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Low-Erosion Nozzle Materials for Long-Duration Hybrid Rocket Burns.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Low-Erosion Nozzle Materials for Long-Duration Hybrid Rocket Burns./
作者:	Babb, Russell S.
面頁冊數:	1 online resource (64 pages)
附註:	Source: Masters Abstracts International, Volume: 85-02.
Contained By:	Masters Abstracts International85-02.
標題:	Aerospace engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9798380100977

Low-Erosion Nozzle Materials for Long-Duration Hybrid Rocket Burns.
Babb, Russell S.

Low-Erosion Nozzle Materials for Long-Duration Hybrid Rocket Burns. - 1 online resource (64 pages)

Source: Masters Abstracts International, Volume: 85-02.

Thesis (M.S.)--Utah State University, 2023.

Includes bibliographical references

Hybrid rocket systems have proven to be a low-cost, safe, practical, and "green" alternative to traditional propellant systems. One major hindrance to hybrid motor performance relates to nozzle throat erosion. The typical operating environment of hybrid systems can lead to nozzle throat erosion due to oxygen-rich exhaust. Additionally, since hybrid systems tend to have a continuous shift in oxidizer-to-fuel ratio the rates of nozzle erosion are highly dependent on motor configuration, flow rates, and burn times. High throat erosion aspects motor performance, reliability, and repeatability. To address this shortcoming low-erosion nozzle materials and configurations were evaluated. Pyrolytic graphite was evaluated as throat material for its high-temperature tolerance and thermal conductivity; boron nitride and reinforced carbon-carbon were evaluated as structural and thermal support around the pyrolytic graphite to be used as a heat sink and to allow the pyrolytic graphite to remain cooler for longer, delaying the onset of pyrolization and throat erosion. Multiple generations of nozzle designs were tested, and the results of long-duration burns show a five-fold decrease in erosion rates under similar burn conditions when compared to isomolded graphite nozzles.

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

Mode of access: World Wide Web

ISBN: 9798380100977Subjects--Topical Terms:

686400
Aerospace engineering.
Subjects--Index Terms:

ErosionIndex Terms--Genre/Form:

554714
Electronic books.

Low-Erosion Nozzle Materials for Long-Duration Hybrid Rocket Burns.
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500 $a Advisor: Whitmore, Stephen A.
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504 $a Includes bibliographical references
520 $a Hybrid rocket systems have proven to be a low-cost, safe, practical, and "green" alternative to traditional propellant systems. One major hindrance to hybrid motor performance relates to nozzle throat erosion. The typical operating environment of hybrid systems can lead to nozzle throat erosion due to oxygen-rich exhaust. Additionally, since hybrid systems tend to have a continuous shift in oxidizer-to-fuel ratio the rates of nozzle erosion are highly dependent on motor configuration, flow rates, and burn times. High throat erosion aspects motor performance, reliability, and repeatability. To address this shortcoming low-erosion nozzle materials and configurations were evaluated. Pyrolytic graphite was evaluated as throat material for its high-temperature tolerance and thermal conductivity; boron nitride and reinforced carbon-carbon were evaluated as structural and thermal support around the pyrolytic graphite to be used as a heat sink and to allow the pyrolytic graphite to remain cooler for longer, delaying the onset of pyrolization and throat erosion. Multiple generations of nozzle designs were tested, and the results of long-duration burns show a five-fold decrease in erosion rates under similar burn conditions when compared to isomolded graphite nozzles.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2024
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 686400
650 4 $a Mechanical engineering. $3 557493
650 4 $a Materials science. $3 557839
653 $a Erosion
653 $a Hybrid
653 $a Low-erosion nozzle materials
653 $a Nozzle
653 $a Rocket systems
653 $a Pyrolytic graphite
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