Stepped nozzle
Patent
·
OSTI ID:871699
- Danville, CA
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.
- Research Organization:
- Lawrence Livermore National Laboratory (LLNL), Livermore, CA
- DOE Contract Number:
- W-7405-ENG-48
- Assignee:
- Regents of University of California (Oakland, CA)
- Patent Number(s):
- US 5779151
- OSTI ID:
- 871699
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
/239/
advantages
allows
devices
diverging
diverging nozzle
ejected
existing
fastened
flight
improved
improved vehicle
increased
increasing
insert
mechanism
mounted
multi-step
nozzle
nozzle segment
operate
payload
performance
propulsion
provides
providing
ratio
ratios
released
retaining
rocket
rocket propulsion
segment
significant
significant advantage
significant advantages
simple
stepped
supersonic
supersonic nozzle
temporarily
variation
vehicle
advantages
allows
devices
diverging
diverging nozzle
ejected
existing
fastened
flight
improved
improved vehicle
increased
increasing
insert
mechanism
mounted
multi-step
nozzle
nozzle segment
operate
payload
performance
propulsion
provides
providing
ratio
ratios
released
retaining
rocket
rocket propulsion
segment
significant
significant advantage
significant advantages
simple
stepped
supersonic
supersonic nozzle
temporarily
variation
vehicle