Temperature constraints at the sharp leading edge of a Crew Transfer Vehicle

Kontinos, Dean

doi:10.2514/6.2001-2886

Cited by 35 publications

(16 citation statements)

References 11 publications

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“…Extensive work in the 1960s and 1970s by ManLabs for the Air Force showed potential for HfB 2 and ZrB 2 for use as nosecones and leading edge materials (Clougherty, Kaufman, Kalish, Hill, Peters, Rhodes et al)…”

Section: !mentioning

confidence: 99%

“…2 The properties of most interest for the application are therefore high thermal conductivity (especially controlled and/or tailorable in specific directions), high fracture toughness and mechanical strength, especially at elevated temperatures, and good oxidation resistance in reentry conditions. Strong covalent bonding is responsible for the high melting points, moduli, and hardness of the UHTC family of materials.…”

Section: Introductionmentioning

confidence: 99%

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Recent Developments in Ultra High Temperature Ceramics at NASA Ames

Johnson

Gasch²,

Lawson³

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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NASA Ames is pursuing a variety of approaches to modify and control the microstructure of UHTCs with the goal of improving fracture toughness, oxidation resistance and controlling thermal conductivity. The overall goal is to produce materials that can perform reliably as sharp leading edges or nose tips in hypersonic reentry vehicles. Processing approaches include the use of preceramic polymers as the SiC source (as opposed to powder techniques), the addition of third phases to control grain growth and oxidation, and the use of processing techniques to produce high purity materials. Both hot pressing and field assisted sintering have been used to make UHTCs. Characterization of the mechanical and thermal properties of these materials is ongoing, as is arcjet testing to evaluate performance under simulated reentry conditions. The preceramic polymer approach has generated a microstructure in which elongated SiC grains grow in the form of an in-situ composite. This microstructure has the advantage of improving fracture toughness while

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Section: !mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Recent Developments in Ultra High Temperature Ceramics at NASA Ames

Johnson

Gasch²,

Lawson³

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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show abstract

“…Ultra-high temperature structure components of supersonic flight vehicles, such as nose caps, sharp leading edges and rocket nozzles, operate in extreme environment with high heat flux and high-pressure gas flow [1,2]. At over 2000°C in air, the use of traditional C/C, C/silicon carbide (SiC) composites or other new materials is limited because of rapid oxidation and ablation [3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Effects of polymer derived SiC interphase on the properties of C/ZrC composites

Chen

Zhang

et al. 2014

Materials & Design

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“…Thermal protection systems (TPS) of hypersonic flight vehicles and atmospheric re-entry vehicles, such as sharp leading edges and nose caps, serve in extreme environments with high temperature (beyond 2000°C), high heat flux, high enthalpy, high pressure, severe thermal shock, and perhaps high velocity ceramic particle erosion [1][2][3]. The conventional high temperature materials, such as refractory alloys, graphite, C/C and C/SiC composites, can hardly withstand the extreme oxidation and ablation environments for long time [3].…”

Section: Introductionmentioning

confidence: 99%