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An Investigation Into Optimal Descent Trajectories for Multipurpose Long Range Space Vehicles Under Advanced Conditions.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	An Investigation Into Optimal Descent Trajectories for Multipurpose Long Range Space Vehicles Under Advanced Conditions./
Author:	Levis, John M.
Description:	1 online resource (127 pages)
Notes:	Source: Masters Abstracts International, Volume: 85-01.
Contained By:	Masters Abstracts International85-01.
Subject:	Mathematics. -
Online resource:	click for full text (PQDT)
ISBN:	9798379953850

An Investigation Into Optimal Descent Trajectories for Multipurpose Long Range Space Vehicles Under Advanced Conditions.
Levis, John M.

An Investigation Into Optimal Descent Trajectories for Multipurpose Long Range Space Vehicles Under Advanced Conditions. - 1 online resource (127 pages)

Source: Masters Abstracts International, Volume: 85-01.

Thesis (M.S.)--The University of Texas Rio Grande Valley, 2023.

Includes bibliographical references

In this work, we investigate the problem of fuel-optimal control of space vehicle descent trajectories. The main tool we use to establish optimality is Pontryagin's Maximum Principle. We present a variety of scenarios with increasing complexities, including drag, wind, and moving landing platforms in the context of differing atmospheric and gravitational conditions. Throughout the paper, we use a balance of analytical and numerical techniques. Finally, observations and conclusions drawn from the investigation form the basis for suggestions into additional areas of analysis.

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

Mode of access: World Wide Web

ISBN: 9798379953850Subjects--Topical Terms:

527692
Mathematics.
Subjects--Index Terms:

Gravitational conditionsIndex Terms--Genre/Form:

554714
Electronic books.

An Investigation Into Optimal Descent Trajectories for Multipurpose Long Range Space Vehicles Under Advanced Conditions.
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504 $a Includes bibliographical references
520 $a In this work, we investigate the problem of fuel-optimal control of space vehicle descent trajectories. The main tool we use to establish optimality is Pontryagin's Maximum Principle. We present a variety of scenarios with increasing complexities, including drag, wind, and moving landing platforms in the context of differing atmospheric and gravitational conditions. Throughout the paper, we use a balance of analytical and numerical techniques. Finally, observations and conclusions drawn from the investigation form the basis for suggestions into additional areas of analysis.
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653 $a Trajectories
653 $a Landing platforms
653 $a Complexities
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