Selection and trajectory design to mission secondary targets
Selection and trajectory design to mission secondary targets
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DOI：
10.1007/s10569-016-9724-x
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发表时间：
2016-09
影响因子：
1.6
通讯作者：
Bruno Victorino Sarli;Y. Kawakatsu
中科院分区：
文献类型：
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作者：
Bruno Victorino Sarli;Y. Kawakatsu
最近，由于采用了新的轨道设计技术和使用了小推力推进系统，飞行任务的效率提高了，推进剂也更便宜了。作为增加使命价值和科学回报的一种方式，通常在转移轨道上增加靠近主轨道的次要目标，并对其进行微小的改变。由于小行星数量众多、重要性高且易于飞越，因此通常将其用作此类目标。这项工作使用Primer Vector理论来定义最小燃料消耗问题的推力方向和大小。小行星中途飞越的小推力轨道设计不仅对小推力问题的解决具有挑战性，而且在目标及其飞越点的选择方面也具有挑战性。目前已查明700 000多个小型物体，这产生了大量可能的飞越点。这项工作使用可达性，参考轨道和线性理论的组合来选择合适的候选人，大大减少了模拟时间，稍后将被包含在主轨道中并进行优化。使用上述选择过程和优化的两个测试用例，添加和设计一个二次飞越的使命与3200 Phaethon飞越和25143 Itokawa会合的主要目标。
Recently, with new trajectory design techniques and use of low-thrust propulsion systems, missions have become more efficient and cheaper with respect to propellant. As a way to increase the mission’s value and scientific return, secondary targets close to the main trajectory are often added with a small change in the transfer trajectory. As a result of their large number, importance and facility to perform a flyby, asteroids are commonly used as such targets. This work uses the Primer Vector theory to define the direction and magnitude of the thrust for a minimum fuel consumption problem. The design of a low-thrust trajectory with a midcourse asteroid flyby is not only challenging for the low-thrust problem solution, but also with respect to the selection of a target and its flyby point. Currently more than 700,000 minor bodies have been identified, which generates a very large number of possible flyby points. This work uses a combination of reachability, reference orbit, and linear theory to select appropriate candidates, drastically reducing the simulation time, to be later included in the main trajectory and optimized. Two test cases are presented using the aforementioned selection process and optimization to add and design a secondary flyby to a mission with the primary objective of 3200 Phaethon flyby and 25143 Itokawa rendezvous.