Multi-Objective Hybrid Optimal Control for Interplanetary Mission Planning

Englander, Jacob; Vavrina, Matthew; Ghosh, Alexander

Preliminary design of low-thrust interplanetary missions is a highly complex process. The mission designer must choose discrete parameters such as the number of flybys, the bodies at which those flybys are performed and in some cases the final destination. In addition, a time-history of control variables must be chosen which defines the trajectory. There are often many thousands, if not millions, of possible trajectories to be evaluated. The customer who commissions a trajectory design is not usually interested in a point solution, but rather the exploration of the trade space of trajectories between several different objective functions. This can be a very expensive process in terms of the number of human analyst hours required. An automated approach is therefore very diserable. This work presents such as an approach by posing the mission design problem as a multi-objective hybrid optimal control problem. The method is demonstrated on a hypothetical mission to the main asteroid belt.

Document ID

20160000217

Acquisition Source

Goddard Space Flight Center

Document Type

Presentation

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Date Acquired

January 5, 2016

Publication Date

January 11, 2015

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Report/Patent Number

Meeting Information

Meeting: AAS/AIAA Space Flight Mechanics

Location: Williamsburg, VA

Country: United States

Start Date: January 11, 2015

End Date: January 15, 2015

Sponsors: American Astronautical Society, American Inst. of Aeronautics and Astronautics

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Public

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