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THERMAL RADIATION CONSIDERATIONS FOR ADVANCED FLIGHT VEHICLES
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English
Abstract
The utilization of radiative systems for control of heat transfer on advanced flight vehicles is discussed. One of the major problems in attaining efficient radiative systems is achieving a high or low emissivity; the desired value depending on whether heat flow is to he maximized or minimized. Means of achieving high and low emissivity surfaces on present and future flight vehicles are presented. It is pointed out that the temperature of space vehicles is dependent upon the thermal radiation characteristics of the exterior surface and applicable materials are discussed. Methods of measuring the thermal radiation properties of materials are briefly mentioned.
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Citation
SIEGEL, H. and KUMMER, D., "THERMAL RADIATION CONSIDERATIONS FOR ADVANCED FLIGHT VEHICLES," SAE Technical Paper 610439, 1961, https://doi.org/10.4271/610439.Also In
References
- Pellini W.S. Harris W.J. Flight in the Thermosphere IV - Material Requirements for Radiative Systems Metal Progress June 1960
- Pellini W.S. Harris W.J. Flight in the Thermosphere I - Material Requirements for Thermal Protection Systems Metal Progress March 1960
- McDonnell Aircraft Corporation Report 7380 II Anom.: Refractory Metals Structural Development Program Quarterly Report
- Anom. : The Thermal Emissivity of Seventeen Materials from 500°F to 2700°F. Southern Research Institute Final Report to Bell Aircraft Corporation August 1959
- Olson O. Harry Morris James C. Determination of Emissivity and Reflectivity Data on Aircraft Structural Materials WADC Technical Report 56-222 April 1960
- Fieldhouse I. B. Lang J. I. Blau H. H. Investigation of Feasibility of Utilizing Available Heat-Resistance Materials for Hypersonic Leading Edge Applications WADC Technical Report 59-744 July 1960