刚体航天器最短时间姿态调整研究

Research on Time-Optimal Attitude Maneuvers for a Rigid-Body Spacecraft

在最小值原理的基础上,研究了完全刚体最短时间机动问题。由最小值原理推导出问题解的必要条件,采用修正开关时间优化算法,由遗传算法确定无耦合项时的开关特性;基于同伦算法的思想,引入松弛参数,采用模拟退火法确定开关点,对传统模拟退火法进行了改进。仿真结果表明,该方法简单可行,对实际工程有一定的参考价值。

On the basis of minimum value principles, a research for reorienting an inertially symmetric spacecraft with time cost function from an initial state of rest to a final state of rest is deduced. And the solution to it is stated below: firstly, the essential condition for solving the problem is inducted with the minimum value principle. The necessary conditions for optimality yield a two point boundary-value problem (TPBVP), which, when solved, gives the control history that minimizes time performance index. Secondly, by the use ofadjusting the switch on/off time, the genetic algorithm, which is a new robust method, is optimized to determine the switch features without the gyroscopic coupling. Based on the idea of the homotopy, the relaxation parameters are introduced, and the switch point is figured out with simulated annealing. There is improvement upon the traditional SA in this research. Computer simulation results using a rigid-body show that the new method is feasible and efficient. A practical method of computing approximate solutions to the time-optimal control switch times for rigid body reorientation has been developed.