File:Ablative heat shield studies for NASA Mars-Earth return entry vehicles (IA ablativeheatshie1094534895).pdf
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Summary
[edit]Ablative heat shield studies for NASA Mars/Earth return entry vehicles ( ) | ||
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Author |
Hamm, Michael K. |
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Title |
Ablative heat shield studies for NASA Mars/Earth return entry vehicles |
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Publisher |
Monterey, California: Naval Postgraduate School |
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Description |
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. Subjects: Space vehicles; Atmospheric entry; Mars (Planet); Ablative materials; Shielding (Heat); Ablative; hypersonic; NASA; Mars; heat shield |
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Language | English | |
Publication date |
September 1990 publication_date QS:P577,+1990-09-00T00:00:00Z/10 |
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Current location |
IA Collections: navalpostgraduateschoollibrary; fedlink |
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Accession number |
ablativeheatshie1094534895 |
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Source | ||
Permission (Reusing this file) |
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted. |
Licensing
[edit]Public domainPublic domainfalsefalse |
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This file has been identified as being free of known restrictions under copyright law, including all related and neighboring rights. |
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current | 06:37, 8 July 2020 | 1,275 × 1,650, 122 pages (2.9 MB) | Fæ (talk | contribs) | FEDLINK - United States Federal Collection ablativeheatshie1094534895 (User talk:Fæ/IA books#Fork8) (batch 1990-1992 #2770) |
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Short title | Ablative heat shield studies for NASA Mars/Earth return entry vehicles |
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Author | Hamm, Michael K. |
File change date and time | 08:05, 29 September 2011 |
Date and time of digitizing | 08:05, 29 September 2011 |
Date metadata was last modified | 08:05, 29 September 2011 |
Software used | Hamm, Michael K. |
Conversion program | |
Encrypted | no |
Page size |
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Version of PDF format | 1.4 |