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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/ /Pelt OfFI61Ak WIiii ,u1L¥ considered in light of the thermal stresses that were certain to develop in a large structure placed in the fluidized bed. Reusable Single-Stage-to-Orbit Vehicles A reusable single-stage-to-orbit (SSO) vehicle will require metallic mater ials for the TPS and for much of the other hot structure. This will be challenging from the standpoint of an empty vehicle weight. With the exception of military applications, which are outside the scope of this document, empty vehicle weight is a critical metric because every additional pound of empty weight reduces the payload by the same amount (assuming a fixed propulsion capability). As mentioned earlier, the key to a lightweight vehicle is the use of design methods that integrate the TPS and the load-bearing structure to minimize structural redundancy and single-function structure (for example, a TPS that is not load bearing). Achieving this goal will require new design paradigms that incorporate true synthesis of new structural concepts. In reality, such designs can be completed only if they are based on a detailed set of mission requirements, including the number of missions and expectations for turnaround time between missions. Furthermore, operational parameters such as the value of inserting a pound of payload into orbit are needed to bound the cost of the in itial vehicle and the maintenance cost per mission (translated into cost per pound of payload). Absent such specific data, the following discusses possibilities for materials systems that can enable a reusable SSO vehicle. It is perhaps more efficient to discuss these materials according to their principal capability and the anticipated temperature regime in which they can be used most productively. This categorization method is illustrated in Table 1. Table 1. Potential Materials by Use Temperature Regime and Property Temperature Specific Specific Fatigue Fracture Creep Regime Strength Stiffness Resistance Toughness Resistance PMCs; Ambient up to 250 °C Advanced Al alloys; AMCs * ; Ti alloys; PMCs; AMCs; TMCs PMCs; AMCs; Ti Alloys; TMCs PMCs; Ti alloys Ti alloys; TMCs TMCs * 250 °Cup to 550 °C Ti alloys; TMCs TMCs Ti alloys; TMCs Ti alloys Ti alloys; TMCs Above 550 °C Ni-base alloys; Ti aluminides; Refractory metal alloys; CMCs * ; C-C Cs* Ti aluminides; CMCs; c-ccs Ni-base alloys; Refractory metal alloys Ni-base alloys; CMCs; Refractory metal alloys Ni-base alloys; Ti aluminides; CMCs; Refractory metal alloys; C-C Cs AMCs = Al matrix composites; TMCs = titanium matrix composites; CMCs = ceramic matrix composites; C-CCs = carbon-carbon composites 10 UNCLASSIFIED/ /FOR. OFFl&IAk WIiii &Ptklf
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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.