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Parametric Study of An Electric Prop...

Maddox, James Warren.

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Parametric Study of An Electric Propulsion, Nuclear Thermal Reactor, Space Vehicle System.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Parametric Study of An Electric Propulsion, Nuclear Thermal Reactor, Space Vehicle System./
Author:	Maddox, James Warren.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2019,
Description:	295 p.
Notes:	Source: Masters Abstracts International, Volume: 81-04.
Contained By:	Masters Abstracts International81-04.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=13896207
ISBN:	9781085797511

Parametric Study of An Electric Propulsion, Nuclear Thermal Reactor, Space Vehicle System.
Maddox, James Warren.

Parametric Study of An Electric Propulsion, Nuclear Thermal Reactor, Space Vehicle System. - Ann Arbor : ProQuest Dissertations & Theses, 2019 - 295 p.

Source: Masters Abstracts International, Volume: 81-04.

Thesis (M.S.)--The University of Alabama, 2019.

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

The feasibility of an electric propulsion, nuclear thermal rocket, in-space propulsion system was evaluated by considering both the full range of theoretical possibilities and the likely performance derived from empirical arcjet performance. Joule heating was assumed for the electric propulsion device. The figures of merit were specific impulse and vehicle total initial mass, which quantify engine and mission performance, respectively, with a goal of achieving 1,200 sec specific impulse. Results were compared with state of the art nuclear thermal and chemical propulsion systems to estimate relative performance using a reference mission - a Hohmann transfer from low Earth orbit to low Mars orbit.The results indicate that while performance gains are realized relative to a nuclear thermal rocket, those gains are small - a specific impulse increase of approximately 5% - while the mass penalty is high - an increase of approximately 25%. The 1,200 sec specific impulse goal was not realized. Further, the addition of electricity generating equipment and additional heat loads pose additional mission risks. For all of these reasons, further analysis of the proposed hybrid system is not recommended.

ISBN: 9781085797511Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Arcjet

Parametric Study of An Electric Propulsion, Nuclear Thermal Reactor, Space Vehicle System.
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020 $a 9781085797511
035 $a (MiAaPQ)AAI13896207
035 $a AAI13896207
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100 1 $a Maddox, James Warren. $3 3556240
245 1 0 $a Parametric Study of An Electric Propulsion, Nuclear Thermal Reactor, Space Vehicle System.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2019
300 $a 295 p.
500 $a Source: Masters Abstracts International, Volume: 81-04.
500 $a Includes supplementary digital materials.
500 $a Advisor: Branam, Richard D.
502 $a Thesis (M.S.)--The University of Alabama, 2019.
506 $a This item must not be sold to any third party vendors.
520 $a The feasibility of an electric propulsion, nuclear thermal rocket, in-space propulsion system was evaluated by considering both the full range of theoretical possibilities and the likely performance derived from empirical arcjet performance. Joule heating was assumed for the electric propulsion device. The figures of merit were specific impulse and vehicle total initial mass, which quantify engine and mission performance, respectively, with a goal of achieving 1,200 sec specific impulse. Results were compared with state of the art nuclear thermal and chemical propulsion systems to estimate relative performance using a reference mission - a Hohmann transfer from low Earth orbit to low Mars orbit.The results indicate that while performance gains are realized relative to a nuclear thermal rocket, those gains are small - a specific impulse increase of approximately 5% - while the mass penalty is high - an increase of approximately 25%. The 1,200 sec specific impulse goal was not realized. Further, the addition of electricity generating equipment and additional heat loads pose additional mission risks. For all of these reasons, further analysis of the proposed hybrid system is not recommended.
590 $a School code: 0004.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Mechanics. $3 525881
653 $a Arcjet
653 $a Electric propulsion
653 $a In space propulsion
653 $a Mars mission
653 $a Nuclear thermal propulsion
653 $a Parametric analysis
690 $a 0538
690 $a 0346
710 2 $a The University of Alabama. $b Aerospace Engineering. $3 3169138
773 0 $t Masters Abstracts International $g 81-04.
790 $a 0004
791 $a M.S.
792 $a 2019
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=13896207