Loading…

PROGRAM ASTEC (ADVANCED SOLAR TURBO ELECTRIC CONCEPT). PART 1. CANDIDATE MATERIALS LABORATORY TESTS

A space power system of the type envisioned by the ASTEC program requires the development of a lightweight solar collector of high reflectance capable of withstanding the space environment for an extended period. A survey of the environment of interest for ASTEC purposes revealed 4 potential sources...

Full description

Saved in:
Bibliographic Details
Main Authors: Hurtt, W W, Blakney, T L, Cunnington, G R, Bradshaw, W G, Pollard, H E
Format: Report
Language:English
Subjects:
Online Access:Request full text
Tags: Add Tag
No Tags, Be the first to tag this record!
cited_by
cites
container_end_page
container_issue
container_start_page
container_title
container_volume
creator Hurtt, W W
Blakney, T L
Cunnington, G R
Bradshaw, W G
Pollard, H E
description A space power system of the type envisioned by the ASTEC program requires the development of a lightweight solar collector of high reflectance capable of withstanding the space environment for an extended period. A survey of the environment of interest for ASTEC purposes revealed 4 potential sources of damage to collector materials: solar uv radiation, low-energy electrons encountered in the auroral zones, vacuum, and combined temperature levels and thermal cycling. A laboratory test program was conducted to determine the basic thermophysical, optical, and mechanical properties of materials developed by the solar-collector industry for use in the ASTEC program, and to test the effects of space environment on these materials. Of 6 material systems selected for testing, 4 were epoxy-bonded metal systems, 1 was phenolic foam with a metal surface, and 1 was polyurethane-rigidized nylon with an aluminized mylar surface. Honeycomb configurations proved to be far superior from a structural standpoint to the nonhoneycomb types. All the reflective surfaces degraded to some extent in the simulated ASTEC environment, but material systems with bare metal surfaces were significantly more stable than systems with silicon oxide overcoatings. In addition, these systems had a higher initial reflectance. No material proved to be ideally suited in all respects for use in the ASTEC solar collector. See also Part 2, AD480103.
format report
fullrecord <record><control><sourceid>dtic_1RU</sourceid><recordid>TN_cdi_dtic_stinet_AD0482282</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>AD0482282</sourcerecordid><originalsourceid>FETCH-dtic_stinet_AD04822823</originalsourceid><addsrcrecordid>eNqFybEOgkAMgOFbHIz6Bg4ddZAoOLCWXtVLDo70qokTMYgJiXGB948M7i7_P3xz09YSzoIlYFQm2KC9YUVsIQaPAnqVIgB7JhVHQGGyWrcJ1CgKhwQIK-ssKkM5RRz6CB6LIKhB7qAcNS7N7PV4D93q94VZn1jpsnuOfdsMY__pxgbt_pinaZ5mf_gLwqQwwA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>report</recordtype></control><display><type>report</type><title>PROGRAM ASTEC (ADVANCED SOLAR TURBO ELECTRIC CONCEPT). PART 1. CANDIDATE MATERIALS LABORATORY TESTS</title><source>DTIC Technical Reports</source><creator>Hurtt, W W ; Blakney, T L ; Cunnington, G R ; Bradshaw, W G ; Pollard, H E</creator><creatorcontrib>Hurtt, W W ; Blakney, T L ; Cunnington, G R ; Bradshaw, W G ; Pollard, H E ; LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA</creatorcontrib><description>A space power system of the type envisioned by the ASTEC program requires the development of a lightweight solar collector of high reflectance capable of withstanding the space environment for an extended period. A survey of the environment of interest for ASTEC purposes revealed 4 potential sources of damage to collector materials: solar uv radiation, low-energy electrons encountered in the auroral zones, vacuum, and combined temperature levels and thermal cycling. A laboratory test program was conducted to determine the basic thermophysical, optical, and mechanical properties of materials developed by the solar-collector industry for use in the ASTEC program, and to test the effects of space environment on these materials. Of 6 material systems selected for testing, 4 were epoxy-bonded metal systems, 1 was phenolic foam with a metal surface, and 1 was polyurethane-rigidized nylon with an aluminized mylar surface. Honeycomb configurations proved to be far superior from a structural standpoint to the nonhoneycomb types. All the reflective surfaces degraded to some extent in the simulated ASTEC environment, but material systems with bare metal surfaces were significantly more stable than systems with silicon oxide overcoatings. In addition, these systems had a higher initial reflectance. No material proved to be ideally suited in all respects for use in the ASTEC solar collector. See also Part 2, AD480103.</description><language>eng</language><subject>ALUMINUM ; ASTEC(ADVANCED SOLAR TURBO ELECTRIC CONCEPT) ; COATINGS ; COMPOSITE MATERIALS ; DEGRADATION ; Electric Power Production and Distribution ; ELECTRON IRRADIATION ; EMISSIVITY ; EPOXY RESINS ; EXPANDED PLASTICS ; HONEYCOMB CORES ; MECHANICAL PROPERTIES ; NICKEL ; OXIDES ; PHENOLIC PLASTICS ; REFLECTION ; REFLECTORS ; SILICON COMPOUNDS ; SOLAR COLLECTORS ; SOLAR RADIATION ; SPACE ENVIRONMENTS ; SPACECRAFT COMPONENTS ; SPECIFIC HEAT ; THERMAL CONDUCTIVITY ; THERMAL EXPANSION ; THERMAL PROPERTIES ; THERMAL STABILITY ; ULTRAVIOLET RADIATION</subject><creationdate>1966</creationdate><rights>Approved for public release; distribution is unlimited.</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27567,27568</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0482282$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Hurtt, W W</creatorcontrib><creatorcontrib>Blakney, T L</creatorcontrib><creatorcontrib>Cunnington, G R</creatorcontrib><creatorcontrib>Bradshaw, W G</creatorcontrib><creatorcontrib>Pollard, H E</creatorcontrib><creatorcontrib>LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA</creatorcontrib><title>PROGRAM ASTEC (ADVANCED SOLAR TURBO ELECTRIC CONCEPT). PART 1. CANDIDATE MATERIALS LABORATORY TESTS</title><description>A space power system of the type envisioned by the ASTEC program requires the development of a lightweight solar collector of high reflectance capable of withstanding the space environment for an extended period. A survey of the environment of interest for ASTEC purposes revealed 4 potential sources of damage to collector materials: solar uv radiation, low-energy electrons encountered in the auroral zones, vacuum, and combined temperature levels and thermal cycling. A laboratory test program was conducted to determine the basic thermophysical, optical, and mechanical properties of materials developed by the solar-collector industry for use in the ASTEC program, and to test the effects of space environment on these materials. Of 6 material systems selected for testing, 4 were epoxy-bonded metal systems, 1 was phenolic foam with a metal surface, and 1 was polyurethane-rigidized nylon with an aluminized mylar surface. Honeycomb configurations proved to be far superior from a structural standpoint to the nonhoneycomb types. All the reflective surfaces degraded to some extent in the simulated ASTEC environment, but material systems with bare metal surfaces were significantly more stable than systems with silicon oxide overcoatings. In addition, these systems had a higher initial reflectance. No material proved to be ideally suited in all respects for use in the ASTEC solar collector. See also Part 2, AD480103.</description><subject>ALUMINUM</subject><subject>ASTEC(ADVANCED SOLAR TURBO ELECTRIC CONCEPT)</subject><subject>COATINGS</subject><subject>COMPOSITE MATERIALS</subject><subject>DEGRADATION</subject><subject>Electric Power Production and Distribution</subject><subject>ELECTRON IRRADIATION</subject><subject>EMISSIVITY</subject><subject>EPOXY RESINS</subject><subject>EXPANDED PLASTICS</subject><subject>HONEYCOMB CORES</subject><subject>MECHANICAL PROPERTIES</subject><subject>NICKEL</subject><subject>OXIDES</subject><subject>PHENOLIC PLASTICS</subject><subject>REFLECTION</subject><subject>REFLECTORS</subject><subject>SILICON COMPOUNDS</subject><subject>SOLAR COLLECTORS</subject><subject>SOLAR RADIATION</subject><subject>SPACE ENVIRONMENTS</subject><subject>SPACECRAFT COMPONENTS</subject><subject>SPECIFIC HEAT</subject><subject>THERMAL CONDUCTIVITY</subject><subject>THERMAL EXPANSION</subject><subject>THERMAL PROPERTIES</subject><subject>THERMAL STABILITY</subject><subject>ULTRAVIOLET RADIATION</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1966</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFybEOgkAMgOFbHIz6Bg4ddZAoOLCWXtVLDo70qokTMYgJiXGB948M7i7_P3xz09YSzoIlYFQm2KC9YUVsIQaPAnqVIgB7JhVHQGGyWrcJ1CgKhwQIK-ssKkM5RRz6CB6LIKhB7qAcNS7N7PV4D93q94VZn1jpsnuOfdsMY__pxgbt_pinaZ5mf_gLwqQwwA</recordid><startdate>196603</startdate><enddate>196603</enddate><creator>Hurtt, W W</creator><creator>Blakney, T L</creator><creator>Cunnington, G R</creator><creator>Bradshaw, W G</creator><creator>Pollard, H E</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>196603</creationdate><title>PROGRAM ASTEC (ADVANCED SOLAR TURBO ELECTRIC CONCEPT). PART 1. CANDIDATE MATERIALS LABORATORY TESTS</title><author>Hurtt, W W ; Blakney, T L ; Cunnington, G R ; Bradshaw, W G ; Pollard, H E</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD04822823</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1966</creationdate><topic>ALUMINUM</topic><topic>ASTEC(ADVANCED SOLAR TURBO ELECTRIC CONCEPT)</topic><topic>COATINGS</topic><topic>COMPOSITE MATERIALS</topic><topic>DEGRADATION</topic><topic>Electric Power Production and Distribution</topic><topic>ELECTRON IRRADIATION</topic><topic>EMISSIVITY</topic><topic>EPOXY RESINS</topic><topic>EXPANDED PLASTICS</topic><topic>HONEYCOMB CORES</topic><topic>MECHANICAL PROPERTIES</topic><topic>NICKEL</topic><topic>OXIDES</topic><topic>PHENOLIC PLASTICS</topic><topic>REFLECTION</topic><topic>REFLECTORS</topic><topic>SILICON COMPOUNDS</topic><topic>SOLAR COLLECTORS</topic><topic>SOLAR RADIATION</topic><topic>SPACE ENVIRONMENTS</topic><topic>SPACECRAFT COMPONENTS</topic><topic>SPECIFIC HEAT</topic><topic>THERMAL CONDUCTIVITY</topic><topic>THERMAL EXPANSION</topic><topic>THERMAL PROPERTIES</topic><topic>THERMAL STABILITY</topic><topic>ULTRAVIOLET RADIATION</topic><toplevel>online_resources</toplevel><creatorcontrib>Hurtt, W W</creatorcontrib><creatorcontrib>Blakney, T L</creatorcontrib><creatorcontrib>Cunnington, G R</creatorcontrib><creatorcontrib>Bradshaw, W G</creatorcontrib><creatorcontrib>Pollard, H E</creatorcontrib><creatorcontrib>LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Hurtt, W W</au><au>Blakney, T L</au><au>Cunnington, G R</au><au>Bradshaw, W G</au><au>Pollard, H E</au><aucorp>LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>PROGRAM ASTEC (ADVANCED SOLAR TURBO ELECTRIC CONCEPT). PART 1. CANDIDATE MATERIALS LABORATORY TESTS</btitle><date>1966-03</date><risdate>1966</risdate><abstract>A space power system of the type envisioned by the ASTEC program requires the development of a lightweight solar collector of high reflectance capable of withstanding the space environment for an extended period. A survey of the environment of interest for ASTEC purposes revealed 4 potential sources of damage to collector materials: solar uv radiation, low-energy electrons encountered in the auroral zones, vacuum, and combined temperature levels and thermal cycling. A laboratory test program was conducted to determine the basic thermophysical, optical, and mechanical properties of materials developed by the solar-collector industry for use in the ASTEC program, and to test the effects of space environment on these materials. Of 6 material systems selected for testing, 4 were epoxy-bonded metal systems, 1 was phenolic foam with a metal surface, and 1 was polyurethane-rigidized nylon with an aluminized mylar surface. Honeycomb configurations proved to be far superior from a structural standpoint to the nonhoneycomb types. All the reflective surfaces degraded to some extent in the simulated ASTEC environment, but material systems with bare metal surfaces were significantly more stable than systems with silicon oxide overcoatings. In addition, these systems had a higher initial reflectance. No material proved to be ideally suited in all respects for use in the ASTEC solar collector. See also Part 2, AD480103.</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng
recordid cdi_dtic_stinet_AD0482282
source DTIC Technical Reports
subjects ALUMINUM
ASTEC(ADVANCED SOLAR TURBO ELECTRIC CONCEPT)
COATINGS
COMPOSITE MATERIALS
DEGRADATION
Electric Power Production and Distribution
ELECTRON IRRADIATION
EMISSIVITY
EPOXY RESINS
EXPANDED PLASTICS
HONEYCOMB CORES
MECHANICAL PROPERTIES
NICKEL
OXIDES
PHENOLIC PLASTICS
REFLECTION
REFLECTORS
SILICON COMPOUNDS
SOLAR COLLECTORS
SOLAR RADIATION
SPACE ENVIRONMENTS
SPACECRAFT COMPONENTS
SPECIFIC HEAT
THERMAL CONDUCTIVITY
THERMAL EXPANSION
THERMAL PROPERTIES
THERMAL STABILITY
ULTRAVIOLET RADIATION
title PROGRAM ASTEC (ADVANCED SOLAR TURBO ELECTRIC CONCEPT). PART 1. CANDIDATE MATERIALS LABORATORY TESTS
url http://sfxeu10.hosted.exlibrisgroup.com/loughborough?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-04T05%3A38%3A58IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-dtic_1RU&rft_val_fmt=info:ofi/fmt:kev:mtx:book&rft.genre=unknown&rft.btitle=PROGRAM%20ASTEC%20(ADVANCED%20SOLAR%20TURBO%20ELECTRIC%20CONCEPT).%20PART%201.%20CANDIDATE%20MATERIALS%20LABORATORY%20TESTS&rft.au=Hurtt,%20W%20W&rft.aucorp=LOCKHEED%20MISSILES%20AND%20SPACE%20CO%20INC%20SUNNYVALE%20CA&rft.date=1966-03&rft_id=info:doi/&rft_dat=%3Cdtic_1RU%3EAD0482282%3C/dtic_1RU%3E%3Cgrp_id%3Ecdi_FETCH-dtic_stinet_AD04822823%3C/grp_id%3E%3Coa%3E%3C/oa%3E%3Curl%3E%3C/url%3E&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true