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Title: Stepped nozzle

Abstract

An insert 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.

Inventors:
 [1]
  1. (Danville, CA)
Issue Date:
Research Org.:
Lawrence Livermore National Lab. (LLNL), Livermore, CA (United States)
OSTI Identifier:
871699
Patent Number(s):
5779151
Assignee:
Regents of University of California (Oakland, CA) LLNL
DOE Contract Number:  
W-7405-ENG-48
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
stepped; nozzle; insert; allows; supersonic; rocket; propulsion; operate; ratios; provides; improved; vehicle; flight; performance; increased; payload; significant; advantages; existing; devices; increasing; temporarily; fastened; simple; retaining; mechanism; diverging; segment; multi-step; variation; ratio; mounted; released; ejected; providing; significant advantages; significant advantage; supersonic nozzle; rocket propulsion; improved vehicle; nozzle segment; diverging nozzle; /239/

Citation Formats

Sutton, George P. Stepped nozzle. United States: N. p., 1998. Web.
Sutton, George P. Stepped nozzle. United States.
Sutton, George P. Thu . "Stepped nozzle". United States. https://www.osti.gov/servlets/purl/871699.
@article{osti_871699,
title = {Stepped nozzle},
author = {Sutton, George P.},
abstractNote = {An insert 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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1998},
month = {1}
}

Patent:

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