be globally asymptotically stable by Lyapunov direct method. ＂ Finally, the simulation results, presented in Figs. 3 through 5, and their analysis illustrate preliminarily that the nonlinear synchronization control algorithm can robustly drive the orbit errors and attitude ones to converge to zero.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2012年第1期32-37,共6页
Journal of Northwestern Polytechnical University
关键词
姿轨耦合模型
自适应同步控制
类拉格朗日方程
修正罗德里格斯参数
algorithms, analysis, control, design , dynamics, methods, models, orbits, Runge-Kutta methods flight, spacecraft, stability, synchronization, equations of motion, errors, kinematics, Lyapunov , robustness （control systems）, simulation, space tracking （ position）, uncertain systems, velocity
attitude and orbital coupling model, Modified Rodrigues Parameters（MRP）, quasi-Lagrange equation
