Thermal responses of man during rest and exercise in a helium oxygen environment.
Thermal responses of man during rest and exercise in helium oxygen environment for various temperatures
HELIUM↗
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Metabolic and thermal responses of man in various He-O sub 2 and air environments.
Metabolic and thermal responses of resting man in He-O mixture or air in comfortable thermal environment
Bowers, R. W.↗
Bio-thermal responses to varied work programs in men kept thermally neutral by water cooled clothing
Physiological response to varied work programs in men wearing water cooled protective clothing
TASK COMPLEXITY↗
Metabolic and thermal responses of the rat to a helium-oxygen environment.
Rats metabolic and thermal responses to helium- oxygen environment at ambient temperatures indicate little adaptive response
Hiatt, E. P.↗
Validation of a Three-Dimensional Ablation and Thermal Response Simulation Code
The 3dFIAT code simulates pyrolysis, ablation, and shape change of thermal protection materials and systems in three dimensions. The governing equations, which include energy conservation, a three-component decomposition model, and a surface energy balance, are solved with a moving grid system to simulate the shape change due to surface recession. This work is the first part of a code validation study for new capabilities that were added to 3dFIAT. These expanded capabilities include a multi-block moving grid system and an orthotropic thermal conductivity model. This paper focuses on conditions with minimal shape change in which the fluid/solid coupling is not necessary. Two groups of test cases of 3dFIAT analyses of Phenolic Impregnated Carbon Ablator in an arc-jet are presented. In the first group, axisymmetric iso-q shaped models are studied to check the accuracy of three-dimensional multi-block grid system. In the second group, similar models with various through-the-thickness conductivity directions are examined. In this group, the material thermal response is three-dimensional, because of the carbon fiber orientation. Predictions from 3dFIAT are presented and compared with arcjet test data. The 3dFIAT predictions agree very well with thermocouple data for both groups of test cases.
Chen, Yih-Kanq↗
One-dimensional numerical analysis of the transient thermal response of multilayer insulative systems
A one-dimensional numerical analysis of the transient thermal response of multilayer insulative systems has been developed. The analysis can determine the temperature distribution through a system consisting of from one to four layers, one of which can be an air gap. Concentrated heat sinks at any interface can be included. The computer program based on the analysis will determine the thickness of a specified layer that will satisfy a temperature limit criterion at any point in the insulative system. The program will also automatically calculate the thickness at several points on a vehicle and determine total system mass.
Pittman, C. M.↗
The evolutionary thermal response of a white dwarf to compressional heating by periodic dwarf nova accretion events
The thermal response of the underlying white dwarf in a cataclysmic variable to the periodic deposition of mass by a dwarf nova accretion event is simulated with a quasi-static stellar evolution code incorporating time variable accretion. After accretion at rates typical of dwarf nova outbursts (approx. 10(exp -7) to 10(exp -8)/yr) for outburst durations of days to 2 weeks, the radial infall is shut off and the evolution of the white dwarf is followed during dwarf nova quiescence. The matter is assumed to accrete softly with the same entropy as the white dwarf outer layers. In some sequences accretion is resumed and shut off repeatedly at intervals of months to simulate the thermal evolution of the white dwarf in typical dwarf novae such as SS Cygni and U Geminorum, between successive dwarf nova outbursts. Thermal timescales for white dwarf cooling following a given dwarf nova outburst depend upon the accretion rate, outburst duration, and white dwarf mass; they are nominally in the range 0.2-0.8 years for parameters typical of dwarf novae (white dwarf masses in the range 1.2-0.6 solar mass, outburst accretion rates in the range 1 x 10(exp -7)-10(exp -8) solar mass/yr, outburst durations in the range 7-14, days and quiescent intervals of 30-300 days). If the e-folding timescale of the white dwarf cooling is shorter than the quiescent interval bewteen outbursts, then the effect of compressional heating is too small to be observationally detectable.
Sion, Edward M.↗
Research study: Thermal curtain permeability and thermal response test for SRB reentry
Nine inch diameter samples of the material which will provide thermal and acoustic protection between the nozzle and outer skirt on the space shuttle solid rocket boosters were subjected to heating tests to determine the porosity of the material and the thermal response to a step change in heating. For the porosity measurements a steady state flow of air at 70 F, 500 F, and 1000 F was passed through a sample of the curtain material and measurements of the flow rates were made at different pressure drops across the sample. For the transient measurements, a sample of the curtain material was subjected to a step change in temperature as air was passed through the sample. Measurements of the heat flow through the sample were made as a function of time after the input of the heat pulse. The sample consisted of three layers of curtain panels. Each panel was made of combinations of quartz and fiberglass cloth between which a fiberfrax filler material had been stitched. The hardware design and test procedures were described. Data are provided in engineering units for the flow conditions and and temperatures at which measurements were conducted.
Fuller, C. E.↗
A coupled computer code for the transient thermal response and ablation of non-charring heat shields and nose tips
Coupled computer code for transient thermal response and ablation of noncharring heat shields and nose tips
Anderson, L. W.↗
Thermal response of integral multicomponent composites to a high-energy aerothermodynamic heating environment with surface temperature to 1800 K
Laminated composite insulations developed for potential use on advanced spacecraft operating between GEO and LEO were tested in an aerothermodynamic environment simulating an AOTV aerobraking maneuver (altitude 82.3 km and velocity = 9.0 km/s). Comparisons are discussed between these data and predictions of in-depth temperature response using dynamical thermal conductivity values to 2000 K.
Stewart, David A.↗
A study of thermal response of the lunar surface at the landing site during the descent of the Lunar Excursion Module /LEM/
Thermal response of lunar surface at landing site due to radiative and convective heat transfer from LEM exhaust nozzle
LUNAR EXCURSION MODULE /LEM/↗
Quantitative Examination of Corrosion Damage by Means of Thermal Response Measurements
Two computational methods are presented that enable a characterization of corrosion damage to be performed from thermal response measurements derived from a standard flash thermographic inspection. The first is based upon a one dimensional analytical solution to the heat diffusion equation and presumes the lateral extent of damage is large compared to the residual structural thickness, such that lateral heat diffusion effects can be considered insignificant. The second proposed method, based on a finite element optimization scheme, addresses the more general case where these conditions are not met. Results from an experimental application are given to illustrate the precision, robustness and practical efficacy of both methods.
Rajic, Nik↗
Influence of damage on the thermal response of graphite-epoxy laminates
A constrained-displacement finite-element approach for studying the influence of transverse cracks and delaminations on the thermal response of laminated composites is presented. Typical results are given in the form of percent-retention curves for the coefficient of thermal expansion as a function of crack density. Cross-ply and quasi-isotropic T300/5208 graphite-epoxy laminates are considered. It is shown that transverse cracks can have a significant influence on the coefficient of thermal expansion, but delaminations located symmetrically about the laminate midplane have no influence on thermal expansion.
Adams, D. S.↗
Thermal Response of Cooled Silicon Nitride Plate Due to Thermal Conductivity Effects Analyzed
Lightweight, strong, tough high-temperature materials are required to complement efficiency improvements for next-generation gas turbine engines that can operate with minimum cooling. Because of their low density, high-temperature strength, and high thermal conductivity, ceramics are being investigated as materials to replace the nickelbase superalloys that are currently used for engine hot-section components. Ceramic structures can withstand higher operating temperatures and a harsh combustion environment. In addition, their low densities relative to metals help reduce component mass (ref. 1). To complement the effectiveness of the ceramics and their applicability for turbine engine applications, a parametric study using the finite element method is being carried out. The NASA Glenn Research Center remains very active in conducting and supporting a variety of research activities related to ceramic matrix composites through both experimental and analytical efforts (ref. 1). The objectives of this work are to develop manufacturing technology, develop a thermal and environmental barrier coating (TBC/EBC), develop an analytical modeling capability to predict thermomechanical stresses, and perform a minimal burner rig test on silicon nitride (Si3N4) and SiC/SiC turbine nozzle vanes under simulated engine conditions. Moreover, we intend to generate a detailed database of the material s property characteristics and their effects on structural response. We expect to offer a wide range of data since the modeling will account for other variables, such as cooling channel geometry and spacing. Comprehensive analyses have begun on a plate specimen with Si3N4 cooling holes.
Baaklini, George Y.↗
Analysis of the thermal response of high density phenolic nylon on a spacecraft launched by the Pacemaker vehicle system
Ablation sensors and thermocouples used to measure thermal response of phenolic-nylon material of spacecraft launched by Pacemaker vehicle system
Witte, W. G.↗
A simplified analytical solution for thermal response of a one-dimensional, steady state transpiration cooling system in radiative and convective environment
A simplified analytical method for calculation of thermal response within a transpiration-cooled porous heat shield material in an intense radiative-convective heating environment is presented. The essential assumptions of the radiative and convective transfer processes in the heat shield matrix are the two-temperature approximation and the specified radiative-convective heatings of the front surface. Sample calculations for porous silica with CO2 injection are presented for some typical parameters of mass injection rate, porosity, and material thickness. The effect of these parameters on the cooling system is discussed.
Kubota, H.↗
Thermal Response and Ablation Programs for TPS Sizing Computation
The computer programs developed at NASA Ames Research Center for TPS sizing computation have been applied to many NASA's space missions, such as Mars Pathfinder, StarDust, Mars 2001, DS-II, and Saturn Entry Probe. These computer programs include FIAT (Fully Implicit Ablation and Thermal Response Program, MAT (Multi-component Ablation Thermochemistry Program), TPSX (Thermal Protection Systems Expert & Material Properties Database), and TPSGui (Thermal Protection Systems Graphical User Interface). For most planetary missions, the aerothermodynamics and material response are strongly coupled; thus a closed loop iteration technique between the FIAT and CFD (Computational Fluid Dynamics) codes has been developed to obtain the high fidelity bench mark TPS sizing solution. The computer codes and predictive methods are presented and discussed in detail.
Chen, Y. K.↗
Determination of Flaw Size and Depth From Temporal Evolution of Thermal Response
Simple methods for reducing the pulsed thermographic responses of flaws have tended to be based on either the spatial or temporal response. This independent assessment limits the accuracy of characterization. A variational approach is presented for reducing the thermographic data to produce an estimated size for a flaw that incorporates both the temporal and spatial response to improve the characterization. The size and depth are determined from both the temporal and spatial thermal response of the exterior surface above a flaw and constraints on the length of the contour surrounding the delamination. Examples of the application of the technique to simulation and experimental data acquired are presented to investigate the limitations of the technique.
Winfree, William P.↗