Optimal impulsive manifold-based transfers with guidance to Earth-Moon L1 halo orbits

William Anthony, Annie Larsen, Eric A. Butcher

Research output: Contribution to journalConference articlepeer-review

2 Scopus citations


An optimization method combining genetic algorithms, differential correction, and primer vector theory is employed for designing fuel optimal 2-impulse transfers from low earth orbit or geostationary orbit to a halo orbit about the Earth-Moon L1 libration point using the stable manifold of the halo orbit. All transfers require one maneuver to leave LEO or GEO and a second maneuver to transfer onto the stable manifold. The trajectories obtained have total ΔV's of 3.61 and 1.14 km/s respectively. An LQR based guidance scheme is presented which maintains the spacecraft on the stable manifold in the presence of injection errors in burn magnitude and direction using a variable low continuous thrust engine. Monte Carlo analyses are conducted to further demonstrate the effectiveness of the guidance scheme. The total ΔV costs to use the guidance scheme averages 14.385 m/s for transfers from LEO and 6.54 m/s for transfers from GEO, when a thrust magnitude Gaussian dispersion with 1σ = 1% is combined with in-plane and out-of-plane thrust direction Gaussian dispersions with 1σ = 1 degree error. The guidance is also implemented assuming a limit to the continuous thrust.

Original languageEnglish (US)
Pages (from-to)2093-2112
Number of pages20
JournalAdvances in the Astronautical Sciences
StatePublished - 2013
Event23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 - Kauai, HI, United States
Duration: Feb 10 2013Feb 14 2013

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science


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