Development of Nonmetallic External Insulation Thermal Protection Systems for Space Shuttle Reentry and Environmental Systems Div., General Electric Company

Format:

Conference/Event

Author/Creator:

Gorsuch, Paul D., author.

Conference Name:

National Aeronautic and Space Engineering and Manufacturing Meeting (1970-10-05 : Los Angeles, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1970

Summary:

Recently completed design studies for launch vehicle-orbiter space transportation systems have indicated that the payload weight fractions are extremely small. These studies have also identified the vehicle structures and thermal protection systems as areas of high weight-savings potential, since their combined weights may be equal to or greater than the payloads. Thermal protection systems based on rigidized and reusable ceramic insulation materials and on reinforced oxidation-resistant or inhibited carbon-carbon composites offer potential for greatly increasing the payload weight fractions. These types of materials are now undergoing extensive development. It is the purpose of this paper to describe their properties and characteristics, to summarize the progress being made in optimizing their properties and/or uniformity and reliability for shuttle vehicle applications, to present some prototype thermal protection system panel designs utilizing these materials, and to make cost and weight comparisons with other candidate systems

Notes:

Vendor supplied data

Publisher Number:

700771

Access Restriction:

Restricted for use by site license