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On the Applications of Signed Distan...

Sikes, Jared.

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On the Applications of Signed Distance Fields to Spacecraft Trajectory Design and Station Keeping.

Record Type:	Electronic resources : Monograph/item
Title/Author:	On the Applications of Signed Distance Fields to Spacecraft Trajectory Design and Station Keeping./
Author:	Sikes, Jared.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2024,
Description:	177 p.
Notes:	Source: Dissertations Abstracts International, Volume: 85-12, Section: B.
Contained By:	Dissertations Abstracts International85-12B.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31140605
ISBN:	9798382812731

On the Applications of Signed Distance Fields to Spacecraft Trajectory Design and Station Keeping.
Sikes, Jared.

On the Applications of Signed Distance Fields to Spacecraft Trajectory Design and Station Keeping. - Ann Arbor : ProQuest Dissertations & Theses, 2024 - 177 p.

Source: Dissertations Abstracts International, Volume: 85-12, Section: B.

Thesis (Ph.D.)--The University of Alabama, 2024.

As computational resources have continued to improve in both performance and accessibility in recent years, the usage of high-fidelity ephemeris models in the preliminary phase of mission design has likewise increased. From a practicality standpoint, it is necessary to use these high-fidelity models, as they better represent the real-world dynamics encountered by the spacecraft during flight and paint a more accurate picture of the mission design space and costs associated with the mission. However, preliminary trajectory design in ephemeris models presents several challenges that may not be apparent when dealing with lower-fidelity models, such as the circular restricted three body problem (CR3BP). Whereas the CR3BP admits periodic solutions in an autonomous reference frame, the ephemeris model only contains quasi-periodic, time dependent solutions, forcing mission designers to carefully consider the mission's epoch when transitioning from the CR3BP to the ephemeris model. To overcome some of these challenges, mission designers typically use trajectories computed in the CR3BP as reference solutions which are patched into the ephemeris model for re-convergence. However, depending on the chosen epoch, the patching process may result in decreased mission performance or failure to converge a valid solution, particularly in highly chaotic regimes like cis-lunar space. To address these issues, this work seeks to develop a more general framework for transitioning CR3BP reference solutions into the ephemeris model through the use of signed distance fields (SDFs) as boundary constraints on the trajectory optimization problem for preliminary mission design and station keeping assessments.SDFs are a scalar field that indicate the closest distance of a point to some pre-defined surface. Typically, SDFs are computed using a triangulated mesh along with the fast marching method to efficiently sweep the area of interest and obtain values for the{A0}distance, which are signed depending on whether the point is inside (negative) or outside (positive) the mesh. SDFs may be computed about a nominal CR3BP orbit by creating a 3D tube of a specified radius and used as a constraint in station keeping and trajectory design problems, irrespective of the ephemeris epoch of interest. By constraining the spacecraft to target and maintain its path through a 3D tube around the nominal orbit, perturbations in the local dynamics due to the time-dependent nature of the ephemeris frame may be exploited within optimization schemes, without being tied to a particular pre-computed reference path. Further, the incorporation of SDFs as a trajectory design boundary condition in ballistic trajectories results in decreased {acute}{88}{86}V usage as compared to more traditional stable manifold targeting schemes when used in an ephemeris model. This investigation will further explore the performance of SDFs in trajectory optimization problems across the commonly used Sun-Earth and Earth-Moon ephemeris reference frames for a variety of regimes near the Lagrange points and central bodies. Lastly, this work will extend the applications of SDFs to computing station-keeping maneuvers about CR3BP reference orbits in high-fidelity models and recontact mitigation when departing from nearly-stable cis-lunar orbits.

ISBN: 9798382812731Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Astrodynamics

On the Applications of Signed Distance Fields to Spacecraft Trajectory Design and Station Keeping.
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520 $a As computational resources have continued to improve in both performance and accessibility in recent years, the usage of high-fidelity ephemeris models in the preliminary phase of mission design has likewise increased. From a practicality standpoint, it is necessary to use these high-fidelity models, as they better represent the real-world dynamics encountered by the spacecraft during flight and paint a more accurate picture of the mission design space and costs associated with the mission. However, preliminary trajectory design in ephemeris models presents several challenges that may not be apparent when dealing with lower-fidelity models, such as the circular restricted three body problem (CR3BP). Whereas the CR3BP admits periodic solutions in an autonomous reference frame, the ephemeris model only contains quasi-periodic, time dependent solutions, forcing mission designers to carefully consider the mission's epoch when transitioning from the CR3BP to the ephemeris model. To overcome some of these challenges, mission designers typically use trajectories computed in the CR3BP as reference solutions which are patched into the ephemeris model for re-convergence. However, depending on the chosen epoch, the patching process may result in decreased mission performance or failure to converge a valid solution, particularly in highly chaotic regimes like cis-lunar space. To address these issues, this work seeks to develop a more general framework for transitioning CR3BP reference solutions into the ephemeris model through the use of signed distance fields (SDFs) as boundary constraints on the trajectory optimization problem for preliminary mission design and station keeping assessments.SDFs are a scalar field that indicate the closest distance of a point to some pre-defined surface. Typically, SDFs are computed using a triangulated mesh along with the fast marching method to efficiently sweep the area of interest and obtain values for the{A0}distance, which are signed depending on whether the point is inside (negative) or outside (positive) the mesh. SDFs may be computed about a nominal CR3BP orbit by creating a 3D tube of a specified radius and used as a constraint in station keeping and trajectory design problems, irrespective of the ephemeris epoch of interest. By constraining the spacecraft to target and maintain its path through a 3D tube around the nominal orbit, perturbations in the local dynamics due to the time-dependent nature of the ephemeris frame may be exploited within optimization schemes, without being tied to a particular pre-computed reference path. Further, the incorporation of SDFs as a trajectory design boundary condition in ballistic trajectories results in decreased {acute}{88}{86}V usage as compared to more traditional stable manifold targeting schemes when used in an ephemeris model. This investigation will further explore the performance of SDFs in trajectory optimization problems across the commonly used Sun-Earth and Earth-Moon ephemeris reference frames for a variety of regimes near the Lagrange points and central bodies. Lastly, this work will extend the applications of SDFs to computing station-keeping maneuvers about CR3BP reference orbits in high-fidelity models and recontact mitigation when departing from nearly-stable cis-lunar orbits.
590 $a School code: 0004.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Astronomy. $3 517668
650 4 $a Mechanics. $3 525881
653 $a Astrodynamics
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