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

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.

Andersson, ChristianLund University,Lunds universitet,Matematik LTH,Matematikcentrum,Institutioner vid LTH,Lunds Tekniska Högskola,Mathematics (Faculty of Engineering),Centre for Mathematical Sciences,Departments at LTH,Faculty of Engineering, LTH(Swepub:lu)naz-cia (författare)
McAdams, James V. (redaktör/utgivare)
McKinley, David P. (redaktör/utgivare)
Berry, Matthew M. (redaktör/utgivare)
Jenkins, Keith L. (redaktör/utgivare)
Matematik LTHMatematikcentrum (creator_code:org_t)

Ingår i:Advances in the Astronautical Sciences (Spaceflight Mechanics 2012: Proceedings of the 22nd AAS/AIAA Space Flight Mechanics Meeting)143 (2012), s. 1189-12030065-34381081-600397808770358179780877035824

Av författaren/redakt...: Grover, Piyush; Andersson, Chris ...; McAdams, James V ...; McKinley, David ...; Berry, Matthew M ...; Jenkins, Keith L ...

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