Ablative heat shield studies for NASA Mars/Earth return entry vehicles
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Authors
Hamm, Michael K.
Subjects
Ablative
hypersonic
NASA
Mars
heat shield
hypersonic
NASA
Mars
heat shield
Advisors
Henline, William D.
Platzer, Max F.
Date of Issue
1990-09
Date
1990-09
Publisher
Monterey, California: Naval Postgraduate School
Language
Abstract
A material that behaves likes a glassy ablator on the surface, has a low thermal conductivity, is structurally tough, lightweight, and is in some sense reusable, would be desirable for the protective heat shield used on Earth entry vehicles. A material for this purpose has been developed that uses silicon dioxide (fused quartz) in a fibrous packed matrix, forming blocks which can behave as a glassy ablator on the surface when subject to very high surface heat fluxes. These fibrous silicon dioxide blocks are called Reusable Surface Insulation (RSI). The primary constituent of the RSI material is silicon dioxide, but may contain other compounds (e.g. alumina borosilicate) to affect the thermal and physical properties. The research performed in this thesis is to determine the ablative behavior of ceramic RSI materials in a hypersonic high enthalpy flow that is used to simulate entry into Earth atmosphere. Actual arc jet experiments were performed to measure mass loss, melt run off, and fiber collapse of these materials and compare the experimental results with predicted theoretical values. The tests were performed to ascertain if RSI type materials could be used for entry vehicles proposed in NASA Mars missions.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
x, 110 p. ill.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.