Cooling of a high-power electron tube in a space vehicle.
High power TWT tube cooling in space vehicle, discussing thermal control system based on heat pipe radiator
Conway, E. C.↗
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Results for “Thermal Control System”
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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Thermal control materials
Heat absorption and emission balance for thermal control system of spacecraft
Sibert, M. E.↗
Task 3 space storable propellant module environmental control technology Summary report
Thermal control system for space storable propellant module
De Land, R. E.↗
Thermal control in a lunar environment
Apollo Lunar Surface Experiment Package (ALSEP) component configuration and deployment environment, describing passive thermal control system for data processing equipment
H E Collicott↗
The Orbiting Geophysical Observatories
OGO spacecraft structures, thermal control systems, attitude control, weight and power supplies
Scull, W. E.↗
Task 7 space storable propellant module environmental control technology
Design of thermal control system for cryogenic fluid storage tanks
De Land, R. E.↗
Task 4 space storable propellant module environmental control technology
Analyzing thermal control system for B2H6/OF2 propulsion module
Haroldsen, O. O.↗
Engineering model test plan. Space storable propellant module environmental control technology
Test program for engineering model of thermal control system of space storable propellant module in simulated environments
Haroldsen, O. O.↗
Phase change solidification dynamics
Phase change solidification phenomena in n- hexadecane for spacecraft thermal control systems, considering two or three dimensional models
Golden, J. O.↗
A lightweight bimetallic actuator for spacecraft thermal control
The design, development, and construction of two types of active thermal-control systems are described. These designs are based on the controlled angular deflections of spiral-wound bimetallic actuators. The use of these actuators and lightweight louvers results in a frictionless system that is low in weight yet simple in design and low in cost. Both designs exhibit high reliability, good performance repeatability, and do not require power from the spacecraft. Design philosophy and implementation, design tradeoffs, and materials selection are reviewed. The test program is described, and results are presented.
Schilling, K. L.↗
Passive seismic experiment
The design, deployment, and operation of the Apollo 16 passive seismic experiment (PSE) are discussed. Since activation, all elements of the PSE have operated as planned, with the exception of the sensor thermal control system. Significant progress in the measurement of meteoroid flux in near-earth space has been made, along with dilineation of active moonquake source regions. The data obtained indicate that moonquakes are concentrated at great depth (800 to 1000 km) and that the apparent disparity between meteoroid flux estimtes based on lunar crater counts and those from earth-based observations can be resolved by seismic measurements in favor of the lower flux indicated by the crater count method. The results obtained from the PSE are summarized and their significance is discussed in detail.
Latham, G. V.↗
Heat Pipe Thermal Conditioning Panel
The technology involved in designing and fabricating a heat pipe thermal conditioning panel to satisfy a broad range of thermal control system requirements on NASA spacecraft is discussed. The design specifications were developed for a 30 by 30 inch heat pipe panel. The fundamental constraint was a maximum of 15 gradient from source to sink at 300 watts input and a flux density of 2 watts per square inch. The results of the performance tests conducted on the panel are analyzed.
Saaski, E. W.↗
Development of electrical feedback controlled heat pipes and the advanced thermal control flight experiment
The development and characteristics of electrical feedback controlled heat pipes (FCHP) are discussed. An analytical model was produced to describe the performance of the FCHP under steady state and transient conditions. An advanced thermal control flight experiment was designed to demonstrate the performance of the thermal control component in a space environment. The thermal control equipment was evaluated on the ATS-F satellite to provide performance data for the components and to act as a thermal control system which can be used to provide temperature stability of spacecraft components in future applications.
Bienert, W. B.↗
Astronomy satellites in the U.S. program
The Orbiting Astronomical Observatory (OAO) series demonstrated that necessary thermal control systems and high pointing stability are feasible on astronomical satellites. A geosynchronous International Ultraviolet Explorer (IUE) is being planned by the US, UK, and ESRO for stellar spectroscopy. High Energy Astronomy Observatories, HEAO-A B, and C, will concentrate on stellar X-ray objects, cosmic ray physics, and gamma ray astronomy. A Shuttle-compatible Solar Maximum Mission (SMM) is planned for studying solar flares and flare related phenomena during the next solar maximum. Now in the instrumentation definition stage is the Large Space Telescope (LST), to provide higher resolution and sensitivity, larger wavelength range (from ultraviolet to far infrared), and higher time resolution than ground-based telescopes.
Aucremanne, M. J.↗
Heat pipes in space and on earth
The performance of heat pipes used in the thermal control system of spacecraft such as OAO-III and ATS-6 is discussed, and applications of heat pipes to permafrost stabilization on the Alaska Pipeline and to heat recovery systems are described. Particular attention is given to the ATS-6, launched in 1974, which employs 55 heat pipes to carry solar and internal power loads to radiator surfaces. In addition, experiments involving radiative cooling based on cryogenic heat pipes have been planned for the Long Duration Exposure Facility spacecraft and for Spacelab. The role of heat pipes in Space Shuttle heat rejection services is also mentioned.
Ollendorf, S.↗
Heat pipe life and processing study
The merit of adding water to the reflux charge in chemically and solvent cleaned aluminum/slab wick/ammonia heat pipes was evaluated. The effect of gas in the performance of three heat pipe thermal control systems was found significant in simple heat pipes, less significant in a modified simple heat pipe model with a short wickless pipe section. Use of gas data for the worst and best heat pipes of the matrix in a variable conductance heat pipe model showed a 3 C increase in the source temperature at full on condition after 20 and 246 years, respectively.
Antoniuk, D.↗
A liquid hydrogen experiment as a Shuttle payload
The paper describes the cryogenic fluid management experiment (CFME) as a Shuttle payload. The experiment includes a liquid hydrogen tank containing a fine-mesh screen acquisition device, and a thermal control system consisting of a thermodynamic vent system to intercept heat leak to the hydrogen tank and control tank pressure. Engineering data obtained will be used to establish design criteria for subcritical cryogenic storage and supply tankage.
Eberhardt, R. N.↗
Nickel-hydrogen battery integration study for the Multimission Modular Spacecraft
A study has been performed to determine the feasibility of using nickel-hydrogen batteries as replacements for the nickel-cadmium batteries currently used for energy storage in the Multimission Modular Spacecraft under a contract with NASA Goddard Space Flight Center. The battery configuration was selected such that it meets volumetric and mounting constraints of the existing battery location, interfaces electrically with existing power conditioning and distribution equipment, and maintains acceptable cell operating temperatures. The battery contains 21, 50 ampere-hour cells in a cast aluminum structural frame. Cells used in the battery design are those developed under the Air Force's Aero Propulsion Laboratory funding and direction. Modifications of the thermal control system were necessary to increase the average output power capability of the Modular Power Subsystem.
Mueller, V. C.↗