科研之友
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摘要
Delivering an orbiter to a planetary moon such as Europa or Titan requires an excessive amount of fuel if the trajectory is not carefully and cleverly planned. V-infinity leveraging maneuvers are an effective means to reduce total Delta-V requirements to achieve orbit about a planetary satellite. This work characterizes optimal sequences of flybys and leveraging maneuvers with the aid of tools to construct, map, and analyze these sequences and compare them with a theoretical minimum. Numerical results show that the optimal location for performing V-infinity reduction maneuvers is not necessarily at apoapsis, due to targeting constraints. By plotting total Delta-V versus time-of-flight for tens of thousands of generated sequences, a Pareto front is created of the most efficient sequences for each given flight time. An infinite series of flybys and leveraging maneuvers (theoretical minimum) results in a Delta-V savings of over 70% when compared with a direct burn during flyby. While infinite missions are not possible, it is feasible to reduce the total Delta-V by 50% with only a modest increase in flight time. Increasing the mission duration further does not result in significant reductions.
- 出版日期2011-10
