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Spacecraft Trajectory Design and Con...

Henry, D. B.

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Spacecraft Trajectory Design and Control Leveraging Quasi-periodic Orbits.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Spacecraft Trajectory Design and Control Leveraging Quasi-periodic Orbits./
Author:	Henry, D. B.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2024,
Description:	191 p.
Notes:	Source: Dissertations Abstracts International, Volume: 85-11, Section: B.
Contained By:	Dissertations Abstracts International85-11B.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31149340
ISBN:	9798382719900

Spacecraft Trajectory Design and Control Leveraging Quasi-periodic Orbits.
Henry, D. B.

Spacecraft Trajectory Design and Control Leveraging Quasi-periodic Orbits. - Ann Arbor : ProQuest Dissertations & Theses, 2024 - 191 p.

Source: Dissertations Abstracts International, Volume: 85-11, Section: B.

Thesis (Ph.D.)--University of Colorado at Boulder, 2024.

Periodic orbits are the most commonly exploited dynamical structure in the preliminary spacecraft trajectory design stages. Recent advancements now enable the efficient computation of quasi-periodic orbits, a far more abundant class of bounded motion that offers significant advantages for spacecraft mission planning. This thesis develops novel trajectory design and control methodologies for leveraging these structures. The techniques are applied in the Earth-Moon system.First, modifications to an existing quasi-periodic orbit computation algorithm are detailed and the resulting algorithm is applied to summarize quasi-periodic orbits foliating normally hyperbolic invariant manifolds (NHIMs) around L1 and L2 in the circular restricted three-body problem (CR3BP). The algorithm is also applied to perform the first fully numerical computation of several quasi-periodic orbit families and their stability in the spatial Hill restricted four-body problem (HR4BP) in these regions.Transfers between quasi-periodic orbits are then considered. A methodology for designing impulsive maneuvers between a pair of unstable orbits is devised that enables the rapid computation of multi-parameter families of transfers between quasi-periodic orbits. Heteroclinic trajectories between quasi-periodic orbits are identified by modifying this technique. A fully numerical methodology to compute the entire two-parameter families of connections that exist between NHIMs that exist at the same energy level in the CR3BP once a single connection is found is devised.Quasi-periodic orbits are also prevalent in formation flying. The lead-follower dynamics of spacecraft operating on a quasi-periodic orbit are analyzed. This analysis leads to the development of a formation design strategy that extends the class of solvable relative trajectory design problems. Control will be necessary to enable designed relative trajectories in practice. A dynamical systems-based control strategy is presented to drive spacecraft to desired locations on quasi-periodic orbit families. Altogether, the current work seeks to develop approaches that unlock the potential of considering quasi-periodic orbits in the early stages of spacecraft trajectory design.

ISBN: 9798382719900Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Formation flying

Spacecraft Trajectory Design and Control Leveraging Quasi-periodic Orbits.
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300 $a 191 p.
500 $a Source: Dissertations Abstracts International, Volume: 85-11, Section: B.
500 $a Advisor: Scheeres, Daniel J.
502 $a Thesis (Ph.D.)--University of Colorado at Boulder, 2024.
520 $a Periodic orbits are the most commonly exploited dynamical structure in the preliminary spacecraft trajectory design stages. Recent advancements now enable the efficient computation of quasi-periodic orbits, a far more abundant class of bounded motion that offers significant advantages for spacecraft mission planning. This thesis develops novel trajectory design and control methodologies for leveraging these structures. The techniques are applied in the Earth-Moon system.First, modifications to an existing quasi-periodic orbit computation algorithm are detailed and the resulting algorithm is applied to summarize quasi-periodic orbits foliating normally hyperbolic invariant manifolds (NHIMs) around L1 and L2 in the circular restricted three-body problem (CR3BP). The algorithm is also applied to perform the first fully numerical computation of several quasi-periodic orbit families and their stability in the spatial Hill restricted four-body problem (HR4BP) in these regions.Transfers between quasi-periodic orbits are then considered. A methodology for designing impulsive maneuvers between a pair of unstable orbits is devised that enables the rapid computation of multi-parameter families of transfers between quasi-periodic orbits. Heteroclinic trajectories between quasi-periodic orbits are identified by modifying this technique. A fully numerical methodology to compute the entire two-parameter families of connections that exist between NHIMs that exist at the same energy level in the CR3BP once a single connection is found is devised.Quasi-periodic orbits are also prevalent in formation flying. The lead-follower dynamics of spacecraft operating on a quasi-periodic orbit are analyzed. This analysis leads to the development of a formation design strategy that extends the class of solvable relative trajectory design problems. Control will be necessary to enable designed relative trajectories in practice. A dynamical systems-based control strategy is presented to drive spacecraft to desired locations on quasi-periodic orbit families. Altogether, the current work seeks to develop approaches that unlock the potential of considering quasi-periodic orbits in the early stages of spacecraft trajectory design.
590 $a School code: 0051.
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653 $a Four-body problem
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653 $a Invariant tori
653 $a Spacecraft control
653 $a Transfer design
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690 $a 0596
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