NASA 

Technical 

Memorandum 

NASA TM - 86578 

, 

(NASA-2E-66575) IRE NCN-ME3ALLIC MATERIALS N87-70910 

SBBPLE AERAY (NASA) 20 p CSCL 71u 

Unclas 

G3/27 43851 

National Aeronautics and 

Space Ad ministration 

George C. Marshall Space Flight Center 

THE NON-METALLIC MATERIALS SAMPLE ARRAY 

By H. M. King, D. D. Webb, and B. E. Goldberg 

Materials and Processes Laboratory 

Science and Engineering Directorate 

December 1986 

MSFC - Form 3190 (Rev. May 1983) 
LIST OF ILLUSTRATIONS 

Figure 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

Title Page 

SL-2 pallet view C-C ................................................. 

MSA diagram and sample location guide for SL-1 ...................... 

4 

5 

6 

7 

8 

9 

10 

MSA diagram and sample location guide for SL-2. ..................... 

MSA SL- 1 preflight configuration ..................................... 

MSA SL- 2 preflight configuration ..................................... 

PJSA SL-2 post flight ................................................. 

MSA SL-2 post flight ................................................. 

LIST OF TABLES 

Table Title Page 

11 

12 

13 

13 

14 

1. 

2. 

"B" Sample Optical Properties ....................................... 

"A" Sample Optical Properties ....................................... 

3. Miscellaneous Optical Properties. ..................................... 

4. Transfer Tunnel Flex Section.. ...................................... 

5. Visual Observations of Samples, Post SL-1.. ......................... 

iv 
TECHNICAL MEMORANDUM 

THE NON-METALLIC MATERIAL SAMPLE ARRAY 

INTRODUCTION 

This report provides the results of the evaluation of material specimens exposed 

to the cargo bay environment during Spacelab (SL) missions 1 and 2. 

specimens were mounted on the Non-Metallic Materials Sample Array (MSA), DWG . 42A40015, and exposed to the ambient flight environment at a location near the righthand pallet sill just forward of the cargo bay aft bulkhead (Fig. 1). 

an article of GFE provided to satisfy a portion of the materials performance evaluation 

requirements during the Spacelab Verification Test Program. 

The material 

The ISIISA was 

EXPERIMENTAL 

The MSA (Figs. 2 and 3) was a 4-ft by 1-ft package, housing test samples 

representing three modes for performance evaluation. The majority of the rrA1r samples 

and the rrCrr sample on SL-2 were equipped with temperature transducers; IrBrl samples 

were designed for pre- and post-flight optical properties measurements ; r?C1r samples 

represent transfer tunnel flex section materials and multilayer insulation and are 

suited for pre- and post-flight evaluations. 

Post -flight optical properties and visual observations were recorded upon 

receipt of the array at MSFC. 

the two missions. 

The Deft 023-GW-3 (A-17 and B-09) had been flown uninstrumented on SL-1 but was 

not flown on SL-2 because the material was no longer commercially available - instead 

A- 17 and B- 09 positions were reflown with Chemglaze 2302 overcoated with RTV670. 

This combination was selected to evaluate the effectiveness of the silicone top coat 

(RTV 670) to protect the 2302 from atomic oxygen attack. 

son A13 position was reflown with Chemglaze 2302 coating without a topcoat of silicone. The rubber system flown on SL-1 in the A13 position was not of sufficient 

interest to justify a second mission. The only other change between missions was 

that the systems tunnel flex section (Sample C) was instrumented with a temperature 

transducer. 

There were minor differences in the array as flown on 

Samples A-13, A-17, and B-09 were changed between missions. 

For purposes of compariThe optical properties data gleaned from the MSA are summarized in Tables 1 

through 3. 

prepared simultaneously with the flight samples and stored in dust-proof containers 

in an area devoid of light, natural or artificial. 

Data from samples identified as controls represent duplicate specimens 

The physical properties data for the transfer tunnel flux section material is 

presented in Table 4. 

Rubber Co., the manufacturer of the flex section material (Nomex reinforced Viton) . This data was generated by both MSFC and the Goodyear 

The summary of the visual inspection is given in Table 5 for Mission SL-1. The 

post SL-2 examination showed no visible differences from SL-1. The RTV 670 overcoated Chemglaze 2302 was degraded more than expected. 
D I S CU S S ION 

The Non-Metallic Materials Sample Array (MSA) was successfully flown on SL- 1 

and SL- 2 missions. Observations after each flight showed degradation of selected 

materials, specifically Chemglaze I1 A276, 3M 425 tape, Chemglaze 2306, Chemglaze 

2302, Chemical Conversion Coating , and Aluminized Kapton tape. In general , exposed 

surfaces degraded to some extent due to both atomic oxygen attack and UV 

degradation. 

The Chemglaze II-A276 appears to have suffered selective UV degradation on 

the retainer plate (Part No. 42A 40017) regions which had pre-flight contact with a 

silicone rubber seal which was part of the non-flight MSA cover. The selective 

yellowing and the maintenance of surface gloss, characteristic of UV rather than 

atomic oxygen degradation, was also noted on regions of sample disks adjacent to the 

gap in the sample retaining rings. 

off-gassing products from the silicone foam cushion underneath each disk. 

This gap appears to function as a vent for the 

The off-gassing products from the silicone foam are not stable against UV 

The extent to which this yellowing contributed to the 

degradation, as evidenced by the yellowing observed in the "vent zone" of the 2-93 

and S-13GLO specimens. 

observed yellowing of Chemglaze A-276 on the retainer plate could not be determined. 

The A-276 coating is known to be susceptible to UV degradation (yellowing) from 

ground test and previous flight results. The yellowed, glossy regions of the retainer 

plate were unchanged after the second mission (SL-2). 

Thermal data from each disk was recorded in an attempt to determine the kinetics 

of the degradation. 

to the time of change was possible. 

Due to the minimal changes in optical properties, no correlation 

The Chemglaze coatings A-276, 2-302, and 2-306, and 3M 401-C10, and the 

exposed Kapton side of the aluminized Kapton tape exhibited the typical effect of 

atomic oxygen attack , loss of surface gloss and/or change in visual appearance. 

These effects were produced during SL-1; the second mission (SL-2) produced little 

change. 

Data from the Multilayer Insulation (MLI) and transfer tunnel flex section show 

little effects other than superficial yellowing of the R?LI and loss of gloss of the flex 

tunnel section. 

CONCLUSIONS 

The observed changes in optical properties are quite minimal and do not indicate 

gross contamination from the Spacelab hardware or experiments nor from the payload 

bay. The contamination from the silicone material used incidentally in the MSA hardware amply demonstrates the local contamination effects possible from materials which 

comply with the general outgassing requirements for Shuttle payloads. The experimental coating hybrid of Chemglaze 2302 overcoated with a clear silicone, RTV670, 

confirm the hypothesis that silicones can inhibit the effects of atomic oxygen on 

underlying coatings. 

2 
Analysis of the optical properties data indicates the short duration of exposure 

The significance of the data must be determined for the coating of interest 

to be generally insufficient for conclusive quantifying of space effects on these coating 

systems. 

in conjucntion with other flight histories - the MSA experience cannot stand alone. 

Data from the Multilayer Insulation (MLI) and systems tunnel flex section reveal 

only superficial effects of the cargo bay environment on these materials. 

In summary, the Non-Metallic Katerials Sample Array (PLSA) was flown successfully as Verification Flight Instrumentation on SL-1 and SL-2. 

gathered on many coating systems; however, the short duration of exposure to the 

space environment limits the usefulness of the data. 

cautious ; other flight histories must be considered when selecting a candidate coating 

for the Shuttle cargo bay environment ; the MSA data is not definitive. 

Valuable data was 

Users of this data must be 
I 

I 

I 

\ 

\ 

I 

I 

I 

a 

a 

\ 

\ 

a 

1 

I 

\ I: ---- 

0- 

0- 

/- 

I 

1 

4 
"A" Samples Samp 1 e s 

Retainer Plate 

Mat er ial 

2-93 

S- 13GLO 

Chemglaze I1 -A276 

Chemglaze 2-306 

Chemglaze 2-302 

Anodiz e 

Chemical Conversion Coating 

Deft 023-GW-3 

Tedlar Laminate 

Silverized Teflon (Sheldahl G 400300) 

Aluminized Tape Kapton 

Aluminized Tape (3M 425) 

Silicone Rubber (RA 38250) 

B-Cloth/MSFC Light Block 

B-Cloth/JSC Light Block 

B-Cloth/No Light Block 

Transfer Tunnel Flex Section 

Multi-layer Insulation 

3M 401-C10 

Sample Posit ion 

01 

02 

04 

05 

06 

03 

07 

08 

17 

09 

10 

12 

11 

13 

14 

15 

16 

01 

02,14 

03,10,7 

04,18 

05 

06,16 

07 

08 

09 

13 

11 

15 

12 

- 

- 

- 

- 

X 

X 

Figure 2. &(SA diagram and sample location guide for SL-1. 

5 
Material 

2-93 

S- 13GLO 

Chemglaze I1 -A276 

Chemglaze 2-306 

Chemglaze 2-302 

Anodize 

Chemical Conversion Coating 

Chemglaze 2302 

Tedlar Laminat e 

Silverized Teflon (Sheldahl G 400300) 

Aluminized Tape Kapton 

Aluminized Tape (3M 425) 

Chemglaze Z302/RTV670 

B-Cloth/MSFC Light Block 

B-Cloth/JSC Light Block 

B-Cloth/No Light Block 

3M 401-C10 

Transfer Tunnel Flex Section 

Multi-layer Insulation 

A 

01 

02 

04 

05 

06 

03 

07 

08 

17 

09 

10 

12 

11 

13 

14 

15 

16 

- 

Sample Position 

- B - C 

01 

02,14 

03,10,7 

04,18 

05 

06,16 

07 

08 

09 

13 

11 

15 

12 

X 

X 

Figure 3. USA diagram and sample location guide for SL-2. 
OR168NAL PAGE .IS 

OF POOR QUALITY 
8 
ORIGINAL PAGE .I3 

OF POOR QUALm .I 

9 
i b 
TABLE 1.. "B" SAMPLE OPTICAL PROPERTIES* 

I'IU- VI, 1 (:Iu 1'OS'l'- 1: I I I (: II'r (s1.- 1 ) "S'r -PI. LGl1'1' ( s I,- 2 ) 

MATERIAL a a a 

293 0.16 0.16 0.15 

S13GLO 0.18 0.18 0.19 

Cow ROL 

SAMPLE a 

BO1 

BO2 

BO3 

BO4 

BO5 

BO6 

BO7 

BO8 

0.16 

0.18 

IIA276 0.25 0.25 0.21 0.25 

2306 0.95 0.99 0.99 0.95 

2302 0.95 0.98 0.97 0.95 

401C10 0.97 0.98 0.99 0.97 

Anodize 0.41 0.41 0.40 0.41 

Conversion 0.42 

Coating 

0.40 0.40 0.42 

BO9 

B10 

B11 

Deft 0.69 0.68 - 0.69 

0.25 

0.06 

IIA276 0.25 0.25 0.25 

Silverized 0.06 0.06 

Teflon 

0.06 

B12 425 Aluminized 0.21 

Tnpt 

0.17 0.17 0.21 

U13 'red Inr 

Laminate 

0.24 0.24 0.26 0.24 

B14 

B15 

S13GLO 0.19 0.19 0.19 0.19 

Aluminized 0.33 0.33 

Kapton 

0.44 0.43 

B16 

B17 

B18 

401C10 0.97 0.98 0.98 0.97 

0.25 

0.96 

IIA276 0.26 0.25 0.27 

2306 0.96 0.98 0.99 

*'Data from Beckman DK2A Spectrophotometer with Gier-Dunkle Integrating Sphere 

11 
SAMPLE 

A0 1 

A02 

A03 

A04 

A0 5 

*A0 6 

A07 

A08 

A09 

A1 0 

A1 1 

A1 2 

A13 

A14 

A15 

A16 

A1 7 

MATERIAL 

TABLE 2. "A" SAMPLE OPTICAL PROPERTIES* 

293 

S13GLO 

401C10 

IIA276 

2306 

2302 

Anod iz e 

Conversion 

Coat 

Tedlar 

Laminate 

Silverized 

Teflon 

425 Tape 

Aluminized 

Kapton 

Silicone 

Rubber 

B-Cloth ASS'Y 

MSFC L.B. 

B-Cloth ASS'Y 

JSC L.B. 

B-Cloth ASS'Y 

Deft Primer 

PRE-FLIGHT 

E 

0.92 

0.92 

0.91 

0.90 

0.91 

0.90 

0.82 

0.07 

POST-FLIGHT (SL-1) POST-FLIGHT (SL-2) F 

0.91 

0.90 

0.91 

0.89 

0.93 

0.90 

0.92 

0.07 

0.91 

0.89 

0.90 

0.88 

0.92 

0.90 

0.82 

0.06 

0.91 0.90 0.90 

0.68 0.65 0.65 

0.03 

0.54 

0.03 

0.50 

0.03 

0.53 

0.90 0.91 - 

0.91 0.90 0.90 

0.90 0.90 0.90 

0.90 

- 

0.90 

0.87 

* 

Data from Portable Instrumentation - Gier-Dunkle DB200 

0.90 

- 

CONTROL 

E 

0.91 

0.90 

0.90 

0.89 

0.91 

0.90 

0.82 

0.08 

0.90 

0.66 

0.03 

0.51 

0.91 

0.90 

0.90 

0.90 

0.67 

12 
TABLE 3. XISCELLANEOUS OPTICAL 

PRE-FL IGHT POST SL-1 

SAMPLE -- a E - a 

Section C 

ML I 0.21 0.90 0.22 

Flex Section 

Exposed 0.93 0.88 0.95 

Flex Section 

Shielded 0.93 0.88 0.93 

A13 

(Chemglaze 2302) 0.94 0.90 - 

(Chemglaze 23021 0.93 0.91 - 

A1 7 

RTV 7 60 ) 

BO9 

( C hemg laze 2 3 02 / 0.96 - - 

RTV760) 

- E 

0.90 

0.88 

0.88 

- 

- 

- 

PROPERTIES* 

POST SL-2 

- a 

0.22 

0.94 

0.92 

0.94 

0.93 

0.97 

- E: 

0.90 

0.88 

0.88 

0.90 

0.91 

- 

* 

Data primarily from portable instrumentation 

a Gier Dunkle MS251 

E Gier Dunkle DB200 

TABLE 4. TRANSFER TUNNEL FLEX SECTION 

- Physical Data - 

MSFC DATA 

Weight Change 

Thickness Change 

Shore Hardness "C I' 

SEM Results 

GOODYEAR DATA * 

Hardness ("Shore A") 

Section A Section B 

(Exposed) (Shielded) 

- 0- -0- 

- 0- -0- 

70 72 

Surface roughening of exposed 

sect ion 

CONTROL 

-- a E 

0.22 0.90 

0.93 0.88 

0.93 0.88 

0.95 0.90 

0.95 0.91 

0.96 - 

Section C 

(Control) 

-0- 

- 0- 

68 

tunnel 

Control Exposed Shielded 

90 93 S8 

Tensile (lbs/in) 1068 1143 1088 

*This data was obtained courtesy of McDonnell Douglas Aerospace Corporation - 

Huntsville. 

13 
TABLE 5. VISUAL OBSERVATIONS OF SAMPLES, POST SL-1 

MATERIAL OBSERVATIONS 

293 

S 13GLO 

Chemglaze 

IIA276 

Visible yellowing in vent zone 

Visible yellowing in vent zone 

Yellowing in silicone contaminated regions. The 

normally glossy coating changes to Lambertian in 

regions not contaminated with silicone. 

No change in silicone contaminated regions. The 

remaining surface area was Lambertian, consistent 

with expected atomic oxygen attack. 

No change in silicone contaminated regions; the 

remaining surface area was Lambertian. Extreme 

degradation of specular reflectance was noted. 

Apparent darkening of the entire surface. 

silicone effect noted. 

No 

Chemglaz e 

2306 

Chemg 1 az e 

2302 

3M 401-C10 

Anodize No visible changes noted. 

Variable changes in coloration; the majority of the 

sample appeared to have lost coating. 

Chemical Conversion 

Coating 

Variable changes in coloration; the regions away from 

the vent zone appeared to have lost coating thickness. 

Degradation does not appear critical to usage in nonoptically-critical areas. 

Deft 023-GW3 

Yellowing in the silicone vent zone; in addition, the 

remainder of the surface area was greyed. 

Tedlar Laminate 

Silverized Teflon No visible changes noted. 

No change in silicone contaminated regions; the 

remaining surface area was Lambertian. 

Aluminized Tape 

Kapton 

425 Aluminized Tape Slight discoloration 

Silicone Rubber No changes 

B-Cloth/MSFC 

Light Block No significant changes 

B-ClothIJSC No significant changes 

Light Block 

B-Clo thh No significant changes 

Light Block 

Slight yellowing of exposed side 

No change in shielded side; the exposed side 

was Lambertian. Scanning Electron Microscopy 

at lOOOX indicates a roughening of the surface 

of the exposed transfer tunnel material. 

MLI 

Transfer Tunnel 

14 
I 

APPROVAL 

THE NON-RSETALLIC MATERIALS SAMPLE ARRAY I 

By H. M. King, D. D. Webb, and B. E. Goldberg 

The information in this report has been reviewed for technical content. 

of any information concerning Department of Defense or nuclear energy activities or 

programs has been made by the MSFC Security Classification Officer. This report, 

in its entirety, has been determined to be unclassified. 

Review 

sses Laboratory 

15 
1. REPORT NO. 2. GOVERNMNT ACCESSION NO. 

NASA TM-86578 

4. TITLE AND SUBTITLE 

Non-Metallic Materials Sample Array 

3. RECIPIENT'S CATALOG NO. 

5. REPORT DATE 

I 

7. AUTHOR(S) I 8. PERFORMING ORGANIZATION REPOR r # 

H. M. King, D. D. Webb, and B. E. Goldberg 

9. PERFORMING ORCANIZATtON NAME AND ADDRESS 10. WORK UNIT NO. 

George C. Marshall Space Flight Center 

Marshall Space Flight Center , Alabama 35812 

12. SPONSORING AGENCY NAME AND ADDRESS 

- 

National Aeronautics and Space Administration 

Washington , D .C . 20546 

11. CONTRACT OR GRANT NO. 

13. TYPE OF REPOR;' & PERIOD COVEREC 

Technical Memorandum 

1.1. SPONSORING AGENCY CODE 

19. SECURITY CLASSIF. (d thle rmport) 20. SECURITY CLASSIF. (or tum p.pe) 21. NO. OF PAGES 

Unclassified Unclassified 20 

I 

15. SUPPLEMENTARY NOTES 

Prepared by Materials and Processes Laboratory , Science and Engineering Directorate. 

22. PRICE 

NTIS 

The Non-Metallic Materials Sample Array (MSA) was flown as verification flight 

instrumentation (VFI) on both Spacelab 1 (SL-1) and Spacelab 2 (SL-2). The basis 

for materials selection was either previous flight history or probable flight suitability 

based upon analysis. 

The observed changes in the optical properties of the exposed materials are, in 

general, quite minimal; however, this data represents the short exposure of two 

Space Shuttle missions, and no attempt should be made to extrapolate the long-term 

exposure. 

The MSA was in orbit for 10 days at approximately 240 km on SL-1 and for 

7 days at approximately 315 km on SL-2. 

for only a portion of the time in orbit. 

The array was exposed to the solar flux 

17. KEt WORDS 18. DISTRIBUTION STATEMENT 

Thermal Control 

Space Environment Unclassified - Unlimited