| 1. | Controller tuning and testing including stability and robustness analysis . 4 . test results to the implementation of mpc for spacecraft control
对控制器的调试和测试(包括对控制器的稳定性和鲁棒性的分析) 。 |
| 2. | This thesis studies the spacecraft control using nonlinear model predictive control and computer simulations are applied in it . the main results fall into two main areas . 1
本文运用非线性模型预测控制理论对空间飞行器位置和姿态的控制进行了系统的分析、研究和计算机仿真，在以下两个方面取得显著成效： 1 |
| 3. | This dissertation mainly studies information fusion estimation theory and its application to spacecraft control . the major researching contents of the dissertation are summarized as follows : 1
本论文就多传感器系统信息融合估计理论及其在航天器控制中的应用进行了深入研究，所作的主要研究工作有以下六个方面： 1 |
| 4. | This dissertation mainly studies information fusion estimation theory and its application to spacecraft control ; automatic diagnosis and system recovery ; strap - down attitude algorithm of fiber optic gyro and its error propagation
由于惯性系统正由框架式平台系统逐步向捷联系统过渡,因此本文还对基于光纤陀螺的捷联姿态更新算法进行了研究。 |
| 5. | The current control approaches are based on frequency domain methods such as pid control which assumes linear time invariant system dynamics . the advantages of these approaches are simplicity and ease of stability and robustness analysis . however , the decrease in performanc e and poor efficiency translates to additional payload and cannot meet the demand of current spacecraft control
当前飞行器主要的控制方法是基于近似时不变线性系统的频域分析法(如pid控制) ，这种方法的优点是简单且易于稳定性和鲁棒性分析，但它所达到的低性能和低效率却转化成了飞行器控制过程的附加载荷，还远不够满足当前飞行器控制的要求。 |
| 6. | This thesis presents the feasibility of nonlinear model predictive control implemented in spacecraft control and the optimality of increasing the control precision and decreasing the fuels expenditure . and the discussions are then focused on the simulation of spacecraft control using function - space model predictive control algorithm as mentioned below : 1
本文的主要研究工作是探讨非线性模型预测控制( nmpc )应用于空间飞行器自适应控制的可行性及对提高控制精度和减少燃料使用方面的优越性，同时利用函数空间模型预测控制算法( f - mpc )对空间飞行器的位置和姿态控制进行仿真，具体内容如下：一 |
| 7. | About the large deformation description , a multi - floating coordinate system is adopted . it can effectively reduce the error of discretization . this paper deals with the design of restrained variable structure control in the way of phase plane analyse , which is concise and avoids complex mathematical descriptions . a new method is promoted for flexible spacecraft control by describing flexible spacecraft dynamics equations as t - s fuzzy model and designing a pdc fuzzy controller
将挠性航天器姿态动力学方程描述为t - s模糊模型为挠性航天器控制提供了新思路;仿真结果表明,基于t - s模型的pdc模糊控制器能满足挠性航天器大角度姿态机动的精度要求,并能有效抑制帆板振动,具有一定的智能性。 |
