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Development of a Small-Scale, Modula...

Christison, Cade.

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Development of a Small-Scale, Modular and Portable, Kerosene-Nitrous Oxide Liquid Rocket Ground Test Rig.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Development of a Small-Scale, Modular and Portable, Kerosene-Nitrous Oxide Liquid Rocket Ground Test Rig./
作者:	Christison, Cade.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2024,
面頁冊數:	80 p.
附註:	Source: Masters Abstracts International, Volume: 86-01.
Contained By:	Masters Abstracts International86-01.
標題:	Aerospace engineering. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31239594
ISBN:	9798383214923

Development of a Small-Scale, Modular and Portable, Kerosene-Nitrous Oxide Liquid Rocket Ground Test Rig.
Christison, Cade.

Development of a Small-Scale, Modular and Portable, Kerosene-Nitrous Oxide Liquid Rocket Ground Test Rig. - Ann Arbor : ProQuest Dissertations & Theses, 2024 - 80 p.

Source: Masters Abstracts International, Volume: 86-01.

Thesis (M.S.)--Oklahoma State University, 2024.

This thesis presents the design and evaluation of a small-scale modular liquid bipropellant rocket engine ground test stand. The motivation is to develop a liquid bipropellant rocket engine test stand for development of component-level technologies, materials, and manufacturing processes. The driving requirements are to develop a system that can accurately measure the performance of a rocket engine with thrust up to 500 lbf using safe storable propellants in a configuration representative of industry applications. Key features of the test stand include pressure-fed propellant feed systems, single-element coaxial shear injector, and ablative chamber liner. The evaluation of the test stand involved static and dynamic tests, which included procedure development and test execution for cold flow testing, as well as hot fire tests. Tests determined engine thrust, specific impulse, and overall performance. Work performed includes system level requirements analysis, parametric cycle design, and individual component level design of the propellant feed system, injectors, combustion chamber, nozzle, and structural supports of the test stand. Key results of this study include measured thrust levels (140 to 290 lbf) over a range of chamber pressures (300 to 150 psi), and total propellant flow rates (1.1 to 0.9 lbm/s). Additionally, the successful design and testing of a modular and portable test stand brings lessons learned that can be used for future research and educational purposes, and for further optimization of the system for specific applications. The impact of this study is developing a broadly applicable, low cost and complexity test apparatus to enable hardware development and further research.

ISBN: 9798383214923Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Component-level technologies

Development of a Small-Scale, Modular and Portable, Kerosene-Nitrous Oxide Liquid Rocket Ground Test Rig.
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245 1 0 $a Development of a Small-Scale, Modular and Portable, Kerosene-Nitrous Oxide Liquid Rocket Ground Test Rig.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2024
300 $a 80 p.
500 $a Source: Masters Abstracts International, Volume: 86-01.
500 $a Advisor: Rouser, Kurt.
502 $a Thesis (M.S.)--Oklahoma State University, 2024.
520 $a This thesis presents the design and evaluation of a small-scale modular liquid bipropellant rocket engine ground test stand. The motivation is to develop a liquid bipropellant rocket engine test stand for development of component-level technologies, materials, and manufacturing processes. The driving requirements are to develop a system that can accurately measure the performance of a rocket engine with thrust up to 500 lbf using safe storable propellants in a configuration representative of industry applications. Key features of the test stand include pressure-fed propellant feed systems, single-element coaxial shear injector, and ablative chamber liner. The evaluation of the test stand involved static and dynamic tests, which included procedure development and test execution for cold flow testing, as well as hot fire tests. Tests determined engine thrust, specific impulse, and overall performance. Work performed includes system level requirements analysis, parametric cycle design, and individual component level design of the propellant feed system, injectors, combustion chamber, nozzle, and structural supports of the test stand. Key results of this study include measured thrust levels (140 to 290 lbf) over a range of chamber pressures (300 to 150 psi), and total propellant flow rates (1.1 to 0.9 lbm/s). Additionally, the successful design and testing of a modular and portable test stand brings lessons learned that can be used for future research and educational purposes, and for further optimization of the system for specific applications. The impact of this study is developing a broadly applicable, low cost and complexity test apparatus to enable hardware development and further research.
590 $a School code: 0664.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Mechanical engineering. $3 649730
650 4 $a Engineering. $3 586835
650 4 $a Fluid mechanics. $3 528155
653 $a Component-level technologies
653 $a Rocket engine
653 $a Industry applications
653 $a Cold flow testing
653 $a Liquid bipropellant
690 $a 0538
690 $a 0548
690 $a 0537
690 $a 0204
710 2 $a Oklahoma State University. $b Mechanical & Aerospace Engineering. $3 3194223
773 0 $t Masters Abstracts International $g 86-01.
790 $a 0664
791 $a M.S.
792 $a 2024
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=31239594