Pdf 2440 q 2013 02 27 103817 dt k dx 2540 chapter

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Unformatted text preview: q 2013-02-27 10:38:17 dT k dx 25/40 Chapter 19.pdf (25/40) • – – • • • • 2013-02-27 10:38:17 26/40 Chapter 19.pdf (26/40) 23 2013-02-27 10:38:18 27/40 Chapter 19.pdf (27/40) Re-entry T Distribution Space Shuttle Orbiter Fig. 23.0, Callister 5e. (Fig. 23.0 courtesy the National Aeronautics and Space Administration. • Silica tiles (400-1260 C) Large scale application reinf C-C silica tiles (1650°C) (400-1260°C) nylon felt, silicon rubber coating (400°C) Fig. 19.2W, Callister 6e. (Fig. 19.2W adapted from L.J. Korb, C.A. Morant, R.M. Calland, and C.S. Thatcher, "The Shuttle Orbiter Thermal Protection System", Ceramic Bulletin, No. 11, Nov. 1981, p. 1189.) Microstructure: ~90% porosity! Si fibers bonded to one another during heat treatment. 100 m Fig. 19.3W, Callister 5e. (Fig. 19.3W courtesy the National Aeronautics and Space Administration. Fig. 19.4W, Callister 5e. (Fig. 219.4W courtesy Lockheed Aerospace Ceramics Systems, Sunnyvale, CA.) 24 2013-02-27 10:38:18 28/40 Chapter 19.pdf (28/40) • • • • • • 25 2013-02-27 10:38:18 29/40 Chapter 19.pdf (29/40) 2013-02-27 10:38:18 30/40 Chapter 19.pdf (30/40) 2013-02-27 10:38:18 31/40 Chapte...
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This note was uploaded on 03/24/2013 for the course ENGINEER 101 taught by Professor Preston during the Winter '13 term at McMaster University.

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