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  • 1
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    Stability characterization of diboride composites under high velocity atmospheric flight conditions (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: COMPOSITE MATERIALS
    Type: In: International SAMPE Technical Conference, 24th and International SAMPE Metals and Metals Processing Conference, 3rd, Toronto, Canada, Oct. 20-22, 1992, Proceedings. Vol. 24 (A93-53376 23-23); p. T1092-T1106.
    Format: text
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  • 2
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    Aerothermal Performance Constraints for Small Radius Leading Edges Operating at Hypervelocity (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Small radius leading edges and nosetips were used to minimize wave drag in early hypervelocity vehicle concepts until further analysis demonstrated that extreme aerothermodynamic heating blunted the available thermal protection system materials. Recent studies indicate that ultra-high temperature composite (UHTC) materials are shape stable at temperatures approaching 3033 K and will be available for use as sharp leading edge components in the near future. Steady-state aerothermal performance constraints for UHTC components are presented in this paper to identify their non-ablating operational capability at altitudes from sea level to 90 km. An integrated design tool was developed to estimate these constraints. The tool couples aerothermodynamic heating with material response using commercial finite element analysis software and is capable of both steady-state and transient analysis. Performance during entry is analyzed by transient thermal analysis along the trajectory. The thermal load condition from the transient thermal analysis is used to estimate thermal stress. Applying the tool to UHTC materials shows that steady-state, non-ablating operation of a HfB2/SiC(A-7) (A-7) component is possible at velocities approaching Earth's circular orbital velocity of 7.9 km/s at altitudes approaching 70 km.
    Keywords: Aerodynamics
    Type: Proceedings of the Eighth Annual Thermal and Fluids Analysis Workshop: Spacecraft Analysis and Design; 9.1-9.8; NASA-CP-3359
    Format: application/pdf
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  • 3
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    Aerothermal/FEM Analysis of Hypersonic Sharp Leading Edges (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Advanced hypersonic vehicles, like wave riders, will have sharp leading edges to minimize drag. These designs require accurate finite element modeling (FEM) of the thermal-structural behavior of a diboride ceramic matrix composite sharp leading edge. By coupling the FEM solver to an engineering model of the aerothermodynamic heating environment the impact of non catalytic surfaces, rarefied flow effects, and multidimensional conduction on the performance envelopes of sharp leading edges can be examined.
    Keywords: Aerodynamics
    Type: HSFF Conference; Nov 06, 1995 - Nov 09, 1995; Houston, TX; United States
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  • 4
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    The Influence of SiC on the Ablation Response of Advanced Refractory Composite Materials (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: In continuing our studies of advanced refractory composite materials we have recently completed an arc-jet test series of a diverse group of ceramics and ceramic matrix composites. The compositions range from continuous fiber reinforced ceramics to monoliths. Many of these materials contain SiC and one objective of this test series was to identify the influence of SiC oxidation mechanisms on material performance. Hence the arc heater was operated at two conditions; one in which the passive oxidation of SiC would be dominant and the other where the active oxidation of SiC would be dominant. It is shown here that the active oxidation mechanism of SiC does not dominate material performance when it is present at levels equal to or below 20 volume percent.
    Keywords: Composite Materials
    Type: 19th Annual Conference on Composites, Materials and Structures; Jan 09, 1995 - Jan 10, 1995; Cocoa Beach, FL; United States
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  • 5
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    Mechanical Properties of Continuous Fiber Reinforced Zirconium Diboride Matrix Composites (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Continuous fiber reinforced zirconium diboride matrix composites, SCS-9a-(RBSiCZrB2)matrix, are being developed for leading edge, rocket nozzle and turbine engine applications. Recently, the composite materials have been characterized for tensile properties to 1250 C, the highest temperature tested. The tensile properties are fiber dominated as the matrix is microcracked on fabrication, but favorable failure characteristic are observed. Compression and shear mechanical testing results will be reported if completed. The effects of fiber volume fraction and matrix density on mechanical properties will be discussed. The target applications of the materials will be discussed. Specific testing being performed towards qualification for these applications will be included.
    Keywords: Composite Materials
    Type: 19th Annual Conference on Composites, Materials, and Structures; Jan 08, 1995 - Jan 12, 1995; Cocoa Beach, FL; United States
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