Design of non-cooperative target's safe corridor and optimization of fly-by approach trajectory
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摘要:
为提高空间非合作目标近距离逼近轨迹的安全性，同时对接近时间及所消耗燃料进行优化，针对空间失效自旋非合作目标近距离接近问题，给出了失效卫星动态安全走廊，并以飞越逼近方式抵达走廊入口，进一步提出了飞越逼近轨迹优化方法。首先，在建立失效卫星自旋模型的基础上，规划了安全区与禁飞区，提出了2种安全走廊的选择依据。其次，采用飞越逼近作为近距离接近方式，以节约燃料和缩短逼近时间为目标对两脉冲机动模型进行优化，选择3种优化算法得到接近轨迹。仿真结果表明：安全走廊的选择与卫星失效自旋的形式、外形以及接口位置有关；在飞越逼近两脉冲机动模型的优化问题中，采用Fgoalattain算法进行优化处理更具优越性。
Abstract:In order to improve the safety of non-cooperative target's close-range approach trajectory, and optimize the approach time and fuel consumption at the same time, this paper designs the dynamic safety corridors of uncontrolled rotating satellite for the proximity to rotating non-cooperative target. The fly-by approach is chosen to reach the corridor entrance and the fly-by approach trajectory optimization method is proposed. First, based on the establishment of an uncontrolled rotating satellite spin model, the safety zone and the keep-out-zone are planned, and the basis for selecting two safety corridors is analyzed. Second, the fly-by approach is used as a close-range approach method, and with the goal of saving fuel and shortening the approach time, the two-pulse maneuver model is optimized and three optimization algorithms are selected to obtain the approach trajectory. The simulation results show that the choice of the safe corridor is related to the form, shape and interface position of the uncontrolled satellite spin. In the optimization problem of fly-by approaching two-pulse maneuver model, it is more advantageous to use the fgoalattain algorithm for optimization.
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图 4 本体坐标系与计算坐标系关系图
Figure 4. Relationship between ontology coordinate system and computational coordinate system
图 5 动量矩矢量在轨道坐标系随时间的变化
Figure 5. Change of momentum moment vector in orbit coordinate system with time
图 10 当H方向变化时不同的走廊示意图
Figure 10. Schematic of different corridors when H direction changes
图 15 章动存在时入口在禁飞球上的投影
Figure 15. Projection of entrance to no-fly ball when nutation exists
图 16 三维飞越逼近(有章动)初始位置曲线
Figure 16. Initial position curve of 3D fly-by approach (when nutation exists)
图 17 总冲量与2段转移时间的关系
Figure 17. Relationship between total impulse and two transition time
图 20 三种不同优化算法在三维逼近下的结果
Figure 20. Results of three different optimization algorithms under 3D approach
表 1 Pareto所选解集
Table 1. Pareto selected solution set
维数 Δ v/(m·s-1) T/s t1/s t2/s 二维 0.154 745 1 312.043 1 131.516 180.526 7 三维 0.188 1 273.956 1 092.404 181.552 
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表 2 Fmincon算法优化结果
Table 2. Optimization results of Fmincon algorithm
维数 v/(m·s-1) T/s t1/s t2/s 二维 0.286 852 672 180 三维 0.438 6 1 091.5 911.433 2 180.066 8
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表 3 Fgoalattain算法优化结果
Table 3. Optimization results of Fgoalattain algorithm
维数 Δ v/(m·s-1) T/s t1/s t2/s 二维 0.130 6 1 497.5 1 317.5 180 三维 0.156 5 1 497.5 1 317.5 180
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表 4 优化性能对比
Table 4. Optimized performance comparison
性能指标 Gamultiobj Fmincon Fgoalattain 二维仿真时间/s 14 1 1 三维仿真时间/s 1 390 19 3 二维燃料消耗/(m·s-1) 0.154 745 0.286 0.130 6 三维燃料消耗/(m·s-1) 0.188 0.438 6 0.156 5 二维逼近时间/s 1 312.043 852 1 497.5 三维逼近时间/s 1 273.956 1 091.5 1 497.5
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