Materials & Coatings

Nanoencapsulated Aerogels Produced by Monomer Vapor Deposition and Polymerization

This technology provides a method for making strong and lightweight aerogels with insulating properties. The nano-encapsulated aerogel technology has the strength and insulation properties for many applications. The Johnson Space Center researched methods to coat aerogel insulation in order to make it better able to withstand vibration, mechanical compression and flexure, and other environmental damage. This NASA-developed nanoencapsulated aerogel technology is a method for increasing the strength of the aerogel through a coating process while maintaining its insulating properties. With this ruggedizing process, the coating of the aerogel reduces mechanical damage, enabling its practical use in products that might not be suitable with the more fragile aerogel. The basic coating can also shield it from adsorbing humidity or other gases, which could otherwise bind to the substance and change its properties. Functionalized coatings could be developed to adsorb certain gases if that is desired. Aerogel’s low density and extremely low thermal conductivity make it useful as a lightweight, volume-efficient insulation material. Encapsulating the aerogel expands its ability to be incorporated into products that are exposed to vibration and compression during manufacture, shipping, or use. It can also improve its flexibility, opening up a range of new product uses.

Posted in: Briefs, Materials

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Insulative Carbon Fiber Systems for Aerospace Applications

New insulative carbon-fiber composite systems have been developed for use in structural and thermal applications for the aerospace vehicle interface. The sandwich-type composite structure, including carbon fiber and aerogel blanket materials, is based on the previously disclosed family of hybrid laminate composites. Offering unique and tailorable combinations of structural and thermal properties, these insulative carbon fiber systems can be used in vehicle shroud and thermal protection system applications at the aerodynamic interface plane, panels between stages, or fairings for spacecraft equipment space of space launch vehicles. The novel, lightweight, fiber composite laminate system with reduced heat transfer also has increased impact resistance at low temperatures.

Posted in: Briefs, Materials

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Optimizing EBM Alloy 718 Material for Aerospace Components

Electronic Beam Melting (EBM) is a leading AM technology that aerospace companies are implementing for production. To leverage the capabilities of EBM, new materials such as Alloy 718 have been developed. Alloy 718 is a nickel-chromium based super alloy ideal for high temperature and corrosive environments, with excellent mechanical properties at elevated temperatures.

Posted in: White Papers, Aerospace, Manufacturing & Prototyping, Materials

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In-Situ Formation of Reinforcement Phases in Ultra-High- Temperature Ceramic Composites

This technology could be used in re-entry vehicles, reusable launch vehicles, hypersonic vehicle leading edges, and commercial spacecraft.Future-generation materials for use on space transportation vehicles require substantial improvements in material properties leading to increased reliability and safety, as well as intelligent design to allow for current materials to meet future needs. Ultra-high-temperature ceramics (UHTC), composed primarily of metal diborides, are candidate materials for sharp leading edges on hypersonic re-entry vehicles. NASA has demonstrated that it is possible to form high-aspect-ratio reinforcement phases in-situ during the processing step for both ceramic composites and UHTCs. Initial characterization of these systems has demonstrated that crack deflection along the matrix-reinforcement interface is observed yielding a system of improved toughness over the baseline system, leading to improved mechanical performance. The reinforced composites should therefore reduce the risk of catastrophic failure over current UHTC systems.

Posted in: Briefs, Coatings & Adhesives, Materials

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Multi-Phase Ceramic System

Bearing surfaces are typically either metal-on-metal (MOM), ceramic-on-ceramic (COC), or metal-on-polyethylene (MOP). MOM and MOP couplings have the drawback that metallic or polyethylene particles can sometimes separate from the couplings, which can cause significant problems, particularly in a hip or joint replacement. COC couplings are less likely to lose particles due to wear, which makes them more biocompatible, but they are more susceptible to fracture. COC couplings also have a tendency to squeak as they move. Innovators at NASA’s Glenn Research Center have developed a technique using rare earth elements to fabricate a dual-phase ceramic composite that combines a wear-resistant phase and a solid-state lubricant phase. The result is a coupling material that, compared to currently used materials, exhibits a tenfold reduction in the friction coefficient, a sixfold reduction in wear, and a significant reduction in debris caused by wear. Glenn’s groundbreaking rare-earth aluminate composite has considerable potential, not only in biomedical applications, but also in commercial and industrial sectors.

Posted in: Briefs, Ceramics, Materials

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Minimally Machined HoneySiC Panels and T300 HoneySiC

The materials are intended for low areal density and near-zero CTE optomechanical structures.The primary purpose of this work is to develop and demonstrate technologies to manufacture ultra-low-cost precision optical systems for very large x-ray, UV/optical, or infrared telescopes.

Posted in: Briefs, Coatings & Adhesives, Materials

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Flexible Volumetric Structure

These composite elastic skins can be tailored for specific applications.NASA’s Langley Research Center has developed composite elastic skins for covering shape-changing (morphable) structures. These skins are intended especially for use on advanced aircraft that change shapes in order to assume different aerodynamic properties. Examples of aircraft shape changes include growth or shrinkage of bumps, conformal changes in wing planforms, cambers, twists, and bending of integrated leading and trailing-edge flaps. Prior to this invention, there was no way of providing smooth aerodynamic surfaces capable of large deflections while maintaining smoothness and sufficient rigidity.

Posted in: Briefs, Coatings & Adhesives, Materials

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