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Metallic materials for the space shuttle

Published online by Cambridge University Press:  04 July 2016

A. A. Tavassoli
A. A. Tavassoli*
Affiliation:
National Research Council Postdoctoral ResidentResearch Associate at Marshall Space Flight Center, NASA
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Extract

One of the great challenges of our time lies in the exploration of space. Part of this challenge has already been fulfilled but, up to this date, the transport of men and materials has been accomplished by means of expendable booster systems. In order to meet this challenge effectively, a new, fully reusable transportation system has been conceived which will be dramatically lower in overall cost than present-day launch systems. The proposed space shuttle is a fully reusable spacecraft consisting of a booster and an orbiter. A key factor in the design of the space shuttle is the selection and development of materials. Many current materials which have been widely and successfully used in space vehicles were developed for the most part with only a single short-time use requirement. The reusable, long-life requirements of the shuttle vehicle necessitates re-evaluation of the suitability of existing materials for this distinctly more demanding task for materials.

Type
Research Article
Information
The Aeronautical Journal , Volume 76 , Issue 735 , March 1972 , pp. 152 - 156
Copyright
Copyright © Royal Aeronautical Society 1972 

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References

1. McDonnell Douglas Corporation. Space shuttle programme, phase B final report, MDC EO308, Part II, March 1971.Google Scholar
2. Black, W. E. Radiative thermal protection systems development for manoeuverable re-entry spacecraft, GDC-ERR-1272, Convair Division, General Dynamics, February 1969.Google Scholar
3. Sprowls, D. O. and Brown, R. H. Resistance of wrought high strength aluminum alloys to stress corrosion, Alcoa Research Labs., Chemical Metallurgy Division, Aluminum Company of America, 1962.Google Scholar
4. Brown, W. F. Review of development in plane strain fracture toughness testing, NASA/ASTM-STP 463, 1970.Google Scholar
5. Materials Division. Selection of state-of-the-art materials for space shuttle thermal protection, NASA TMX-64533, 10th July 1970.Google Scholar
6. Coyne, J. E. and Sparks, R. B. New titanium alloys for structural forgings, Wayn-Gordon Company, AIAA/ASME 7th Structures and Materials Conference, Cocoa Beach, Fl. 18th-20th April 1966.Google Scholar
7. Aircraft Designers Handbook for Ti and Ti Alloys, AFML-TR-67-142, Defense Information Center, Battelle Memorial Institute, March 1967.Google Scholar
8. Moon, D. P., Simon, R. C. and Favor, R. J. The elevated-temperature properties of selected superalloys, ASTM Data Series DS 7-S1, July 1968.Google Scholar
9. Decker, R. F. Strengthening mechanisms in nickel-base superalloys, Steel Strengthening Mechanisms Symposium, Zurich, Switzerland, 5th and 6th May 1969.Google Scholar
10. Materials Systems Division. Materials for consideration in space shuttle thermal protection system, Union Carbide Corp., March 1969.Google Scholar
11. TDNiCr a Dispersion Strengthened Alloy, Tech. Bulletin TD 007-2, Fansteel Corp., 1968.Google Scholar
12. Johnson, R. and Kilpatrick, D. H. Dispersion-strengthened metal structural development, AFFDL-TR-68—130. Part I, DAC-62342, 1st February 1967 to July 1968, Contract F33615-67-C-1319, McDonnell Douglas Astronautics Company, WD, 1968.Google Scholar
13. Lessmann, G. G. Determination of the weldability and elevated temperature stability of refractory metal alloys, final report, Tasks I and II weldability of refractory metal alloys. WANL-PR-(P)-013, Westinghouse Astro-nuclear Laboratory, October 1969.Google Scholar
14. MIL-HDBK-5A, Metallic materials and elements for aerospace vehicle structures, MAAE/WPAFE, December 1968.Google Scholar
15. Mayer, L. W. Alcoa aluminum alloy 2219, Green Letter 176. Aoplication Engineering Division, Aluminum Company of America, November 1966.Google Scholar
16. Space Shuttle Data, V. Ill Structures, materials and thermal protection system, Space System Division, Lockheed Missiles & Space Company, LMSC-A955317A, 12th September 1969.Google Scholar
17. Fansteel, FS-85 Metal Technical Data Bulletin, TD-823-B, Fansteel Metallurgical Corporation, 29th October 1962.Google Scholar
18. Titran, R. H. and Hall, R. W. High temperature creep behaviour of a columbium alloy, FS-58, NASA TN D-2885, June 1965.Google Scholar
19. Beuhring, V. F. and Wagner, H. J. Ed. Structural stability in superalloys, DMIC Tech. Note, September 1968.Google Scholar
20. Cole, F. W., Padden, J. B. and Spencer, A. R. Oxidation resistant materials for transpiration cooled gas turbine blades—II, wire specimen tests, NASA CR-1184, Bendix Corp. to NASA—LeRC on Contract NAS3-7269, September 1968.Google Scholar
21. Davis, J. W. Effect of multiple re-entry on the reuse properties of superalloys, Presentation at Marshall Space Flight Center, NASA, Materials and Processes, McDonnell Douglas Astronautics Co., ED. 1971.Google Scholar
22. Frank, R. G. Recent advances in columbium alloys. Machlin, I., Begley, R. T. and Weisert, E. D., (Ed). Refractory metal alloys, metallurgy and technology, Plennum Press, p. 344, 1968.Google Scholar
23. Tavassoli, A. A. Development of columbium alloy WC-3015. NASA TN-D 6390, July 1971.Google Scholar
24. Metcalfe, A. G. and Stetson, A. R. Interaction incoated refractory metal systems, same as ref. 17, p. 121.Google Scholar
25. Fitzgerald, B. Evaluation of the fused slurry silicide coating considering component design and reuse, Contract USAF F33615-67-C-1674, Progress Reports 1-3, McDonnell Douglas Astronautics Company, 1st July 1968 to 15th July 1969.Google Scholar
26. Fitzgerald, B. Evaluation of the fused slurry silicide coating considering component design and reuse. Contract USAF F33615-(67, 68, 69)-C-1574, McDonnell Douglas Astronautic Company, 15th July 1969.Google Scholar
27. Kohl, F. J. and Strews, C. A. Vaporization of chromium oxide from the surface of TDNiCr under oxidizing condition, NASA TMX-52879, August 1970.Google Scholar