Anodized Aluminum Coatings for Temperature Control of Space Vehicles PDF Download
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Author: James H. Weaver
Publisher:
ISBN:
Category : Aluminum coating
Languages : en
Pages : 40
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Book Description
Author: James H. Weaver
Publisher:
ISBN:
Category : Aluminum coating
Languages : en
Pages : 40
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Book Description
Author: James H. Weaver
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Author:
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ISBN:
Category :
Languages : en
Pages : 18
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Book Description
The importance of surface radiation characteristics in controlling the internal temperature of space vehicles has been comprehensively reviewed by other investigatorsl. It is imperative that extraterrestrial vehicles now in design be provided a surface with a ratio of solar absorptance (alpha) to long wavelength emittance (epsilon) equal to about 0. 15 to 0. 18. Ideally, a surface should possess an alpha of 0.10 and an epsilon of 0.9, or an alpha-to-epsilon ratio of 0.11.
Author: Louis A. Teichman
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 602
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: RS. Alwitt
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ISBN:
Category : Anodized aluminum coatings
Languages : en
Pages : 22
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A concern for the use of anodized aluminum as Space Station thermal control surfaces is the potential degradation of critical optical properties due to oxide coating cracking. This cracking may be induced by differential thermal expansion during hot adhesive bonding of the radiator assembly or during 30 years of exposure to sunlight/darkness cycles in low earth orbit (LEO). This paper summarizes investigations into the effects of temperature and humidity on coating stresses and cracking. Experimentally measured coating residual stresses after anodizing and sealing are shown to be strongly dependent on humidity. Two sets of tests are used to study cracking directly: one determines the temperature (Tc at which cracks first appear during a single heating cycle, while the other involves rapid thermal cycling (RTC) between maximum and minimum temperatures. The effects of several test parameters on cracking are reviewed, with special attention to temperature, coating thickness, and humidity. Fatigue models are developed to describe the observed cracking and to serve as the basis for predictions of LEO cracking. The physical characteristics of cracks and related substrate plastic deformation in both Tc and RTC tests are discussed briefly.
Author: Louis A. Teichman
Publisher:
ISBN:
Category : Carbon composites
Languages : en
Pages : 20
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Author: Air Force Materials Laboratory (U.S.)
Publisher:
ISBN:
Category : Materials
Languages : en
Pages : 294
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Technical reports published by the Air Force Materials Laboratoy during the period 1 July 1962 - 30 June 1963 are abstracted herein. Reports on reseqrch conducted by the Air Force Materials Laboratory personnel as well as that conducted on contract are included. These reports cover basic and applied research in the materials area being conducted by the Metals and Ceramics Division, Non-metallic Materials Division, Materials Physics Division, Manufacturing Technology Division, and Materials Applications Division of the Air Force Materials Laboratory.
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 2300
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Author: United States. Naval Research Office
Publisher:
ISBN:
Category :
Languages : en
Pages : 922
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