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Plug cluster engine concept for in-space missionsThe development of a suitable orbital transfer vehicle (OTV) engine is discussed. The OTV's dimensions are limited by those of the Space Shuttle payload bay on which it will be carried. An approach to utilize the available diameter to achieve high area ratio and thus high engine performance, is presented. Unconventional nozzles, such as clusters of small thrusters around a large diameter contoured plug, are investigated to arrive at engine designs which feature lower chamber pressures, with attendant lower heat flux, lower wall temperature, longer fatigue life, and less critical turbomachinery. Attention is also given to plug nozzle technology, high area ratio module- and scarfed bell- Plug Cluster Engine (PCE) concepts, as well as PCE performance, weight, and assessment. A conceptual design of a PCE formed from a cluster of high area ratio, scarfed, bell nozzles proved to be competitive with bell and spike nozzle engines. PCE advantages cited include increased payload length due to shorter engine length, ability to increase or decrease the number of modules and thereby the thrust, and low cost due to utilization of off-the-shelf technology.
Document ID
19790054959
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Obrien, C. J.
(Aerojet Liquid Rocket Co. Sacramento, Calif., United States)
Aukerman, C. A.
(NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 9, 2013
Publication Date
June 1, 1979
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 79-1179
Meeting Information
Meeting: AIAA, SAE, and ASME, Joint Propulsion Conference
Location: Las Vegas, NV
Start Date: June 18, 1979
End Date: June 20, 1979
Sponsors: SAE, AIAA, ASME
Accession Number
79A38972
Distribution Limits
Public
Copyright
Other

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