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  • Open Daily: 10am - 10pm
    Alley-side Pickup: 10am - 7pm

    3038 Hennepin Ave Minneapolis, MN
    612-822-4611

Open Daily: 10am - 10pm | Alley-side Pickup: 10am - 7pm
3038 Hennepin Ave Minneapolis, MN
612-822-4611
Space Mission Planning: Multi-Body Trajectories for Space Vehicles

Space Mission Planning: Multi-Body Trajectories for Space Vehicles

Vepa, Ranjan

Paperback

Series: de Gruyter Textbook

Technology & Engineering

Publisher Price: $94.99

PREORDER - Expected ship date October 19, 2026

ISBN10: 3111541223
ISBN13: 9783111541228
Publisher: de Gruyter
Published: Oct 19 2026
Pages: 284
Language: English

Over the last decade the three body problem has emerged as the standard model for defining reference trajectories in space. It is now essentially feasible to patch together segments of trajectories defined by different sets of three bodies and construct a reasonably feasible trajectory in space. The actual trajectories may be constructed by solutions to either the circular restricted or the elliptic restricted three body problems (RTBP). For example, the stable manifolds of a three body cluster help in transferring the spacecraft into the Halo orbit and the unstable manifolds help in escaping from the Halo orbit. A combination of the stable and unstable manifolds could be utilized to transfer the spacecraft from the Sun-Earth system to the Sun-Jupiter system or another such system under the framework of the circular restricted TBP. A similar application is feasible with the elliptic restricted TBP. Further significant reductions in the fuel requirements can be achieved by adopting optimal elliptic restricted TBP trajectories including ballistic trajectories, which could be synthesized by methods outlined in this monograph, thus making hem suitable for mission planning.

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