NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Materials Problems in Chemical Liquid-Propellant Rocket SystemsWith the advent of the space age, new adjustments in technical thinking and engineering experience are necessary. There is an increasing and extensive interest in the utilization of materials for components to be used at temperatures ranging from -423 to over 3500 deg F. This paper presents a description of the materials problems associated with the various components of chemical liquid rocket systems. These components include cooled and uncooled thrust chambers, injectors, turbine drive systems, propellant tanks, and cryogenic propellant containers. In addition to materials limitations associated with these components, suggested research approaches for improving materials properties are made. Materials such as high-temperature alloys, cermets, carbides, nonferrous alloys, plastics, refractory metals, and porous materials are considered.
Document ID
19980227984
Acquisition Source
Headquarters
Document Type
Technical Memorandum (TM)
Authors
Gilbert, L. L. (Aerojet-General Corp. Azusa, CA United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1959
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-X-89
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available