Feb 17, 1993 - In addition, the contents of the database are condensed in two tables in the two appendixes to this report: one ..... their tow and ring location (shown in the schematic in Figure 2). Thereafter. the trays ..... RARMH (sift nsat hth). CAI ...... 0 q. W. W- W Uf W*AWW(A*i1. A. :t z.~. S. Vt 0l~. 2-StA. Ul ift. tn. 0'0t. ImNU ...
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: : AEROSPACE RE PORT NO.
Long Duration Exposure Facility Experiment M0003 Deintegration Observation Database Prepared by S. R. GYETVAY, J. M. COGGI, and M. J. MESHISHNEK Mechanics and Materials Technology Center Technology Operations ~DTIC_
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ELECTE AUG 0 41993
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17 February 1993
Prepared for SPACE AND MISSILE SYSTEMS CENTER AIR FORCE MATERIEL COMMAND Los Angeles Air Force Base P. 0. Box 92960 Los Angeles, CA 90009-2960
Engineering and Technology Group
THE AEROSPACE CORPORATION El Segundo, California
93-17463
APPROVED FOR PUBLIC RELEASE: DISTRIBUTION UNLIMITED
3
:173
-
This report was submitted by The Aerospace Corporation, El Segundo, CA 90245-4691, under Contract No. F04701-88-C-0089 with the Space and Missile Systems Center, P. 0. Box 92960, Los Angeles, CA 90009-2960. It was reviewed and approved for The Aerospace Corporation by R. W. Fillers, Principal Director, Mechanics and Materials Technology Center. Capt. Don Johnson was the Space Test Program project officer responsible for the retrieval of LDEF. This report has been reviewed by the Public Affairs Office (PAS) and is releasable to the National Technical Information Service (NTIS). At NTIS, it will be available to the general public, including foreign nationals. This technical report has been reviewed and Is approved for publication. Publication of this report does not constitute Air Force approval of the report's findings or conclusions. It is published only for the exchange and stimulation of Ideas.
DONALD C. JOHNSON, JR. Captain, USAF Chief, Test Planning Division
WM KYLE S , Capt, USAF Deputy Chief Industrial & International Programs Division
INCLASSIFIED
, SECUr~fl
CLASSIFICATION OF THIS PAGE,
REPORT DOCUMENTATION PAGE la. REPORT SECURITY CLASSIFICATION
lb. RESTRICTIVE MARKINGS
Unclassified 2a. SECURITY CLASSIFICATION AUTHORITY
3. DISTRIBUTION/AVAILABILITY OF REPORT
Approved for public release; distribution unlimited
2b. DECLASSIFICATIONXOOWNGRADING SCHEDULE 4. PERFORMING ORGANIZATION REPORT NUMBER(S)
5. MONITORING ORGANIZATION REPORT NUMBER(S)
TR-92(2935)-9
SMC-TR-93-38
6.. NAME OF PERFORMING ORGANIZATION
6b. OFFICE SYMBOL y0'0 )
The Aerospace Corporation
Technologv Operations
7a. NAME OF MONITORING ORGANIZATION
Space and Missile Systems Center
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SpaceandMissileSystemsCenter_,_,
6c. ADDRESS (CG),State. and ZIP Code)
7b. ADDRESS (Cit, State, andZIP Code)
Los Angeles Air Force Base
El Segundo, CA 90245-4691
Los Angeles, CA 90009-2960
a. NAME OF FUNDINGISPONSORING
8b. OFFICE SYMBOL
ft, ADORESS (Cy State, and ZIP Code)
9. PROCUREMENT INSTRUMENT IDENTIFICATION NUMBER
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SOURCE OF FUNDING NUMBERS PROGRAM ELEMENT NO. NO.
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LONG DURATION EXPOSURE FACILITY EXPERIMENT M0003 DEINTEGRATION OBSERVATION DATABASE 12. PERSONAL AUiOR(S)
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13b. TIME COVERED
14. DAIEOF REPORT (YVW. ~Mnh Day)
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The four trays of the M0003 materials experiment on LDEP contained over 1600 samples from 20 subexperinents. iMi complete sample complement represented abroad range of materials, Including tdin itm optcal coatings, paints, polymer sheets and tape, adhesives and composites. for use in various spacecraft applications, including thermal control, structures, optics, and solar power. Since some subexperiments included duplicate samples exposed on the leading and trailing edge trays for 9-week, 19.week, 40-week, and 69-month durations, comparisons pIomttice a valuable thne history of degradation
During the deintegration of the subexperitnents fro the M0003 trays. each sample was examined using bright field, dark field, and Nornarski light microscopy techniques. Over 3,000 color macrographs anu phoronicrograptu were made of the
condition of the M0003 trays and the Individual samples. Records of the condition of the samples, photographic records
and all available references of publications on postflight anilyses on each sample were collected In a computer database (4th DlmensiooTM for the Macintosh computer), Upon written request, the database records and photographs for specific samples may be obtained from The Aerospace Corporation Archives. Copies of the electronic database are available on floppy disk by request as well. Directions for requesting the records. photographs, and database copies are given in tis o. 0ITAUT6WAVAtABfIfYOF AST
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SUMMARY This report summarizes the extensive photographic and electronic observation database compiled during the disassembly of The Aerospace Corporation M0003 Materials Experiment that was aboard the NASA Long Duration Exposure Facility (LDEF) spacecraft. The LDEF was deployed by Space Shuttle into low Earth orbit (LEO) in April 1984, and was retrieved in January 1990. The M0003 Experiment contained more than 1600 material test samples from various organizations, including the Aerospace Laboratories, DoD Laboratories, and other government contractors. The M0003 test samples included a variety of current or baseline spacecraft materials such as thermal control coatings, laser optics, polymer composites, structural materials, laser communication components, dosimeters, antenna materials, contamination monitors, solar cells, fiber optics, and electronic
piece parts. This report describes the M0003 experiment and the deintegration effort at The Aerospace Corporation. It gives an overview of the contents of the M0003 sample database in diagrammatic form. In addition, the contents of the database are condensed in two tables in the two appendixes to this report: one providing a list of the sample complement by Database Number with an abbreviated description of the samples and their post-flight condition, and the second, giving the sample complement sorted by spacecraft application. The M0003 Deintegration Observation Database is available M to requestors on a 3 112 in. floppy disk (in 4th DimensionT for the Macintosh format) tbr more complete examination of the contents. Through its Corporate Archives, The Aerospace Corporation is distributing individual database records and prints of photographs taken to document the post-flight condition of the M0003 trays and samples. The records and photographs of the test samples are valuable because they are of spacecral materials that were retrieved and physically examined after extended exposure in the nalurl space environment, a very rare event, A few examples of the over 3,000 color photographs (although in black and white) and an example of an observation record are shown In this report, Information on how to order copies of the photographs and records or to request disk copies of the M0003 Deintegration Database is also provided. Po Accusio'n NTIS CR1A&I DTIC ''A2 U lti""'JCAI J
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PREFACE The authors express their sincere appreciation to the Space Test Program (SMC/CUL) for funding the M0003 deintegration and to Lt. Col. M. Obal of the Strategic Defense Initiative Organization SDIO/TNI, Materials and Structures, and Lt. M. Jones, W. Ward, and K. Davidson of Wright Laboratory Materials Directorate for funding the database portion of this work. We would like to thank the NASA Langley LDEF Science Office for their unstinting support to our project. We also wish to acknowledge the contribution of the following individuals to this effort: Col. J. Armstrong, R. Bachus, D. H. Barker, G. W. Boyd, R. A. Brose, W. C. Burns, W. H. Childs, L. G. Clark, A. F. DIGiacomo, L. Fishman, E. L. Galvin, C. S. Hemminger, Capt. D. Johnson, J. L. Jones, H. K. A. Kan, W. H. Kinard, C. Kiser, F. Knight, A. Levine, B. Lightner, N. Marquez, G. D. Martin, L. A. Okada, R. O'Neal, K. W. Paschen, C. Rochester, H. T. Sampson, T. A. Stoner, W. K. Stuckey, T. K. Tessensolh, G. A. ToH. . Wang, D. B. Wisehart, and J. C. Uht.
3
CONTENTS
1 SUUAARY ........................................................
PREAE..............................
3
ACE..............................
INTRODUCTION ............................................................................................................
7
1U.
THE AEROSPACE CORPORATION M0003 EXPERIMENT ............
9
A. M0003 Trays and Samples ............................................................................
9
B. Environment Exposure Control Canisters .....................................................
10
THE M0003 EXPERIMENT DEINTEGRATION ..............................................
II
A. Inspection At Kennedy Space Center ............................................................
I1
B Disassembly At The Aerospace Corporation ................................................
I
THE M0003 DATABASE ...................................................................................
13
A. Observation and Photographic Documentation .............................................
13
B. Data and Photograph Retrieval from the Database ........................................
13
I1.
IV.
REFERENCES .................................................................................................
............
15
APPENDIX A ....................................................................................................................
35
APPENDIX B ...................................................................................................................
67
AEROSPACE FORM 5365: Order Forni for M0003 DIWntcgratton Database ................... . .........................
97
FIGURES L,
Th LDEF in space just after deploymnt by the Space Shuttle Columbia (April 1984) ..........................................................................................
17
2.
Dlagtam of LDEF showing row and ring nom wnlature .......................................
18
3.
Diagram ofopcal sanpes in databa .........................................................
19
4.
Diagram of smctural samples in database .........................................................
19
S.
Diagram of thermal control samples Indatabase......................
20
6.
DLgram of polymeric sampl"s in daLabase .......................................................
20
5
7.
Diagram of solar power materials in database .....................................................
21
8.
Post-flight photograph of the leading edge 3-in. tray, D9 (L3) ..........................
22
9.
Diagram of sample layout on leading edge 3-in. tray, D9 (L3) ........................
23
10.
Post-flight photograph of the trailing edge 3-in. tray, D3 (T3) ..........................
24
11.
Diagram of sample layout on trailing edge 3-in. tray, D3 (T3) ...........................
25
12.
Post-flight photograph of the leading edge 6-in. tray, D8 (L6) ..........................
26
13.
Diagram of sample layout of the leading edge 6-in. tray, D8 (L6) ....................
27
14.
Post-flight photograph of the trailing edge 6-in. tray, D4 (T6) ..............
28
15.
Diagram of sample layout of the trailing edge 6-in. tray, D4 (T6) ............
29
16.
Post-flight photograph of the open leading edge canister (Tray D8, Module VI) ...........................................................................................................
30
Diagram of sample layout of the open trailing edge canister (Tray D8, M odule VI) .........................................................................................................
30
Post-flight photograph of the open trailing canister (Tray 1)4, Module V ) .......................................................................................................
31
Diagram of sample layout of the open trailing edge canister (Tray D4, M odule VI) ...........................................................................................................
31
View of two hypervelocity particle impacts to the Chemglaze A-276painted sunshleld on leading edge tray )4 (.6) ................................ ..................
32
17. 18. 19. 20.
..........
32
21.
Diagram of MOO03 database organization ..... ..........
22.
Examples of photographs that can be ordered from archives ..............................
33
23.
Eamnple of hard copy database obseation record ............................................
34
TABLES
L
Summary of M0003 Subexperinents ..................................................................
H.
Environmea
Expeidenced by Samples on the M0003 Trays....................
6
16
18
I. INTRODUCTION In 1990, after extended exposure to the space environment, the NASA Long Duration Exposure Facility (LDEF) was retrieved from low Earth orbit (LEO) by the Shuttle Columbia. The LDEF, shown in space just after deployment in Figure 1, is a 12-sided, 30-ft. long, 14-ft. diameter, unmanned spacecraft. It was deployed by the Space Shuttle Challenger into a near circular orbit at 476 km altitude, 28.50 inclination, on 7 April 1984. Originally intended for an 11 month stay in space, a backlog in the NASA launch schedule delayed the LDEF recovery until 69 months had elapsed. LDEF was retrieved in a decaying orbit at 332 km. During the 69 months exposure, materials on the LDEF were subjected to -12,000 hours of solar UV, 32,422 thermal vacuum cycles, an electron dose of 2.5 x 105 Rads, a proton dose of 1.6 x 103 Rads, and thousands of micrometeoroid and space debris Impacts. The LDEF was gravity gradient-stabilized and therefore maintained a constant orientation with respect to the velocity vector on orbit. Only those experiments on the side of the spacecraft facing Into the velocity vector (leading edge) received a significant atomic oxygen dose (maximum 9 x 1021 atoms/CM 2). Atomic oxygen effects often overshadowed or completely removed the damage due to UV exposure on leading edge materials, The leading edge experiments were Impacted by space debris and micrometeorold particles by an order of magnitude more than the experiments on the wake side (trailing edge) of LDEF. The largest crater produced by hypervelocity Impact was 5.25 num in diameter and was found on structural hardware on the spaceward-facing end of LDEF.
7/
U. THE AEROSPACE CORPORATION M0003 EXPERIMENT
One of 57 experiments flown on the 86 experiment-holding trays arrayed around the LDEF, M0003 was the most comprehensive materials experiment. It occupied four of the experiment trays. The M0003 experiment, planned and integrated by The Aerospace Corporation Mechanics and Materials Technology Center, was designed to study the effects of the space environment on 1978 current and developmental spacecraft materials. M0003 was a collection of 20 subexperiments from The Aerospace Corporation laboratories, Air Force and Navy laboratories, and Department of Defense contractors, and was fielded under the sponsorship of The Aerospace Corporation Mission Oriented Investigation and Experimentation (MOLE) program, the Air Force Space and Missile Systems Center (then SAMSO) and the Space Test Program. The compilation of the deintegraton observation database was funded in part by The Aerospace Corporation MOJE program and the Strategic Defense Initiative Organization (SDIO) with Wright Laboratory through the SDIO Space Environmental Effects Program. The M0003 subexperiments, each with the current point of contact, are summarized in Table I. A. M0003 TRAYS AND SAMPLES The M0003 hardware consisted of four peripheral ,- ys, two experiment power and data systems (EPDS), two environment exposure control canisters (EECC), and several Li/SO2 batteries to satisfy power requirements. The experiment was equipped to record temperature, strain, quartz crystal microbalance (QCM) frequency, solar cell output, fiber optics output, circuit interrogation, and various data system parameters. The trays were flown in pairs, one pair consisting of a 6-inch deep tray (carrying an EPDS and a canister) that was connected by wiring harness to a 3-inch deep tray (carrying mostly sample coupons). One tray pair was located on the LDEF leading edge and a similar pair was located on the trailing edge. Aerospace designated the trays as "LY, "L6", "T3". and "T6", according to the tray depth and leading or trailing edge location. Later, NASA assigned the trays to an exact location on the LDEF and adopted a nomenclature that designated the trays according to their tow and ring location (shown in the schematic in Figure 2). Thereafter. the trays were known as "9" (3), "D8" (L6), "D" (T3). and 'D4" (T6). The Aerospace tray designations had already been incorporated into a unique identification code that the M0003 integrators had aWsgned to each ample. The code was used extensively in the preflight coordination and planning documentation for the M0003 experiment and could not easily be cianged thereafter. The design of the trays was modular, a system that allowed samplea to be themnally coupled or decoupled from the tray and the LDEF structure. Each tray had six modules, designated by Roman Numerals I through VI Most test samples were mounted on blackanodized aluminum hardware plates on the modules. Many samples were apatured, therefore, exposed versus unexposed portons of their surface could be compared. The samples on the M0003 trays included a variety of paints, coatings, laser optics, composite structural materials, laser communication components, dositeters, antenna materials, contamination monitors, solar cells, fiber optics, and electronic piece parts, Nearly all of the samples can be informally grouped into five material types: thermal control, polymteric, optical, structural, and solar power materials. Figures 3 through 7 show diagrams delineating the M0003 sample complement by these types. Post-flight photographs of the four trays before deintegratlon of the samples and maps showing the layout of the samples on the modules are presented in Figures 8 through 15. Figures 16 through 19 show post-flight photographs of th open caidsteirs with
9
sample maps. Preflight photos are available for all four trays and the open canisters loaded with the samples, but are not Included in this report. These photographs are available in black and white or in color. Most M0003 subexperiments included samples that were exposed for 69 months duration on at least one of the four trays and many subexperiments contained duplicate sample sets on the leading and trailing edge trays. A few subexperiments included sets in the canisters as well. Some subexperiments also contained a set of flight control samples that were mounted within the modules, and therefore were not directly exposed to the space environment For the 69-month duration of the LDEF exposure in LEO, the four trays of samples experienced somewhat different environments, depending on their location on LDEF (shown in Table II). Measurements made following LDEF retrieval revealed that, on orbit, the vehicle had been oriented so that Row 9 was 80 off normal to the spacecraft velocity vector (Refs. 1 and 2). The solar exposure values In the table are combined direct sun and earth-reflected radiation (Ref. 3). All trays on LDEF experienced the same number of thermal vacuum cycles, but temperature ranges varied, depending on the particular thermal control design of each experiment. Temperature monitoring devices showed a temperature range of -50 0C to 120 0C at the extremes. Most materials experienced more moderate temperature cycling. Materials on the leading edge trays, D8 and D9. were struck by an order of magnitude more hypervelocity particles than Impacted the trailing edge trays, D3 and 14 (Refs. 4 and 5). The largest diameter hypervelocity particle-produced crater on M0003, shown in Figure 20. was a 2.5 mm dia. puncture through the Chemglaze A-276-coated, 40 mil-thick aluminum sunshield covering the EPDS on the D8 tray. B. ENVIRONMENT EXPOSURE CONTROL CANISTERS The canisters on trays 1)4 (T6) and D8 ML6) were closed (O-ring seals) preflight and were programmed to open in three stages to obtain different Intervals of exposure on certain materials, Two weeks after the LDEF deployment, the canisters opened to expose a large (-314 area) of specimens. The next canister stepped movement occurred approximately 23 weeks after deployment and exposed an additional tow of samples (-118 additional area). The final canister stepped movement was at approximately 33 weeks and exposed the last tow of samples (1/8 area) by opening to the canister's fullest extension. The canister drawer teturned to the completely closed position at 42 weeks after initial opening and remained closed during the remainder of the LDW mission. Thus, varying exposure times of 9, 19, and 40 weeks were obtained for some samples in addition to the full mission exposure of 69 months for duplicate samples on the other M0003 trays. The canisters were opened in the clean room at Aerospace rougliy 51/2 months after LDEF retrieval. LDEF special investigation group (SIG) personnel were present during this event and assisted in sampling the canister gases and In helium leA testing of the seals. The canisters had lost vacuum and wer both essentially at altmospheric pessure when opened; some leakage of the front seals was dcetc&
10
II. THE M0003 EXPERIMENT DEINTEGRATION
As Principal Investigator for the M0003 experiment, The Aerospace Corporation Mechanics and Materials Technology Center was charged by the Space Test Program with documentation of the handling and disassembly of the M0003 experimental trays and with providing support to the subexperimenters. The support included full photographic documentation of the trays, modules, and quarter-modules from the earliest stages of retrieval through the complete deintegration of the trays, photographic documentation of the condition of the individual samples, packaging and return of the a.amples, and providing flight data to the subexperimenters. The deintegration tasks were documented in a relational computer database. 4th DimenslonTh for the Macintosh computer, as the disassembly
proceede&.
A. INSPECTION AT KENNEDY SPACE CENTER
The deintegration began with inspection of the M0003 trays at Kennedy Space Center after the removal of LDEF from the payload bay of the Shuttle Columbia to the Spacecraft Assembly and Encapsulation Facility 11 clean room at Kennedy. Observations were recorded and NASA photographic surveys were made to document the condition of the trays and samples following their reintroduction into the earth environment (air, humidity. gravity. etc.). The condition of flight control samples and the samples in the canisters could not be recorded as they were not accessible for inspec. don. Following the photographic surveys, Exoeriment M0002, which occupied Module VI on both D3 and D9. was removed from the trays before they were shipped to Arospixie. B. DISASSEMBLY AT THE AEROSPACE (ORPORATION
The four M0003 trays were shipped by air freight to The Aerospace Corporation and unpacked and dssembled in a class 10,000 clean room facility. Or the over 1600 samples on the trays, 1275 were individually examined at Aerospace. Boeing Aerospace had two subiexp imtrnts that occupied entire modules (Module V on D)3 and Module V on 139). These subexperuents wew not disassem. bled at Aerospace. As test samples were removed from the othr modules, they were individually exatnined by optical microscopy and photographed, preserving thke orientation of the samples as mounted on the LDITP. Many of the samples experienced space environnitmt-induced damage such as clazing, srface roughening, discoloratlon, erosion, contamination staining, and hypervelocity impact crater form"on. Not all samples exlioited discernible changes, however. Obseations of the condition of the samples were made by a single examiner who maintained consistent criteria tor the qualitative descriptions of all of the M0003 samples in the visual inspection ad in the optical rucaoscopy exanm ination, Important effects were photographed using optical microscopy at magncficorm from 3X to i00X. A WildHeetbrtug sterconacroscope and a Zeiss Axioplan Pol tc-arch microscoix were used for the examinations. Bright-field. dark-field. and Nomarski diffcrcntial intetference contrast microscopy techniques were used in the examinations. The obscrvwtons of the oditiotin of the samples were entered in teal time into the computer database. The objective of the microscopy examination of the M0003 materials smnples was to provide
the subexperimentets with a quick-look summary of effects observed on thir samples that could assist them in plnning their pot-flight investigations.. Another objectvc of the miscopy exami-
1I
nation was to provide a record of the post-flight condition of all samples in the event that some subexperiments were not claimed by the original investigators. The observations made in the microscopy examination must be considered preliminary as this survey was only the first step in performing detailed analysis on the materials. In-depth analysis of the effects of space exposure on the samples was the prerogative of the subexperimenters and was not the role of the examiner or the deintegration team.
12
IV. THE M0003 DATABASE
A. OBSERVATION AND PHOTOGRAPHIC DOCUMENTATION In the deintegration task, all M0003 samples were given a simple Database Number that corresponded to the more complex Aerospace Sample Identification Code permanently assigned to each sample in the preflight documentation. All entries into the database were keyed on these two identifiers, as illustrated in Figure 21. The Database Number in the example shown is 73. The Aerospace Sample Identification Code contains the M0003 tray location for that sample, the Roman numeral of the module on which it was mounted, its subexperiment number, the sample location number on the module, and the sample designation given it by the subexperimenter. In the example shown, the sample, L311-7-65-10, is a specimen that was flown on tray L3, the leading edge 3-in, deep tray (D9) on Module II. It was part of subexperiment 7 and occupied sample position #65 on Module II (see Figure 9). It was designated as "10" by the principal investigator of the subexperiment. Either the Database Number or the Sample Identification Code can be used to retrieve the sample record which contains information identifying this sample as a ZnS optical coating on a fused silica substrate. The physical dimensions of the sample, the post-flight observations, and the address of the current point of contact are also given in the record. The photographic portion of the database is for the use of the Corporate Archives. It contains the data on the number and type of photographs taken of the individual sample as well as the conditions (lighting, magnification, etc.). Over 3,000 macrographs and photomicrographs were made to document the condition of the M0003 trays and the Individual samples. Overall photographs of the trays, modules, and quartermodules, (front and back) were shot with large format print film In color and black and white. The post-flight tray photographs In this report (Figures 8, 10, 12, and 14) are examples of such photographs. As individual samples were dismounted from the modules, the underlying tiers of the module hardware were photo-documented to display their condition. In addition, photographs of leading and trailing edge module hardware placed side-by-side were made for visual comparison of contamination staining, erosion, discoloration, etc. Photomicrographs made during the optical microscopy examination were recorded on high-resolution 35 mm color print film. The prints of Database Number 73 In Figure 22 are examples of the types of photographs made to document the condition of the samples. Not every sample was photographed In this detail. The observation record for this sample Is shown In Figure 23. This sample is a ZnS optical thin-film coating on a fused silica substrate. The ZnS coating buckled and probably flaked during the 69 months of exposure to the space environment. In addition, minute ring-like features were observed on the buckled surface at high (200X) magnification. Photographic prints and the accompanying observation records can be requested for particular samples (using the Database Number or Sample Identification Code) from the Aerospace Corporation Corporate Archives. B. OBTAINING DATA AND PHOTOGRAPHS The contents of the M0003 Deintegration Observation Record Database are condensed in two tables in the Appendix to this report. One table lists the sample complement by Database Number and gives a sample description and a brief description of Its post-flight condition for each. The second table gives the same sample list sorted by spacecraft application. Many samples fall Into several application categories. These tables can be used to identify samples of interest. Someone interested
13
in obtaining photograp's of materials that show specific effects, i.e., graphite epoxy composites that have impact craters, could survey the description and post-flight condition columns in the first table to find many examples of such materials that are "cratered." Someone interested in adhesives used in bonding thermal control materials on the other hand, could look through the applications table to find thermal control materials that also were listed as adhesives. The Database Number of samples of Interest could be noted and then consulting the first table using the Database Number, the description of the samples and their post-flight condition could be found. The location of the samples, leading edge or trailing edge, could be determined from the Sample Identification Code of each. If photograph prints and hard-copy records were desired, the Database Numbers could be entered on the Aerospace Form to request all photographs and records pertaining to those particular samples. In addition to sample photographs and records and the condensed tables in this report, the entire M0003 Deintegration Observation Record Database is available to requesters on a 1.4 MB (HD) floppy disk In Macintosh 4th Dimension TM format. The database was streamlined to fit on the disk by omitting the photographic portion of the database. A user instruction text file is provided on the disk. The text file contains an explanation of the criteria used by the examiner in compiling the deintegration observations on the samples. The database structure file contains various layouts for searching through the contents of the database data file by Database Number, Sample Identification Code, or by Spacecraft Application. Searches may also be made by material, damage effects, categories, or text strings. Records In the data file include the dimensions of the samples, the descriptions of the composition and construction of the samples, the observations made at Kennedy Space Center, the deintegration observations, and the current subexperiment contacts for additional information on the samples (also publication lists, when available). The Aerospace Corporate Archives maintains a copy of the complete database to coordinate requests for photographs of specific samples. Aerospace Form 5365 Is provided at the end of this report to facilitate requests. Requests should be sent to the Aerospace Corporate Archives, P. 0. Box 92957, Mail Station M2/326, Los Angeles, CA 90009-2957, phone (310) 336-5319; FAX (310) 3365912. The requester should be as specific as possible In stating the type of Information desired (e.g., color prints of full trays, black and white photographs of certain modules, color mlcrographs of a specific sample, and data records). This service will be provided as long as resources allow.
14
REFERENCES 1. R. J.Bourassa and J. R. Gillis, DataSummary Atomic Oxygen Flux and Fluence Calculationfor Long DurationExposure Facility(LDEF), NAS1-18224, Task 12, Boeing Defense and Space Group, Seattle, WA (18 January 1991). 2. R. J. Bourassa, "Atomic Oxygen Fluences Update," LDEF Space Environmental Effects Newsletter, Vol. 11, 6, (15 Nov. 1992). 3. R. J. Bourassa and J. R. Gillis, Solar Exposure of LDEF Experiment Trays, NASA Contractor Report 189554, Boeing Defense and Space Group, Seattle, WA (February .)92). 4. T. H. See, M. A. Allbrooks, D. R. Atkinson, C. G. Simon, and M. Zolensky, Meteoroid and Debris Impact FeaturesDocumented on the Long DurationExposure Facility,A PreliminaryReport, Publication # 84, JSC #24608, (1990). 5. M. J. Meshishnek, S. R. Gyetvay, K. W. Paschen, and J. M. Coggi, LDEF ExperimentM0003 Meteoroidand Debris Survey, Aerospace Report No. TR92(2935)-12, The Aerospace Corporation, El Segundo, CA (1993)
/i
Table I. Summary of M0003 Subexperiments. Subexperiment number
Scope
I
Subexperiment Point of Contact
Organization/Address
-1
Radar camouflage materials and electro-optical signature coatings
Charles Hurley
Univ. of Dayton Research Inst. 300 College Park Dayton, OH 45469-0001
-2
Laser optics
Linda De Hainaut
-3
Structural materials
Charles Miglionico
-4
Solar power components
Terry Trumble
-5
Thermal control materials
Charles Hurley
-6
Laser communication components
Randall R, Hodgson
Phillips Lab/LIDA Kirtland AFB, NM 871176008 Phillips Lab/PLIVTSI Kirtland AFB, NM 87117-6008 Wright Labs/POOC Wright Patterson AFB, OH 45433-6533 Univ. of Dayton Research Inst. 300 College Park Dayton, OH 45469-0001 McDonnell Douglas Astronautics Corp. Mail Code 1067267 P. 0. Box 516
-7
Laser mirror coatings
Terry M. Donovan
-8
Composite materials, electronic piece parts, fiber optics
Gary Pippin
-9
Thermal control materials, antenna materials, composite materials, and cold welding
Brian C. Petrie
Advanced composite materials
Gary L. Steckel
Contamination monitoring, Radiation measurements Laser hardened materials
Eugene N.Borson. F. B. Sinsheimer Randall R.Hodgson
St. Louis, MO 63166
3481 Murdoch Dr. Palo Alto, CA 94306 Boeing Aerospace Co. Materials technology Dept., MS 2E.01 P. o. Box 3999 Seattle, WA 98124
_Sunnyvale,
.10 _
__
-11, -12 -13 ._____ _
_Los
Lockheed Missiles & Space Co. Dept. 62.92, Bldg. 564 P. 0. Box J04 CA 94086 The Aerospace Corp. P. o. Box 92957, M2/242 Angeles, CA 90009 The Aerospace Corp. M2/270 McDonnell Douglas Astronautics Corp. Mail Co0a 1067267 P, O. Box 516 Louis, MO "1166
_St.
-14
Quartz crystal microbalance
Donald A,Wallace
QCM Researctk 2825 Laguna Canyon Road P. 0. Box 277
-15
Thermal control materials
Oscar Esquivel
-16
Advanced polymer composites
Gary L. Steckel
The Aerospace Corp. M2/241 The Aerospace Corp. M21242
.17
Radiation dosimetry
Sam S.Imamoto,
Lanuna Beach, CA 92652
The Aerospace Corp.
J. Bernard Blake
M2/260
-18
Thermal control paints
Christopher H. Jaggers
The Aerospace Corp. M21271
-19
Elect-onic Piece Parts
Seymour Feuerstein
The Aerospace Corp. M2/244
-20
Tray Hardware
Michael J. Mesblshnek
16
The Aerospace Corp. M2/271
Figure 1. The LDEF inspace just after deployment by the Space Shuttle Columbia (April 1984). 17
LDEF Surface Nomenclature SPACE END
12 111 I : .,, = l,
,..,,,
.-'%c'
LEADING EDGE
10
#
2
TRAIUNG EMG
S3
S4
M0003 TRAYS; D3, Wt D8$ D9 EARTH END
Figure 2. Diagram of LDEF showing row and ring nomenclature.
Table 11. Environmenls Experienced by Samples on the MOXX)3 Trays AO
Solar Exposure
(atom*/cm2)
(hr)
Thermal Cycles
Leading edge D9
8.99E 21
11.155
32,422
Leading edge D8
7.1 6E+21
9,409
32,422
Tri lng edge D3
1.32E+3
11,110
32,422
Traling edge D4
2.31E 5
10,458
32,422
Tray
18
~
5.0,
~
~
~
5F n50
Othicso.M
ThF.IQon
MO MAIdLM
Cu
SO) SAon5OA N&Fon $I%,
(AhOySibNfA Sao
MZnSIThFOan
.0-,1
g
"a,. on S04 0 a
S.OPI1U AutCu
SAhOINAu on.Go Lton0PC
ZoSo
Al0n6.0,
ZoISThl'.
794080
AqonAl
hoOF
Toro8.0
AUan.NkClii oW Al ImorCu
oJ MF 110,orVI.
%$Figure 3. Diagram of optical samIples in database.
S21
Smple (354 L O a, 36Rn
IdnoI4M
CermicCopolsiteacMetal
Matt IONO PoysW40A
JioFca ON Fam
4oU SutA sani0n 1 Ml Aried
w
7-mwFvnMi
Figure 4. Diagram
t
te slrcwrlysmlsi
'9am f~w
aaae
Bloch p5414 22 Samples
WhinPtin't 109 Smples.
R 1i4clor 21Smples
0
Coating 117 Sampe
Metallized Polymert 62 Sale
AkvIS.0 1
CMMQIU'oA276
C~mgiIZ*Z3 G
OXtd)&MO
AWFEP
AQISIO? AV.,Ye-7t
293
0411
Aj*6d. Al
AI'Kplon
Swex SP-102
ITV 602 Blacki
Rtoeoaled
J13
707S Sprasylon Bla~kChtonrrWFE
42011 S14WGI0 NS 430
FEWIOqW iciaP01
4mros APlIII h4f Otlonafl
AUK&Won
Usc Ceramicuoarn
PanS
Woe: Some Thermal Control SampleS tall into several categorieS
Figure S. DiugraniC of thcrnial control saniPles Indatabase.
PolyslioreNPolymers
Dacro Pta72ta
Sample Ledig dg. 2tmeegEde
1ole: KWto
6AT hjua~oft
Tell;
Yave"
Somela Poy1i
sarimple ta cgoo
111-a supe ndtbie f oymC
RV-520
Cell Coating
Soa elSolar
HESP 11GaAs HESP 11Si Cu/ln/Se Conventional Si Vertical Junction Si High Performance Si
Electronic Material
350nm AR on SiO2 350 nm AR on Ce-doped SI02 Mark III HEA
Bulk GaAs GaAs FETS CMOs Devices
Others
Note: Not ail Soar Power samples Wai tnto these three categoies
Figure 7. Diagram of Solar Power samples indatabase.
21
Vol'4
al
2lo
(4'83 W01; IsS41% ePIs) 30VdS
00
00
isI
uNEI
1990
L IIJ
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Figure 16. Post-flight photograph of open leading edge canister (Tray D8, Module VI). EARHh (We. mmrt Eart)
nC)
FIN
SPACE(
WO"
ar faro ft"~
Figure 17. Diagram of sample layout on leading edge canister (Tray D8, Module VI). 130
Figure 18. Post-fight photograph of open trailing edge canister (Tray D4, Module VD). RARMH (sift nsat hth)
CAI -'
Figure 19. Diagram of sample layo.ut on trailing edge canister (Tray D4, Module VI).
31
- mw7
T
Figure 20. View of two hypervelocity particle impacts to the Chemnglaze A276-painted sunshield on leading edge Tray D4 (U6). The puncture is 2.5mm in diameter. The second impact created a small crater surrounded by an exfoliated zone in the atomic oxygen-eroded paint.
Sample Data Bfase # Sample ID Code L3--65-10 Leading Edge
rm nc
wue~ C od
3-In, tray (D9) ortisale Modulej Sample # on Module Subexperiment #
Data Base Obsirvation
Subexperiment
Record
Point or Contact
Material coutposition imensions
N-ame Addma~
Obsevations, Del
Publicatimn
Observations, KSC
Phone #
Figure 21. Diagram of M0003 database. 32
L
I;
M
....
f
Xxt"4&'
'30.,
V,
333''
I1SJ4
C7E
Co.
Au$~
74;
*4'*~
"A. ~~~%d'' "-AN"* .9-4'4
10x9,
,
C:
'a.a
Siml-
33
LDEF M0003 Sample Observation Sample ID: L311-7-65-1O0 Database #: 7 3 0.375
Width: Length Thickness
Tray: D9
Module: II
Experiment:
7
Description: ZnS coating on Si2 substrate Post-flight Condition: Buckled (+), delaminated
Exposure: 69 months
0.100
Category: Coating, glass Subcategory: Coated substrate Application: Optics Observations at KSC Before Do-Integration: SURFACE CRACKED, FLAKING
Observations at Date Tuesday, May 15,1990 The Aerospace Corporation: The exposed coating appears uniformly buckled; some areas have buckled so severely that the coating has flaked. In the flaked areas, the residual surface (the substrate) is smooth. Another phase appears to have nucleated on the top of the buckled surface. This phase Is manifested, in various stages of formation, as crescent-, ring- or circular.shaped features on the surface.
Publications: 1, T,M.Donovan, J. M,Bennett, and S. Gystvay, 'Space Environmental Eflects on Coated Optics," Proceedings of the First Post.Retrieval Symposium. Kissimmee. FL. June 2.8, 1991, NASA Conference Publition 3134. Part 3
Point of Contact: Terry Donovan 3481 Murdoch Dr. Stanford (000) 0000000
CA 94306 FAX: ()000.0000
Mechanics and Materials Technology Center THE AEROSPACE CORPORATION
Figure 23. Example of hard copy database observation record (DB#73).
34
APPENDIX A
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