Hypersonic airbreathing vehicle visions and enhancing technologies

Hunt, J. L.; Lockwood, Mary Kae; Petley, D. H.; Pegg, R. J.

doi:10.1063/1.51938

Cited by 5 publications

(2 citation statements)

References 9 publications

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“…4 From the perspective of reducing the expense of orbital transportation, there is interest in hypersonic vehicles with reusable TPS including Reusable Launch Vehicles (RLVs), 6, 7 miliary spaceplane, 8 spaceplanes for tourism, 9 space trucks, 10 suborbital package delivery vehicles, 11 and hypersonic air breathing vehicles. 12 Material type is a concern. Metallics are robust and waterproof, but heavy and of either limited temperature capability or with poor environmental resistance.…”

Section: Introductionmentioning

confidence: 99%

Analysis of Reusable Integrated Thermal Protection Panel Elements with Various Insulating Core Options

Jiang

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A finite element analysis (FEA) tool was developed for evaluating the effects of basic design features and materials choices on a basic panel for an Integrated Thermal Protection System (ITPS). A set of practical optimization problems regarding different insulating core options was solved by utilizing the commercial FEA software ANSYS. The core options represent five different layouts for the insulation layer: bonded/unbonded foam with blade stiffeners, bonded/unbonded foam with hat-section stiffeners, and simple bonded foam. A conventional design with parasitic insulation tiles was also analyzed as a reference. Figures of Merit (FoMs) identifying the combination of load-bearing capability and the mass of the ITPS were defined. Using these FoMs, the optimization objective functions were created so as to consider both the insulation performance and structural strength and stiffness. Some examples of FoMs of each design candidate were optimized and compared with each other to identify the best structural layout. Finally, the effects of materials properties on the best core options were investigated.

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Section: Introductionmentioning

confidence: 99%

Analysis of Reusable Integrated Thermal Protection Panel Elements with Various Insulating Core Options

Jiang

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Proposed vehicles include the Reusable Launch Vehicle (RLV),' military spaceplane: spaceplanes for t o~r i s m ,~ space trucks: suborbital package delivery vehicles: and hypersonic airbreathing vehicles. 6 One of the key technologies required by all of these vehicles is a reusable, low maintenance, light weight thermal protection system (TPS). Although the primary function of a TPS is to protect the vehicle from the effects of aerodynamic heating, the operational capability and system weight also have significant impact on vehicle performance.…”

Section: Introductionmentioning

confidence: 99%

Parametric weight comparison of current and proposed thermal protection system (TPS) concepts

David

Martin

Max

1999

33rd Thermophysics Conference

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A parametric weight assessment of advanced metallic panel, ceramic blanket, and ceramic tile thermal protection systems (TPS) was conducted using an implicit, one-dimensional (1 -D) thermal finite element sizing code. This sizing code contained models to account for coatings, fasteners, adhesives, and strain isolation pads. Atmospheric entry heating profiles for two vehicles, the Access to Space (ATS) rocket-powered single-stage-to-orbit (SSTO) vehicle and a proposed Reusable Launch Vehicle (RLV), were used to ensure that the trends were not unique to a particular trajectory. Eight TPS concepts were compared for a range of applied heat loads and substructural heat capacities to identify general trends. This study found the blanket TPS concepts have the lightest weights over the majority of their applicable ranges, and current technology ceramic tiles and metallic TPS concepts have similar weights. A proposed, state-of-the-art metallic system which uses a higher temperature alloy and efficient multilayer insulation was predicted to be significantly lighter than the ceramic tile systems and approaches blanket TPS weights for higher integrated heat loads.

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Supersonic Combustion of Kerosene/H₂-Mixtures in a Model Scramjet Combustor

Gruenig

Mayinger

1999

Combustion Science and Technology

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Hypersonic airbreathing vehicle visions and enhancing technologies

Cited by 5 publications

References 9 publications

Analysis of Reusable Integrated Thermal Protection Panel Elements with Various Insulating Core Options

Analysis of Reusable Integrated Thermal Protection Panel Elements with Various Insulating Core Options

Parametric weight comparison of current and proposed thermal protection system (TPS) concepts

Supersonic Combustion of Kerosene/H₂-Mixtures in a Model Scramjet Combustor

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Hypersonic airbreathing vehicle visions and enhancing technologies

Cited by 5 publications

References 9 publications

Analysis of Reusable Integrated Thermal Protection Panel Elements with Various Insulating Core Options

Analysis of Reusable Integrated Thermal Protection Panel Elements with Various Insulating Core Options

Parametric weight comparison of current and proposed thermal protection system (TPS) concepts

Supersonic Combustion of Kerosene/H2-Mixtures in a Model Scramjet Combustor

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Supersonic Combustion of Kerosene/H₂-Mixtures in a Model Scramjet Combustor