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  • 1
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    STEADY- A STEADY STATE THERMAL ANALYSIS PROGRAM FOR MICROCOMPUTERS (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The Steady State Thermal Analysis Program (STEADY) provides the thermal designer with a quick and convenient method for calculating heat loads and temperatures. STEADY can be used on small nodal networks for conceptual or preliminary thermal design and analysis. STEADY will accept up to 20 nodes of fixed or variable temperature, with constant or temperature-dependent thermal conductivities, and any set of consistent units. In a steady state thermal network, the heat balance on each variable temperature node must sum to zero. The general heat transfer equations are solved with a Newton-Raphson technique and refined by a fourth order quartic solution. Input data includes the number of nodes, number of boundary nodes, the fixed temperatures at all boundary nodes, initial temperature guesses for variable nodes, impressed heat loads, conduction and radiation coefficients, and control parameters such as convergence criteria, maximum iterations, and damping factors. The output is stored in a print file and tabulates final temperatures and heat flows for all nodes. STEADY is menu driven and allows the user to save files for future modification. STEADY is written in FORTRAN 77 (Ryan McFarland's RMFORTRAN) for interactive execution and has been implemented on the IBM PC computer series under DOS with a central memory requirement of approximately 92K of 8 bit bytes using a math coprocessor, and 103K bytes without the coprocessor. This program was developed in 1987.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NPO-17179
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  • 2
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    Thermal systems analysis for the Space Infrared Telescope Facility dewar (1991)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Thermal systems analysis models were used to design SFHe cooled dewar for the Space Infrared Telescope Facility (SIRTF), a 1 m class cryogenically cooled observatory for IR astronomy. The models are capable of computing both the heat leaks into the dewar and the operating temperature of a SFHe tank. The models are aimed at predicting the ability of the SIRTF cryogenic system to satisfy a five-year mission lifetime requirement and maintain the SFHe tank operating temperature of 1.25 K to provide sufficient cooling for science instruments and the optical system. The thermal models are very detailed and very fast with a typical steady state run of about 20 sec on a VAX minicomputer.
    Keywords: ENGINEERING (GENERAL)
    Type: In: Infrared technology XVII; Proceedings of the Meeting, San Diego, CA, July 22-26, 1991 (A93-38376 15-35); p. 97-108.
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  • 3
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    SIRTF thermal design modifications to increase lifetime (1993)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: An effort was made to increase the predicted lifetime of the SIRTF dewar by lowering the exterior shell temperature, increasing the radiated energy from the vapor cooled shields and reconfiguring the vapor cooled shields. The lifetime increases can be used to increase the scientific return from the mission and as a trade-off against mass and cost. This paper describes the configurations studied, the steady state thermal model used, the analytical methods and the results of the analysis. Much of the heat input to the outside dewar shell is radiative heat transfer from the solar panel. To lower the shell temperature, radiative cooled shields were placed between the solar panel and the dewar shell and between the bus and the dewar shell. Analysis showed that placing a radiator on the outer vapor cooled shield had a significant effect on lifetime. Lengthening the distance between the outer shell and the point where the vapor cooled shields are attached to the support straps also improved lifetime.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: In: Cryogenic optical systems and instruments V; Proceedings of the Meeting, San Diego, CA, July 23, 24, 1992 (A93-28226 10-19); p. 227-234.
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  • 4
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    System test and flight results from infrared astronomical satellite external thermal subsystem (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The Infrared Astronomical Satellite (IRAS) received its system level thermal testing in a solar simulator in September and October 1982 and was launched in January 1983. In order to reduce costs and meet a tight launch schedule, a system thermal test approach was employed which combined the goals of thermal design development tests, thermal balance tests, and thermal vacuum qualification tests. This approach relied heavily on the use of a computer-controlled automatic data handling and heater control system which reduced reliance on human monitoring of test data in comparison to past projects. The validity of this approach has been borne out by flight results. During the whole mission most temperatures were within the desired range and close to predictions. Included under the external thermal subsystem are room temperature electronics and radiatively cooled surfaces with temperatures below 100 and 200K.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 166-169
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  • 5
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    Radiative cooler (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method and radiative cooling device for use in passively cooling spaces is described. It is applicable to any level of thermal radiation in vacuum and to high-intensity thermal radiation in non-vacuum environments. The device includes an enclosure nested in a multiplicity of thin, low-emittance, highly-reflective shields. The shields are suspended in a casing in mutual angular relation and having V-shaped spaces defined therebetween for redirecting, by reflection, toward the large openings of the V-shaped spaces, thermal radiation entering the sides of the shields, and emitted to the spaces, whereby successively reduced quantities of thermal radiation are reflected by the surfaces along substantially parallel paths extended through the V-shaped spaces to a common heat sink such as the cold thermal background of space.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 6
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    Hydrogen gas generation in water/stainless-steel heat pipes. (1972)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 72-WA/HT-37 , Winter Annual Meeting of the American Society of Mechanical Engineers; Nov 26, 1972 - Nov 30, 1972; New York, NY
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  • 7
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    Space Infrared Telescope Facility mission and cryogenic design (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The Space Infrared Telescope Facility is the last of the Great Observatory missions. It is presently scheduled for launch in 2001. The mission will study the infrared spectrum from 2 to 1200 microns with three imaging and spectral instruments. The observatory will have a 5 year lifetime and will be placed in a 100,000 km earth orbit. The cryogenic system is based on a 4000 I superfluid helium cryostat. The mission and the cryogenic system are described, and the cryogenic technology issues are discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Cryogenics (ISSN 0011-2275); 32; 2, 19; 107-110
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  • 8
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    Steady-State Thermal-Analysis Program For Microcomputers (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Nodal-network model of heat flow implemented by computer program. Steady State Thermal Analysis Program, STEADY, provides thermal designer with quick and convenient method for calculation of heat loads and temperatures. Used on small nodal networks for conceptual or preliminary thermal design and analysis. Accepts up to 20 nodes of fixed or variable temperatures, with constant or temperature-dependent thermal conductivities, and any set of consistent units. Written in FORTRAN 77.
    Keywords: MECHANICS
    Type: NPO-17179 , NASA Tech Briefs (ISSN 0145-319X); 11; 10; P. 62
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  • 9
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    Advanced radiative cooler with angled shields (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Recent demands for spaceborne sensor temperatures below 90 K are exceeding the capabilities of present passive radiative cooler designs. To improve cooling performance, a novel technique was developed to radiatively and conductively isolate the radiating plate from the spacecraft using low-emittance, highly specular angled radiation shields. An experimental test of the new shield concept verified its effectiveness and enabled calibration of a detailed thermal model. Based on the concept test results, performance predictions show that the Advanced Radiator can achieve lower temperatures, deliver more cooling power and be smaller and lighter than the best state-of-the-art coolers.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-1100 , Thermophysics Conference; Jun 23, 1981 - Jun 25, 1981; Palo Alto, CA
    Format: text
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