Topic
Space Shuttle thermal protection system
About: Space Shuttle thermal protection system is a research topic. Over the lifetime, 746 publications have been published within this topic receiving 5785 citations.
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TL;DR: In this article, a detailed description of these plasma generators and an overview of the simulation regions and operation areas of the plasma wind tunnels are presented, as well as a detailed analysis of their operation areas.
Abstract: The qualification of thermal protection systems (TPS) and numerical design tools for re-entry vehicles and space probes requires the ability to understand and duplicate the prevailing complex physico-chemical phenomena, including thermal and chemical nonequilibrium near the surface of a body that enters the atmosphere of the Earth or another celestial body. At the Institut fur Raumfahrtsysteme of the University of Stuttgart, four plasma wind tunnels (PWK1-4) are in operation to simulate the thermal, aerodynamic, and chemical loads on the surface of a space vehicle. Three different plasma sources have been developed for this purpose: 1) a magnetoplasmadynamic generator for the simulation of the highenthalpy and low-pressure environment during the first phase of re-entry, 2) a thermal arcjet device for the follow-on flight path at moderate specific enthalpies and higher stagnation pressures, and 3) an inductively heated generator for basic materials experiments over a wide range of specific enthalpies and pressures. Special efforts were made to avoid electrode erosion to preclude impairing the erosion and catalytic behavior of TPS materials. A detailed description of these plasma generators and an overview of the simulation regions and operation areas of the plasma wind tunnels are presented.
132 citations
01 Jul 1980
TL;DR: In this article, the energy transfer catalytic recombination coefficient for nitrogen and oxygen recombination on the surface coating of high-temperature reusable surface insulation (HRSI) is inferred from stagnation point heat flux measurements in a hightemperature dissociated arc jet flow.
Abstract: The energy transfer catalytic recombination coefficient for nitrogen and oxygen recombination on the surface coating of high-temperature reusable surface insulation (HRSI) is inferred from stagnation point heat flux measurements in a high-temperature dissociated arc jet flow. The resulting catalytic recombination coefficients are correlated with an Arrhenius model for convenience, and these expressions may be used to account for catalytic recombination effects in predictions of the heat flux on the HRSI thermal protection system of the Space Shuttle Orbiter during reentry flight. Analysis of stagnation point pressure and total heat balance enthalpy measurements indicates that the arc heater reservoir conditions are not in chemical equilibrium. This is contrary to what is usually assumed for arc jet analysis and indicates the need for suitable diagnostics and analyses, especially when dealing with chemical reaction phenomena such as catalytic recombination heat transfer effects.
115 citations
TL;DR: In this paper, an integrated thermal protection system for spacecraft reentry based on a corrugated core sandwich panel concept fulfilling both thermal and structural functions is optimized for minimal mass, but directly optimizing both continuous geometric parameters and discrete material choices is difficult.
Abstract: An integrated thermal protection system for spacecraft reentry based on a corrugated core sandwich panel concept fulfilling both thermal and structural functions is optimized for minimal mass. We seek the optimal dimensions and the best materials, but directly optimizing both continuous geometric parameters and discrete material choices is difficult. Accordingly the optimization problem is solved in two steps. In the first step, good candidatematerialsareselectedbasedmainlyontheirthermalperformance, obtainedfromasplineinterpolation of the maximum bottom face sheet temperature. Mild simplifying assumptions allowed a reduction of the number of variables in the interpolation to two nondimensional variables. In combination with a material database, this procedure allowed a graphical comparison and selection of candidate materials. In the second step, the geometry of the integrated thermal protection system panel is optimized for different combinations of the materials identified in step one. The optimization considers both thermal and structural constraints. The lightest panel employs aluminosilicate/Nextel 720 composites for the top face sheet and web corrugation and beryllium for the bottom face sheet. For the same thermal reentry environment, this design was found to be only about 40% heavier than a reference conventional thermal protection system that does not provide any structural load carrying capabilities.
87 citations
TL;DR: In this paper, a new metallic thermal protection system concept has been designed, analyzed, and fabricated, and a specific location on a slngle-stage-to-orbit reusable launch vehicle was selected to develop loads and requirements needed to design prototype panels.
Abstract: A new metallic thermal-protection-system concept has been designed, analyzed, and fabricated. A specific location on a slngle-stage-to-orbit reusable launch vehicle was selected to develop loads and requirements needed todesign prototype panels. The design loads include ascent and entry heating rates, pressures, acoustics, and accelerations. Additional design issues were identified and discussed. An iterative sizing procedure was used to size the thermal protection system panels for thermal and structural loads as part of an integrated wall construction that included the thermal protection system and cryogenic tank structure. The panels were sized to maintain acceptable temperatures on the underlying structure and to operate under the design structural loading. Detailed creep analyses were also performed on critical components of the panels. Four 18-in.-square metallic thermal-protection-system panels were fabricated. A lightweight, thermally compliant support system to connect the thermal protection system to the cryogenic tank structure was designed and fabricated.
77 citations
TL;DR: The effect of isolated roughness on the windward surface boundary layer of the Shuttle Orbiter has been experimentally examined in the NASA Langley Research Center 20-InchMach 6 Tunnel as discussed by the authors.
Abstract: The effect of isolated roughness on the windward surface boundary layer of the Shuttle Orbiter has been experimentally examined in the NASA Langley Research Center 20-InchMach 6 Tunnel. The size and location of isolated roughness elements (intended to simulate raised ormisalignedShuttleOrbiter Thermal Protection System tiles and protruding gap ller material) were varied to systematically examine the response of the boundary layer. Global heat transfer images of the windward surface of a 0.75%-scaleOrbiter at an angle of attack of 40 deg were obtained over a range of Reynolds numbers using phosphor thermography and were used to infer the status of the boundary layer. Computationalpredictions were performed to provide both laminar and turbulent heating levels for comparison to the experimental data and to provide ow eld parameters used for investigatingboundary-layer transition correlations. A variety of roughness heights and locations along the windward centerline were used. The roughness-transition correlation, using the predicted edge parameters Re /Me and k/ , was well behaved. The off-centerline results illustrate the potential for an asymmetric transition pattern to be isolated to one side of the vehicle, thereby causing the increased yawing moments experienced in ight.
76 citations