Chapter
Jul 11, 2012
Regolith-Derived Heat Shield for Planetary Body Entry and Descent System with In Situ Fabrication
Authors: Michael D. Hogue [email protected], Robert P. Mueller [email protected], Paul E. Hintze [email protected], Laurent Sibille [email protected], and Daniel J. Rasky [email protected]Author Affiliations
Publication: Earth and Space 2012: Engineering, Science, Construction, and Operations in Challenging Environments
Abstract
In this paper we will discuss a new mass-efficient and innovative way of protecting high-mass spacecraft during planetary Entry, Descent & Landing (EDL). Heat shields fabricated in situ can provide a thermal-protection system (TPS) for spacecraft that routinely enter a planetary atmosphere. By fabricating the heat shield with space resources from regolith materials available on moons and asteroids, it is possible to avoid launching the heat-shield mass from Earth. Three regolith processing and manufacturing methods will be discussed: 1) oxygen & metal extraction ISRU processes produce glassy melts enriched in alumina and titania, processed to obtain variable density, high melting point and heat-resistance; 2) compression and sintering of the regolith yield low density materials; 3) in-situ derived high-temperature polymers created to bind regolith particles together, with a lower energy budget.
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© 2012 American Society of Civil Engineers.
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Published online: Jul 11, 2012
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NASA, Electrostatics & Surface Physics Laboratory, NE-S-1, Kennedy Space Center, FL 32899.E-mail: [email protected]
NASA, Surface Systems Office, NE-S, Kennedy Space Center, FL 32899.E-mail: [email protected]
NASA, Corrosion Laboratory, NE-L, Kennedy Space Center, FL 32899.E-mail: [email protected]
ESC QinetiQ North America, Kennedy Space Center, FL 32899.E-mail: [email protected]
NASA, Emerging Space Office, Ames Research Center, Moffett Field, CA 94035.E-mail: [email protected]
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