椭圆参考轨道的卫星编队队形设计比圆参考轨道要困难得多,有时很难找到符合队形要求的初始条件。基于L aw den方程,给出了利用遗传算法设计椭圆参考轨道情形下的星下点圆形编队设计方法。由于参考轨道为大偏心率椭圆轨道时不存在圆形星下点队形,只讨论了参考轨道为小偏心率椭圆的情形。与对圆参考轨道的C-W方程初始条件进行修正的方法相比,该方法有更高的设计精度。最后使用脉冲推力模型求解了椭圆参考轨道编队的能量最省队形重构的轨迹规划问题。结果表明,遗传算法可以很好地应用于小偏心率参考轨道编队的队形和重构轨迹设计中。
The paper investigates the relative motion around the planetary displaced orbit. Several kinds of displaced orbits for geocentric and martian cases were discussed. First, the relative motion was linearized around the displaced orbits. Then, two semi-natural control laws were investigated for each kind of orbit and the stable regions were obtained for each case. One of the two control laws is the passive control law that is very attractive for engineering practice. However, the two control laws are not very suitable for the Martian mission. Another special semi-natural control law is designed based on the requirement of the Martian mission. The results show that large stable regions exist for the control law.
形成在太阳地球的一条光圈轨道附近飞的重构限制了三个身体系统与推动演习被调查。为短时间重构，二推动的演习与分析、数字的方法并且开始结束被调查()方法被证明是一精力最佳二推动的所有( TI )之一重构，和精力消费独立于主要太空船的位置，并且与重构时间减少。然后，基因算法被采用优化精力消费。结果证明最佳的精力与起始、最后的轨道之间的半径差别增加，并且与重构时间减少。
A robust attitude tracking control scheme for spacecraft formation flying is presented.The leader spacecraft with a rapid mobile antenna and a camera is mod- eled.While the camera is tracking the ground target,the antenna is tracking the follower spacecraft.By an angular velocity constraint and an angular constraint,two methods are proposed to compute the reference attitude profiles of the camera and antenna,re- spectively.To simplify the control design problem,this paper first derives the desired inverse system (DIS),which can convert the attitude tracking problem of 3D space into the regulator problem.Based on DIS and sliding mode control (SMC),a robust attitude tracking controller is developed in the presence of mass parameter uncertainties and ex- ternal disturbance.By Lyapunov stability theory,the closed loop system stability can be achieved.The numerical simulations show that the proposed robust control scheme exhibits significant advantages for the multi-target attitude tracking of a two-spacecraft formation.
