Research study to provide concepts of panel attachment mechanisms suitable for refurbishable panel application
Panel attachment mechanism for replaceable heat shield system of manned lifting entry vehicle
PANEL↗
SEARCH · Engineering Papers
Results for “heating systems”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Zero-G hydrogen tank venting systems.
Low gravity liquid hydrogen tank venting, considering systems with heat exchange for space missions
PROPELLANT TANK↗
Energy in space - Program planning for space power system technology.
Space power generation systems converting heat or light energy to electricity, noting energy storage
Woodward, W. H.↗
Two systems developed for purifying inert atmospheres
Two systems, one for helium and one for argon, are used for purifying inert atmospheres. The helium system uses an activated charcoal bed at liquid nitrogen temperature to remove oxygen and nitrogen. The argon system uses heated titanium sponge to remove nitrogen and copper wool beds to remove oxygen. Both use molecular sieves to remove water vapor.
Foster, M. S.↗
Proceedings of the Third Southeastern Seminar on Thermal Sciences
Report contains papers discussing rheology, low temperature thermodynamics with emphasis on the helium system, aerodynamic heating, and thermophysics research at Marshall Space Flight Center. Abstracts of selected research and development programs covering entire spectrum of thermal sciences are included.
Source record↗
A microwave feeding system for extended space missions
Microwave feeding system for heating and cooking prepackaged meals during extended space missions
Gould, J. W.↗
Inexpensive system protects megawatt resistance-heating furnace against high-voltage surges
Coolant gas extinguishes arcing across the break in a heater element. Air-gap shunt which bypasses high voltage impressed across the circuit prevents damage if the resistance elements break and open the inductive circuit.
Stearns, E. J.↗
Simulation of passive thermal behavior of a cooling biological system - Entry into hibernation
Thermal behavior simulation of cooling biological system, describing heat generation and transfer at normothermic to hibernating body temperatures with mathematical model
Gray, E. W.↗
Space technology applicable to hybrid vehicle batteries
Nickel-zinc batteries for use in hybrid heat engine/electric systems of low pollutant passenger cars, increasing service life by aerospace technology
Schwartz, H. J.↗
Thermal induced flow oscillations in heat exchangers for supercritical fluids
Analytical model has been developed to predict possible unstable behavior in supercritical heat exchangers. From complete model, greatly simplified stability criterion is derived. As result of this criterion, stability of heat exchanger system can be predicted in advance.
Friedly, J. C.↗
Flight test of carbon-phenolic on a spacecraft launched by the pacemaker vehicle system
Carbon-phenolic material consisting of 50 percent carbon fibers and 50 percent phenolic resin was flight tested on a recoverable spacecraft launched by the Pacemaker vehicle system. The heat shield of the spacecraft was fabricated so that the carbon fibers in the ablator material had different orientations over several areas of the spacecraft. The environment in which the spacecraft was tested produced heating rates on the hemispherical nose up to 13.6 MW/sq m (1200 Btu/sq ft/sec) and stagnation-point pressures up to 1.27 MN/sq m (12.5 atm). The experimental results are presented. Due to high heating rates and possible spallation and mechanical char removal the greatest mass loss occurred in the nose region. Essentially uniform surface recession and char thickness were observed on the conical section of the spacecraft. A comparison of measured heating rates with computed turbulent and laminar heating rates, as well as measurements of sound-pressure fluctuations in the boundary layer obtained with acoustic sensors, indicated that the boundary layer underwent transition. The acoustic sensor provides an interesting new data form for the general study of boundary-layer transition for free-flight investigations.
Walton, T. E., Jr.↗
Laboratory prototype flash evaporator
A laboratory prototype flash evaporator that is being developed as a candidate for the space shuttle environmental control system expendable heat sink is described. The single evaporator configuration uses water as an evaporant to accommodate reentry and on-orbit peak heat loads, and Freon 22 for terrestrial flight phases below 120,000 feet altitude. The design features, fabrication techniques used for the prototype unit, redundancy considerations, and the fluid temperature control arrangement are reported in detail. The results of an extensive test program to determine the evaporator operational characteristics under a wide variety of conditions are presented.
Gaddis, J. L.↗
Theory and design of variable conductance heat pipes: Steady state and transient performance
Heat pipe technology pertinent to the design and application of self-controlled, variable conductance heat pipes for spacecraft thermal control is discussed. Investigations were conducted to: (1) provide additional confidence in existing design tools, (2) to generate new design tools, and (3) to develop superior variable conductance heat pipe designs. A computer program for designing and predicting the performance of the heat pipe systems was developed.
Edwards, D. K.↗
Post impact behavior of mobile reactor core containment systems.
In the future, nuclear assemblies containing fission products will be transported at high speeds. An example is a reactor supplying power to a large subsonic airplane. In this case an accident can occur resulting in a ground impact at speeds up to 1000 ft/sec. This paper analyzes the containment vessel temperatures after impact and attempts to understand the design variables that affect the post impact survival of the system. The heat transfer analysis includes conduction, radiation, and convection in addition to the core material heats of fusion and vaporization under partial-burial conditions. Also, included is the fact that fission products vaporize and transport radially outward and condense on cooler surfaces, resulting in a moving heat source.
Puthoff, R. L.↗
Electrostatically controlled heat shutter
Electrically controlled chamber filled with inert gas efficiently removes heat from heat-generating components. System can be reversed to bring heat from external source to component.
Derr, L. J.↗
Thermal conductivity of heterogeneous mixtures and lunar soils
The theoretical evaluation of the effective thermal conductivity of granular materials is discussed with emphasis upon the heat transport properties of lunar soil. The following types of models are compared: probabilistic, parallel isotherm, stochastic, lunar, and a model based on nonlinear heat flow system synthesis.
Vachon, R. I.↗
Reflectance and unsteady temperature distribution of diffuse reflectors
The applicability of a previously derived solution of the Kubelka-Munk differential equations for the reflectance of an absorbing and scattering material for the case of a zero absorption coefficient to the description of the reflectance of a weakly absorbing, highly scattering material is examined. A solution for the transient heating of a one-dimensional volume reflector is obtained, and the error incurred in the use of the zero absorption coefficient solution is assessed for early times appropriate to the entry heat protection system application. It is found that the small difference in reflectance causes a significant difference in internal temperature.
Weston, K. C.↗
Viking entry aerodynamics and heating
The characteristics of the Mars entry including the mission sequence of events and associated spacecraft weights are described along with the Viking spacecraft. Test data are presented for the aerodynamic characteristics of the entry vehicle showing trimmed alpha, drag coefficient, and trimmed lift to drag ratio versus Mach number; the damping characteristics of the entry configuration; the angle of attack time history of Viking entries; stagnation heating and pressure time histories; and the aeroshell heating distribution as obtained in tests run in a shock tunnel for various gases. Flight tests which demonstrate the aerodynamic separation of the full-scale aeroshell and the flying qualities of the entry configuration in an uncontrolled mode are documented. Design values selected for the heat protection system based on the test data and analysis performed are presented.
Polutchko, R. J.↗