Integrated modular propulsion for launch vehiclesThe paper proposes a modular approach to rocket propulsion which offers a versatile method for realizing the goals of low cost, safety, reliability, and ease of operation. It is shown that, using practical modules made up of only 4-6 individual elements, it is possible to achieve thrust levels of 2-3 mln lbf and more, using turbomachinery, thrust chambers, lines, and valves about the size of SSME hardware. The approach is illustrated by a LOX/LH2 configuration.
Document ID
19930065765
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Knuth, William (NASA Headquarters Washington, DC United States)
Crawford, Roger (NASA Headquarters Washington, DC United States)
Litchford, Ron (Univ. of Tennessee - Calspan Center for Space Transportation and Applied Research Tullahoma, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-1889
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit