航天器近距离交会斜滑制导算法

提出了满足测量视场、最小脉冲间隔、最大脉冲受限等约束的燃料最省的航天器近距离交会多脉冲斜滑制导算法.建立了近距离交会(接近和撤离)多脉冲斜滑制导算法的统一数学模型;提出了理想交会轨道距离和速率的指数函数变化关系,使得算法能够实现任意时间的近距离交会,同时满足接近操作减速和撤离过程加速的任务要求;设计了对数函数映射法进行脉冲寻优.最后通过接近段和撤离段的操作仿真算例进行验证,仿真结果表明,相比最优化方法,对数函数映射法以较小的计算量实现了较好的寻优效果;算法能够以较省的燃料消耗实现轨道面内任意方向、任意时间内满足约束的近距离交会.

Glideslope Guidance Algorithm for Close Range Rendezvous of Spacecraft

The multi-impulse glideslope guidance algorithm for close range rendezvous of spacecraft is presented. The algorithm takes the fuel economy and the constraints of field-of-view of navigation facilities, the minimum interval of impulses, and the value of impulse into consideration. Furthermore, a consolidated model of glideslope algorithm to guide dose range rendezvous (both proximity and departure) is described. By designing the relationship of exponential function between distance and speed of ideal rendezvous trajectory, the algorithm can be applied to any specified rendezvous time, and satisfies the need of decelerating during the proximity operation and accelerating during the departure operation. By defining the logarithmic mapping function, the optimized impulses can be obtained. Finally, several scenarios of the proximity and departure operations are simulated. In some scenarios, compared with the optimization method, the using of logarithmic mapping function can also economize fuel at a cost of low computational complexity. The other scenarios illustrate that the guidance algorithm can ensure a close range rendezvous motion in any direction, at any time with the fuel economy and under the constraints as well.