l22_reentry

l22_reentry - the extreme heating conditions Heat sinks...

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Reentry Col John E. Keesee MIT Dept of Aeronautics and Astronautics November 25, 2003
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Background • An ICBM with a range of 6500 miles has a stagnation temperature of 12,000 ºF, 2000 ºF hotter than the surface of the sun • Calculations showed that the optimum design for structural strength, resistance to heating, and free flight stability was a long, needle nosed reentry body – But it would vaporize during reentry
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Background • Harry Julian Allen proposed an alternate solution, using pencil and paper – Contradicted 50 years of research – Suggested a blunt body would better put more of the heat the air and less into the body – Strong bow shockwave
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Background • Still needed unusual materials to survive
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Unformatted text preview: the extreme heating conditions Heat sinks Copper, tungsten, molybdenum, beryllium Shuttle Ablators Teflon, nylon, fiberglass Mercury, Gemini, Apollo, ICBMs Thermal Barrier 2 2 1 2 2 c c V m Q Q mV KE = = = Material Energy to Vaporize BTU/lb Melting Temperature R Tungsten 1870 6500 Titanium 3865 3700 Beryllium oxide 13,400 2900 Graphite 28,700 6800 Stagnation Temperature p o p o p C V T V T C T C 2 / 2 / 2 2 = + = V (fps) To R 10,000 8,325 20,000 33,300 26,000 56,277 How Much Heat Actually Enters the Body Reentry Body Shapes http://kittyhawk.public.hq.nasa.gov/essay/ Evolution_of_Technoogy/reentry/Tech19.h tm...
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l22_reentry - the extreme heating conditions Heat sinks...

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