TR2012-024

Optimized Three-Body Gravity Assists and Manifold Transfers in End-to-End Lunar Mission Design


    •  Grover, P.; Andersson, C., "Optimized Three-Body Gravity Assists and Manifold Transfers in End-to-End Lunar Mission Design", AAS/AIAA Space Flight Mechanics Meeting, January 2012.
      BibTeX Download PDF
      • @inproceedings{Grover2012jan,
      • author = {Grover, P. and Andersson, C.},
      • title = {Optimized Three-Body Gravity Assists and Manifold Transfers in End-to-End Lunar Mission Design},
      • booktitle = {AAS/AIAA Space Flight Mechanics Meeting},
      • year = 2012,
      • month = jan,
      • url = {http://www.merl.com/publications/TR2012-024}
      • }
  • MERL Contact:
  • Research Areas:

    Dynamical Systems, Mechatronics


TR Image

We describe a modular optimization framework for GTO-to-moon mission design using the planar circular restricted three-body problem (PCR3BP) model .The three-body resonant gravity assists and invariant manifolds in the planar restricted three-body problem are used as basic building blocks of this mission design. The mission is optimized by appropriately timed delta-Vs, which are obtained by a shooting method and a Gauss-Pseudospectral collocation method for different phases of the mission. Depending upon the initial and final orbits, the optimized missions consume between 10-15 % less fuel compared to a Hohmann transfer, while taking around 4 to 5 months of travel time.