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| 1 | Controllability of an underactuated spacecraft with one thruster under disturbance显示文摘For an underactuated spacecraft using only one thruster,the attitude controllability with respect to the orbit frame is studied in the presence of periodical oscillation disturbance,which provides a preconditional guide on designing control law for underactuated attitude control system.Firstly,attitude dynamic model was established for an underactuated spacecraft,and attitude motion was described using the special orthogonal group(SO(3)).Secondly,Liouville theorem was used to confirm that the flow generated by the drift vector of the underactuated attitude control system is volume-preserving.Furthermore,according to Poincare''s recurrence theorem,we draw conclusions that this drift field is weakly positively poisson stable(WPPS).Thirdly,the sufficient and necessary condition of controllability was obtained on the basis of lie algebra rank condition(LARC).Finally,the controllable conditions were analyzed and simulated in different cases of inertia matrix with the installed position of thruster. | Dong-Xia Wang Ying-Hong Jia Lei Jin Hai-Chao Gui Shi-Jie Xu | 2012 | Acta Mechanica Sinica2012，28，3： | 6 |
| 2 | Underactuated spacecraft angular velocity stabilization and three-axis attitude stabilization using two single gimbal control moment gyros显示文摘为当致动器被调查,使用二个仅仅单个万向节控制时刻旋转罗盘(SGCMG ) 的一只 underactuated 太空船的尖速度稳定控制和态度稳定控制。首先, underactuated 太空船的动态模型被建立,有二 SGCMG 的不同配置的奇特被分析。在二 SGCMG 的万向节轴在任何方向被安装的假设下面,并且全部的系统尖动量不是零,经由 Lyapunov 方法的一条州的反馈控制法律被设计到 asymptotically 全球性稳定太空船的尖速度。在二 SGCMG 的万向节轴同轴地被安装的假设下面,三位校长的任何人太空船惯性削减,并且尖动量是的全部的系统零,一条不连续的州的反馈控制法律被设计关于惯性的框架稳定太空船的三轴的态度。而且,为上述二个控制问题的 SGCMG 的奇特逃跑也被学习。模拟结果表明控制法律的有效性。关键词单个万向节控制时刻旋转罗盘 - Underactuated 太空船 - 尖速度稳定 - 三轴的态度稳定 - | Lei Jin Shijie Xu | 2010 | Acta Mechanica Sinica2010，26，2： | 6 |
| 3 | Birkhoff系统积分的新方法(英文)显示文摘将Vujanovi提出的用于积分完整非保守系统动力学方程的梯度法思想移植到Birkhoff系统,给出了Birk-hoff系统积分的一种新方法.首先,列写出Birkhoff系统的运动微分方程;其次,将2n个Birkhoff变量分成2部分,并假设其中一部分变量是其余变量及时间的函数,由此建立拟线性的基本偏微分方程组;如果求出此基本偏微分方程的完全解,则问题的解由一组代数方程给出.该方法具有灵活性,对于具体问题可选Birkhoff变量中任意n个变量作为余下n个变量和时间的函数,其主要困难在于求基本偏微分方程的完全解.一旦求出完全解,就可以不用进一步积分而求得系统的运动.最后,举例说明结果的应用. | 张毅 | 2011 | Journal of Southeast University(English Edition)2011，27，2： | 1 |
| 4 | Attitude control of a rigid spacecraft with one variable-speed control moment gyro显示文摘Nonlinear controllability and attitude stabilization are studied for the underactuated nonholonomic dynamics of a rigid spacecraft with one variable-speed control moment gyro(VSCMG), which supplies only two internal torques.Nonlinear controllability theory is used to show that the dynamics are locally controllable from the equilibrium point and thus can be asymptotically stabilized to the equilibrium point via time-invariant piecewise continuous feedback laws or time-periodic continuous feedback laws. Specifically,when the total angular momentum of the spacecraft-VSCMG system is zero, any orientation can be a controllable equilibrium attitude. In this case, the attitude stabilization problem is addressed by designing a kinematic stabilizing law, which is implemented through a nonlinear proportional and derivative controller, using the generalized dynamic inverse(GDI)method. The steady-state instability inherent in the GDI controller is elegantly avoided by appropriately choosing control gains. In order to obtain the command gimbal rate and wheel acceleration from control torques, a simple steering logic is constructed to accommodate the requirements of attitude stabilization and singularity avoidance of the VSCMG. Illustrative numerical examples verify the efcacy of the proposed control strategy. | Hai-Chao Gui Lei Jin Shi-Jie Xu | 2013 | Acta Mechanica Sinica2013，29，5： | 0 |
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