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Enabling Outer Planet Exploration: P...

Kumar, Saroj,

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Enabling Outer Planet Exploration: Performance and Feasibility of Nuclear Thermal Propulsion for Rendezvous Missions /

Record Type:	Electronic resources : Monograph/item
Title/Author:	Enabling Outer Planet Exploration: Performance and Feasibility of Nuclear Thermal Propulsion for Rendezvous Missions // Saroj Kumar.
Author:	Kumar, Saroj,
Description:	1 electronic resource (211 pages)
Notes:	Source: Dissertations Abstracts International, Volume: 85-10, Section: B.
Contained By:	Dissertations Abstracts International85-10B.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30995354
ISBN:	9798382309651

Enabling Outer Planet Exploration: Performance and Feasibility of Nuclear Thermal Propulsion for Rendezvous Missions /
Kumar, Saroj,

Enabling Outer Planet Exploration: Performance and Feasibility of Nuclear Thermal Propulsion for Rendezvous Missions /Saroj Kumar. - 1 electronic resource (211 pages)

Source: Dissertations Abstracts International, Volume: 85-10, Section: B.

Nuclear Thermal Propulsion (NTP) provides the compelling alternative between the chemical and electric propulsion systems for outer planet robotic missions. High-thrust and high-specific impulse (over twice the best chemical propulsion engine) NTP systems can enable outer planet missions that have been limited due to the large ∆V requirements. This dissertation identifies an enabling mission architecture and NTP engine thrust class for rendezvous missions to the Gas giant and Ice giant systems. The work presented in the dissertation demonstrates the performance impact of the NTP system and its feasibility for robotic missions using a systems engineering model driven by the model based systems engineering (MBSE) which is coupled with the domain engineering analysis models and systems engineering architectural models. The performance metrics are chosen based on the finite maneuver analysis and design reference mission trade tree to determine the solution space of NTP for high energy missions. The developed spacecraft integrated system model allows rapid mission analysis for engine thrust class ranging from 5 klbf to 30 klbf and Isp from 850 s to 900 s for expendable and non-expendable architectures. The direct spacecraft injection analysis showed payload delivery of over 12% to Jupiter and over 30% to Saturn for NTP system on a commercial heavy lift launch vehicle when compared with standalone super heavy-lift launch vehicles. The point design studies demonstrated the enhanced capability of NTP system by reducing the trip times to Gas giant missions by a factor of two or more. Engine trade analysis shows 12.5 to 15 klbf NTP engines are optimum for rendezvous missions to the outer planets using expendable configuration, which consists of a spacecraft and NTP injection stage with injection stage being used for trans-planetary injection and plane change maneuver only and spacecraft's storable propellant to be used for planetary orbit insertion. Payload mass delivery using an expendable configuration for a Jupiter rendezvous mission is shown to outperform non-expendable configuration (NTP system to be used for both trans-planetary injection and planetary orbit insertion) by 5.67% for Hohmann transfers. However, non-expendable configurations have shown similar payload delivery for high energy Type-I trajectory missions with trip times of 1.49 years.

English

ISBN: 9798382309651Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Jupiter rendezvous missions

Enabling Outer Planet Exploration: Performance and Feasibility of Nuclear Thermal Propulsion for Rendezvous Missions /
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300 $a 1 electronic resource (211 pages)
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500 $a Source: Dissertations Abstracts International, Volume: 85-10, Section: B.
500 $a Advisors: Thomas, L. Dale; Cassibry, Jason T. Committee members: Frederick, Robert; Turner, Matthew; Xu, Gabriel.
502 $b Ph.D. $c The University of Alabama in Huntsville $d 2024.
520 $a Nuclear Thermal Propulsion (NTP) provides the compelling alternative between the chemical and electric propulsion systems for outer planet robotic missions. High-thrust and high-specific impulse (over twice the best chemical propulsion engine) NTP systems can enable outer planet missions that have been limited due to the large ∆V requirements. This dissertation identifies an enabling mission architecture and NTP engine thrust class for rendezvous missions to the Gas giant and Ice giant systems. The work presented in the dissertation demonstrates the performance impact of the NTP system and its feasibility for robotic missions using a systems engineering model driven by the model based systems engineering (MBSE) which is coupled with the domain engineering analysis models and systems engineering architectural models. The performance metrics are chosen based on the finite maneuver analysis and design reference mission trade tree to determine the solution space of NTP for high energy missions. The developed spacecraft integrated system model allows rapid mission analysis for engine thrust class ranging from 5 klbf to 30 klbf and Isp from 850 s to 900 s for expendable and non-expendable architectures. The direct spacecraft injection analysis showed payload delivery of over 12% to Jupiter and over 30% to Saturn for NTP system on a commercial heavy lift launch vehicle when compared with standalone super heavy-lift launch vehicles. The point design studies demonstrated the enhanced capability of NTP system by reducing the trip times to Gas giant missions by a factor of two or more. Engine trade analysis shows 12.5 to 15 klbf NTP engines are optimum for rendezvous missions to the outer planets using expendable configuration, which consists of a spacecraft and NTP injection stage with injection stage being used for trans-planetary injection and plane change maneuver only and spacecraft's storable propellant to be used for planetary orbit insertion. Payload mass delivery using an expendable configuration for a Jupiter rendezvous mission is shown to outperform non-expendable configuration (NTP system to be used for both trans-planetary injection and planetary orbit insertion) by 5.67% for Hohmann transfers. However, non-expendable configurations have shown similar payload delivery for high energy Type-I trajectory missions with trip times of 1.49 years.
546 $a English
590 $a School code: 0278
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Nuclear engineering. $3 595435
650 4 $a Systems science. $3 3168411
650 4 $a Mechanical engineering. $3 649730
653 $a Jupiter rendezvous missions
653 $a Model based systems engineering
653 $a Nuclear Thermal Propulsion
653 $a Outer planets
653 $a Trajectory analysis
690 $a 0538
690 $a 0552
690 $a 0790
690 $a 0548
710 2 $a The University of Alabama in Huntsville. $b Mechanical and Aerospace Engineering. $e degree granting institution. $3 3825179
720 1 $a Thomas, L. Dale $e degree supervisor.
720 1 $a Cassibry, Jason T. $e degree supervisor.
773 0 $t Dissertations Abstracts International $g 85-10B.
790 $a 0278
791 $a Ph.D.
792 $a 2024
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30995354