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Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem./
Author:	Hevia, Grant.
Description:	1 online resource (100 pages)
Notes:	Source: Masters Abstracts International, Volume: 84-12.
Contained By:	Masters Abstracts International84-12.
Subject:	Aerospace engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9798379695828

Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem.
Hevia, Grant.

Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem. - 1 online resource (100 pages)

Source: Masters Abstracts International, Volume: 84-12.

Thesis (M.S.)--University of Colorado at Boulder, 2023.

Includes bibliographical references

The increasing interest in cislunar spaceflight is a motivating factor for trajectory analysts to investigate the motion of a spacecraft in Earth-Moon system. Due to the new capabilities that arise from the modern innovations in rocketry and small satellite technology, this thesis focuses on the computation of optimal low-thrust trajectories for smaller satellites equipped with electric propulsion systems. The circular restricted three-body problem (CR3BP) is used to describe motion in Earth-Moon system, and the corresponding equations of motion and natural structures are derived. The equations are augmented to include continuous thrust. Numerical methods such as multiple shooting and parameter continuation are discussed and used to generate results. Primer vector theory using hyperbolic smoothing is introduced and applied to the thrust enabled equations to generate fuel-optimal transfers in the Earth-Moon CR3BP. The approach for computing optimal transfers is leveraged to generate optimal spiral out transfers between low Earth/Moon orbits and Lyapunov orbits about the L1 equilibrium point. The resulting low-thrust transfers are analyzed to investigate the properties of optimal transfers in the CR3BP.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798379695828Subjects--Topical Terms:

686400
Aerospace engineering.
Subjects--Index Terms:

AstrodynamicsIndex Terms--Genre/Form:

554714
Electronic books.

Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem.
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500 $a Advisor: Bosanac, Natasha.
502 $a Thesis (M.S.)--University of Colorado at Boulder, 2023.
504 $a Includes bibliographical references
520 $a The increasing interest in cislunar spaceflight is a motivating factor for trajectory analysts to investigate the motion of a spacecraft in Earth-Moon system. Due to the new capabilities that arise from the modern innovations in rocketry and small satellite technology, this thesis focuses on the computation of optimal low-thrust trajectories for smaller satellites equipped with electric propulsion systems. The circular restricted three-body problem (CR3BP) is used to describe motion in Earth-Moon system, and the corresponding equations of motion and natural structures are derived. The equations are augmented to include continuous thrust. Numerical methods such as multiple shooting and parameter continuation are discussed and used to generate results. Primer vector theory using hyperbolic smoothing is introduced and applied to the thrust enabled equations to generate fuel-optimal transfers in the Earth-Moon CR3BP. The approach for computing optimal transfers is leveraged to generate optimal spiral out transfers between low Earth/Moon orbits and Lyapunov orbits about the L1 equilibrium point. The resulting low-thrust transfers are analyzed to investigate the properties of optimal transfers in the CR3BP.
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538 $a Mode of access: World Wide Web
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650 4 $a Astronomy. $3 593935
653 $a Astrodynamics
653 $a Circular restricted three body problem
653 $a Orbital mechanics
653 $a Primer vector theory
653 $a Spiral trajectories
653 $a Trajectory optimization
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