Stepped nozzle
Abstract
An insert is described which allows a supersonic nozzle of a rocket propulsion system to operate at two or more different nozzle area ratios. This provides an improved vehicle flight performance or increased payload. The insert has significant advantages over existing devices for increasing nozzle area ratios. The insert is temporarily fastened by a simple retaining mechanism to the aft end of the diverging segment of the nozzle and provides for a multi-step variation of nozzle area ratio. When mounted in place, the insert provides the nozzle with a low nozzle area ratio. During flight, the retaining mechanism is released and the insert ejected thereby providing a high nozzle area ratio in the diverging nozzle segment. 5 figs.
- Inventors:
- Issue Date:
- Research Org.:
- Univ. of California (United States)
- Sponsoring Org.:
- USDOE, Washington, DC (United States)
- OSTI Identifier:
- 672502
- Patent Number(s):
- 5779151
- Application Number:
- PAN: 8-654,478
- Assignee:
- Univ. of California, Oakland, CA (United States)
- DOE Contract Number:
- W-7405-ENG-48
- Resource Type:
- Patent
- Resource Relation:
- Other Information: PBD: 14 Jul 1998
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS; ROCKETS; PROPULSION SYSTEMS; NOZZLES; SUPERSONIC FLOW; DESIGN; PERFORMANCE
Citation Formats
Sutton, G P. Stepped nozzle. United States: N. p., 1998.
Web.
Sutton, G P. Stepped nozzle. United States.
Sutton, G P. Tue .
"Stepped nozzle". United States.
@article{osti_672502,
title = {Stepped nozzle},
author = {Sutton, G P},
abstractNote = {An insert is described which allows a supersonic nozzle of a rocket propulsion system to operate at two or more different nozzle area ratios. This provides an improved vehicle flight performance or increased payload. The insert has significant advantages over existing devices for increasing nozzle area ratios. The insert is temporarily fastened by a simple retaining mechanism to the aft end of the diverging segment of the nozzle and provides for a multi-step variation of nozzle area ratio. When mounted in place, the insert provides the nozzle with a low nozzle area ratio. During flight, the retaining mechanism is released and the insert ejected thereby providing a high nozzle area ratio in the diverging nozzle segment. 5 figs.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1998},
month = {7}
}
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