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This Defense Intelligence Reference Document, DIA-08-0912-008, is dated 12 January 2010. It was prepared by the Defense Warning Office's Acquisition Support Division at the Defense Intelligence Agency as one of a series of FY 2009 technology reports under the Advanced Aerospace Weapon System Applications program. It reviews materials for launch vehicles, space vehicles and reusable rocket engines, including aluminum alloys, polymer and metal matrix composites, titanium and nickel alloys, and titanium aluminides. It concludes that newer materials and integrated design could improve on the space shuttle.
From the source:Release of 2026-09-18 Incident: 1/12/10, Las Vegas, Nevada. Released with redactions. This document is a Defense Intelligence Reference Document (DIRD), a technical reference format used by the Defense Intelligence Agency (DIA) to capture baseline knowledge on a specific topic for later analytic use. DIRDs are best understood as reference and synthesis products rather than as original research. It is one of 38 DIRDs produced under the Advanced Aerospace Weapon System Applications Program (AAWSAP) between 2009 and 2011. Because AAWSAP’s scope permitted a broad range of supporting topics, not every DIRD in the series directly concerns aerospace systems or future threat assessment. The following summary reflects the DIRD’s scope and framing at the time of writing and should not be read as implying current validation of the concepts discussed. This DIRD surveys the structural materials needed for advanced aerospace platforms and argues that material choice cannot be separated from overall vehicle design, because launch vehicles, space vehicles, reusable systems, and propulsion hardware each face different temperature, durability, weight, and manufacturing constraints. The report reviews a range of candidate material classes, including advanced aluminum alloys; polymer-, aluminum-, and titanium-matrix composites; titanium alloys; nickel-base alloys; refractory metals; ceramic-matrix composites; carbon-carbon composites; and titanium aluminides. It emphasizes that balancing performance against practical limits such as fabrication methods, cost, inspection, contamination control, and service environment remains a major challenge. Its overall conclusion is that many promising materials exist, but their usefulness depends on application-specific tradeoffs and on closer integration of material selection with design and manufacturing, with some systems judged to be more valuable targets for development than others.
UNCLASSIFIED/ J'FOR OFFI@IAl W&liii 9PU.Y design of a cryopump potentially can benefit from these new materials and from abandoning the use of notched strength as a design paradigm . The combustion chamber of a rocket engine is made from a copper alloy and is cooled by passing liquid hydrogen through channels in the outer wall. The space shuttle main engine combustion chamber is made of NARloy-Z, a Cu-3%Ag-0.5%Zr alloy that has excellent thermal conductivity and better strength than the commercially available Cu- 0.15%Zr alloy known as AMZIRC. While a lighter combustion chamber would be welcome, developing hydrogen-resistant turbine materials would be a much better use of available rocket engine alloy development resources. SUMMARY AND RECOMMENDATIONS This document has attempted to review a range of materials that may have promise for all aspects of aerospace platforms. Because of the breadth of this topic, discussion has focused on opportunities and associated risks, but with little technical detail. Practical issues such as manufacturing capabilities and costs and the availability of materials also have been addressed where appropriate. Another recurring issue is the ability to achieve better design efficiency through a design synthesis process that concurrently treats form, fit and function, manufacturing capability, and materials capability as equally important design constraints. Although this approach has yet to be successfully used for a major high-performance structure project, engineering is nearing a state of development where it may now be feasible. If the space shuttle is used as a benchmark, it is clear that numerous opportunities will exist to improve structural efficiency. This possibility reflects the progress made since the shuttle and its engine were designed. Improved durability and reduced operating cost also are possible. The issue of long lead time holding back these improved design methods is most often one of timely availability of new, attractive materials that are mature enough to be used in a system without increasing the risk of failure. The materials community is actively developing and using computational models and simulation methods to address this concern. Despite some progress, further advances are required to bring computational materials engineering to the desired level of maturity. 1. Hatch, J. ed . Aluminum, Properties and Physical Metallurgy. American Society for Metals, 1984. 2. Chawla K. Composite Materials, Science and Engineering 2nd edition. Springer, 1998. 3. Baker, A., Dutton, S. and Kelly, D. Composite Materials for Aircrah Structures 2nd edition. AIAA, 2002. 4. Lutjering, G and Williams, J. Titanium, 2nd edition . Springer, 2007. 5. Sims, C. and Hagel, W. The Superalloys. Wiley, 1972. 6. Mishra, R. and Ma, Z. Friction Stir Welding and Processing, Materials Science and Engineering. v .50, pp. 1-78, 2005. 22 UNCLASSIFIED/fFOR: OFFIQl.\k Uili Qfslk¥
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Official release, from the pursue collection. The PDF is mirrored here; the original link is above. 27 pages are in the text index: search them above, or from the library's search.