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Low Thrust Optimal Trajectories in t...

Hevia, Grant.

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

Record Type:	Electronic resources : Monograph/item
Title/Author:	Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem./
Author:	Hevia, Grant.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
Description:	100 p.
Notes:	Source: Masters Abstracts International, Volume: 84-12.
Contained By:	Masters Abstracts International84-12.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30425304
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. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 100 p.

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

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

This item must not be sold to any third party vendors.

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.

ISBN: 9798379695828Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Astrodynamics

Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem.
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100 1 $a Hevia, Grant. $3 3766952
245 1 0 $a Low Thrust Optimal Trajectories in the Circular Restricted Three-Body Problem.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2023
300 $a 100 p.
500 $a Source: Masters Abstracts International, Volume: 84-12.
500 $a Advisor: Bosanac, Natasha.
502 $a Thesis (M.S.)--University of Colorado at Boulder, 2023.
506 $a This item must not be sold to any third party vendors.
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.
590 $a School code: 0051.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Astronomy. $3 517668
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
690 $a 0538
690 $a 0606
710 2 $a University of Colorado at Boulder. $b Aerospace Engineering. $3 1030473
773 0 $t Masters Abstracts International $g 84-12.
790 $a 0051
791 $a M.S.
792 $a 2023
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30425304