SMC-TR-00-03 AEROSPACE REPORT NO. TR-2000(8565)-8

Space Environmental Stability of Tedlar with Multi-Layer Coatings: Space Simulation Testing Results

20 August 2000

Prepared by

W. K. STUCKEY and M. J. MESHISHNEK Space Materials Laboratory Laboratory Operations

Prepared for

SPACE AND MISSILE SYSTEMS CENTER AIR FORCE MATERIEL COMMAND 2430 E. El Segundo Boulevard Los Angeles Air Force Base, CA 90245

Engineering and Technology Group

THE AEROSPACE CORPORATION El Segundo, California

APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED

20010305 If9

This report was submitted by The Aerospace Corporation, El Segundo, CA 90245-4691, under Contract No. F04701-93-C-0094 with the Space and Missile Systems Center, 2430 E. El Segundo Blvd., Los Angeles Air Force Base, CA 90245. It was reviewed and approved for The Aerospace Corporation by P. D. Fleischauer, Principal Director, Space Materials Laboratory. Michael Zambrana was the project officer for the Mission-Oriented Investigation and Experimentation (MOIE) program.

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.

idu Michael Zambrana SMC/AXE

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1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE

20 August 2000 3. REPORT TYPE AND DATES COVERED

4. TITLE AND SUBTITLE

Space Environmental Stability of Tedlar with Multi-Layer Coatings: Space Simulatin Testing Results

5. FUNDING NUMBERS

F04701-93-C-0094 6. AUTHOR(S)

W. K. Stuckey and M. J. Meshishnek

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

The Aerospace Corporation Laboratory Operations El Segundo,CA 90245-4691

8. PERFORMING ORGANIZATION REPORT NUMBER

TR-2000(85665)-8

9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) Space and Missile Systems Center Air Force Materiel Command 2430 E. El Segundo Boulevard Los Angeles Air Force Base, CA 90245

10. SPONSORING/MONITORING AGENCY REPORT NUMBER

SMC-TR-00-03

11. SUPPLEMENTARY NOTES

12a. DISTRIBUTION/AVAILABILITY STATEMENT

Approved for public release; distribution unlimited 12b. DISTRIBUTION CODE

13. ABSTRACT (Maximum 200 words) Cloud White Tedlar with a multi-layer, thin-film coating on the surface applied by Optical Coatings Laboratory, Inc.

(OCLI) is being investigated for potential spacecraft applications. Space environment exposure tests have been performed on a variety of samples exposed to simulated Low Earth Orbit (LEO) and Geosynchronous Orbit (GEO) conditions. The Space Environmental Effects Chamber used to provide the simulation of the LEO and GEO space environment contains a 2500-W xenon arc lamp for long-wavelength ultraviolet (UV) and a 150-W deuterium arc lamp for vacuum UV radiation. Beam sizes are a nominal 10 in. x 12 in. for long-wavelength UV and 7 in. x 7 in. for vacuum UV. The electron beam is about 14 in. x 14 in. with a beam energy variable from 5 keV to 120 keV. All beams are confocal. The large beam area allows multiple samples to be exposed and compared during a test.

Several tests have been performed for at least 2500 equivalent sun-hours. The initial value for solar absorptance of the 0.002-in. Cloud White Tedlar film was 0.12, while the multi-layer-coated Cloud White Tedlar was 0.09. After a five-year solar UV exposure, the solar absorptance values were 0.32 and 0.10, respectively. The presence of the coating provides excellent stability to the solar UV compared to uncoated Tedlar.

Electron depth dose curves have been calculated for a LEO orbital environment of 410 nmi and for a GEO orbit. These curves are presented along with the selected simulation electron energies and fluences to replicate the expected on-orbit exposure in the coated Tedlar material. Electron irradiations corresponding to LEO and GEO orbits were then performed. All samples were removed for solar absorptance end-of-life measurements. Data are presented for the coated Tedlar mat- erial for both LEO and GEO orbital exposures. The multi-layer coating on Tedlar provides protection from the damaging portion of the UV solar spectrum and would provide protection from the atomic oxygen environment as well. The material is very stable for LEO environments but does degrade in GEO exposure conditions for the multi-layer coating configuration studied.

14. SUBJECT TERMS

Space simulation, Space radiation, Space environmental effects, Spacecraft materials, Thermal control materials

15. NUMBER OF PAGES

24 16. PRICE CODE

17. SECURITY CLASSIFICATION OF REPORT

UNCLASSIFIED

18. SECURITY CLASSIFICATION OF THIS PAGE

UNCLASSIFIED

19. SECURITY CLASSIFICATION OF ABSTRACT

UNCLASSIFIED

20. LIMITATION OF ABSTRACT

NSN 7540-01-280-5500 Standard Form 298 (Rev. 2-89) Prescribed by ANSI Std. Z39-18 298-102

Preface

This work was presented in a poster session at the 8th International Symposium on "Materials in a Space Environment" and 5lh International Conference on "Protection of Materials and Structures from the LEO Space Environment," Arcachon, France 5-9 June 2000. The authors would like to express their appreciation for the cooperation and helpful discussions with Dr. James Barrie of the Space Materials Laboratory of The Aerospace Corporation and Dr. Fred Van Milligan of Optical Coating Laboratory, Incorporated, Santa Rosa, California. Support for this work through SMC Contract F04701-00-C-0009 is gratefully acknowledged.

ill

Contents

1. Introduction 1

2. Experimental 3

3. Results 7

4. Conclusion 9

Charts for the Poster Presentation 11

Figures

1. The space environmental effects chamber 3

2. Test configuration for LEO exposure 4

3. Predicted simulation dose profiles and orbital dose profile for LEO orbit 4

4. Predicted simulation dose profiles and orbital dose profile for GEO orbit 5

5. Reflectance curves for coated Tedlar sample 8

6. Solar absorptance degradation curve for coated Tedlar sample 9

Table

1. Solar Absorptance and Transmittance Data.

1. Introduction

Tedlar is a polyvinyl fluoride film produced by E. I. DuPont de Nemours & Co. (Inc.) with a variety of additives that can be introduced to produce different properties. The designation code of TWH is for a white Tedlar film, and a TCW designation is indicative for a Cloud White version that has a lower solar absorptance (is a whiter material). The full designation for these products, for example, TCW20BE3, identifies color, thickness, surface finish, gloss, and type of elongation properties.

Cloud White Tedlar with a multi-layer, thin-film coating on the surface applied by Optical Coating Laboratory, Inc. (OCLI) is being investigated for a number of potential spacecraft applications. A space environment exposure test has been performed on a variety of samples exposed to simulated Low Earth Orbit (LEO) and Geosynchronous Orbit (GEO) conditions. The final portion of the test was performed to represent 10-year GEO environmental exposure on a subset of samples from the LEO test. This report addresses the samples exposed to GEO conditions.

The first portion of the test exposed the samples to an environment corresponding to five years at a LEO orbit of 410 nmi and an inclination of 57°. All samples were removed for LEO solar absorp- tance end-of-life measurements. The exposure then continued to 10-year GEO conditions (19,270 nmi) for the remaining samples. Solar absorptance at end-of-life for the GEO samples was then measured.

2. Experimental

The Space Environmental Effects Chamber ( Figure 1) used to provide the simulation of the LEO and GEO space environment contains a 2500-W xenon arc lamp for long-wavelength ultraviolet (UV) (230-400 nm) and a 150-W deuterium arc lamp for vacuum ultraviolet (VUV) radiation (115-200 nm). Beam sizes are a nominal 10 in. x 12 in. for long-wavelength UV and 7 in. x 7 in. for VUV. The UV beams have a uniformity within 50% but contain small central hot spots. The electron beam is about 14 in. x 14 in. and is more uniform at about 10%. The beam energy is variable from 5 keV to 120 kV with flux roughly proportional to electron energy and a function of beam spot size (max. 1000 cm ). All beams are confocal. The chamber is turbopumped and cryopumped, and the base pressure is currently 2x10" torr. The volume is roughly 400 liters with a sample table (12 in. x 48 in.) capa- ble of temperature control from -150°C to +150°C, but kept at about 25°C for these tests. Comput- erized data acquisition is used for chamber diagnostics, which include several temperature and elec- tron flux measurements.

The sample arrangement in the chamber is shown in Figure 2. The larger area represents the approximately 10 in. X 12 in. area covered by the xenon lamp. The area covered by the deuterium lamp is about 7 in. in diameter so it does not illuminate all samples in the LEO exposure. The solar cell is used as a diagnostic during the exposure to monitor the xenon lamp output. The Faraday cups monitor the electron flux at several locations during the electron exposure. An Optical Solar Reflec- tor (OSR) is present as a check for any contamination that might condense during the test and poten- tially affect test results.

1 - 20 keV electron gun or Deuterium

vacuum ultraviolet lam

f~

(_J>| lurbo- I C\ nolaculi I Q pump I

Xenon Arc Lamp

solar simulator (ultraviolet

source^

1-20 keV electrons

orD2 vacuum

ultraviolet light

ultraviolet light

5 -120 keV electrons

0 - 50 keV protons

entry/exit door

side view

Faraday Cup * Thermocouple

■™ Sample Irradiation area: 12"

Base pressure: 3 x 10"' torr

Figure 1. The space environmental effects chamber.

® Faraday Cups

Figure 2. Test configuration for LEO exposure.

The electrons were added in the presence of Solar UV in the final stages of each exposure. The UV was not started until the chamber pressure was in the low to mid 10 torr region. After accumulation of 2554 equivalent UV sun-hours (982 h, at a solar intensity of 2.6 suns), electron doses were added to correspond to a LEO orbit of 410 nmi at a 57° inclination. These fluences are based on predicting the depth-dose electron profile in Tedlar for the assumed orbit using AE8 maximum predictions of electron fluences. The best set of reasonable conditions using the set energies of the electron gun on the chamber were chosen to match the depth-dose profile via a linear combination of multiple ener- gies. The prediction curves are shown in Figure 3 for Low Earth Orbit Exposure and Figure 4 for Geosynchronous Orbit. The electron exposures were performed starting with the highest energy first and progressing successively to lower energies. The LEO test was performed with an electron current of about 0.1 nA/cm2, corresponding to 6.25 x 108 electrons/s-cm . This level is typical of the current expected on orbit, although it fluctuates dramatically.

^Electron Ooae Depth Profile far Tedlar TCW20BE3, 2.0 mil

!5 Years at 410 nml/57° Model: AE8 MAX. Cods: ITS »3.0 Electron Fluence: 6.75 E13/cm2

-— Dose_410/57* Dose_10Kev(8.5E12)

Dose_20KeV(1.2E13) - - - Dose_35 KeV (6.4 E12)

Dose_50KeV(1.5E13) Dose_100KeV(2.4E13)

■ DOSE_SUM

1.0

Depth, mil*

Figure 3. Predicted simulation dose profiles and orbital dose profile for LEO orbit.

JElectron Dose Depth Profile for TedlarTCW20BE3, 2.Q mil |

10 Years at 19,270 nmM>" (3EO) Model: AE8 MAX. Code: ITS v 3.0 Electron Fiuence: 9.0155 E15'cm2

Dose_GEO - Dose_100Kev(3.3E15)

Dose_50KeV(1.9E15) Dose_35KeV(8.6E14)

•Dose_20KeV(1.4E15) Dose_10KeV(1.3E15)

- DOSE_SUM

Depth, mils

Figure 4. Predicted simulation dose profiles and orbital dose profile for GEO orbit.

After 2917 equivalent UV sun-hours, (1122 h, at a solar intensity of 2.6 suns), the LEO electron exposure was completed, and the LEO samples were removed. The UV exposure was then continued on the remaining samples up to 4282 sun-hours (1647 h, at a solar intensity of 2.6 suns) while the GEO electron dose was added. The GEO test was performed with an electron current of about 1 nA/cm2 to more rapidly accumulate the desired fiuence. This level of current could be expected on orbit, although it fluctuates dramatically. Throughout the entire exposure, the deuterium lamp was cycled on periodically (effectively 3.75 h per day) to accumulate approximately the same number of equivalent UV sun-hours as the xenon source. The deuterium source has been estimated to have an initial output of about 17 solar constants over its operating wavelength range, as compared to about 2.6 for the xenon source. The xenon source output is spectrally calibrated pretest using a calibrated spectral radiometer. Relative intensity over the sample area is mapped with a solar cell.

The following method was used to obtain the solar reflectance, transmittance, and absorptance. The Ultraviolet-Visible-Near Infrared (UV-VIS-NIR) diffuse hemispherical reflectance was measured on a Perkin-Elmer Lambda-9 equipped with a 6-in. Labsphere, Inc. Spectralon-coated integrating sphere. The reflectance measurements were made using a 240 nm/min. scan rate, 2 nm slit width, 0.5-s response, with the scan range being 250-2500 nm. The reflectance spectrum was background- corrected and referenced to a NIST 2019d White Tile Diffuse Reflectance Standard. The sample spectra were then normalized to the ASTM E490 solar air mass zero curve to obtain the solar absorp- tance/transmittance.

3. Results

During the exposure, photographs were taken periodically through the chamber viewports, and a short video was taken through an overhead viewport each day. The uncoated White Tedlar (TWH) samples were observed to turn brown during the initial LEO exposure to the UV. The Chemglaze A276 white paint sample also darkens, as expected from prior tests and from flight experience from the Long Duration Exposure Facility, for example. This material is included as a control sample for the exposure test. At the end of the LEO exposure, the changes in solar absorptance for the OCLI-coated Tedlar samples have been measured to be -0.05 or less. The values are different for different samples due to the solar transmission of the 2-mil OCLI-coated Tedlar that is the outer layer of each sample. The differing underlying layers result in different solar properties. The measurement data is presented in Table 1.

The solar absorptance and transmittance data in Table 1 are consistent with the visual observations. The solar absorptance of the OCLI-coated TCW20BE3 has increased significantly with the GEO exposure (~6x over LEO). Again, the variations from sample to sample are due to effects of the underlying layers. The post-test solar absorptance was lowest for samples MLI-21 and MLI-22 with two underlying layers of Cloud White Tedlar (TCW). The most degradation appears to be for the case with two layers of White Tedlar (TWH) as the underlying layers. Figure 5 shows the changes in reflectance of one sample for the LEO and GEO exposures.

Table 1. Solar Absorptance and Transmittance Data

LEO

Sample # Pretest p Pretest x Pretest a Posttest p Posttest T Posttest a Delta a

RDM 03 0.82 0.18 0.817 0.183 0.003

RDM 22 0.813 0.187 0.763 0.237 0.05

MLI03 0.633 0 0.367 0.633 0.367 0

MLI21 0.822 0.024 0.154 0.791 0.026 0.183 0.029

MLI22 0.821 0.029 0.15 0.784 0.031 0.185 0.035

MLI23 0.782 0.003 0.215 0.728 0.003 0.269 0.054

MLI24 0.774 0.003 0.223 0.733 0.003 0.264 0.041

MLI25 0.781 0 0.219 0.74 0 0.26 0.041

MLI26 0.787 0 0.213 0.742 0 0.258 0.045

A 276 0.694 0 0.306 0.522 0 0.478 0.172

OSR 0.935 0 0.065 0.909 0 0.091 0.026

GEO

Sample # Pretest p

0.82

Pretest z Pretest a Posttest p Posttest t Posttest a Delta a

RDM 03 0.18 0.818 0.182 0.002

RDM 22 0.813 0.187 0.523 0.477 0.29

MLI03 0.633 0 0.367 0.633 0.367 0

MLI21 0.822 0.024 0.154 0.547 0.019 0.434 0.28

MLI22 0.821 0.029 0.15 0.543 0.012 0.445 0.295

MLI23 0.782 0.003 0.215 0.469 0.001 0.53 0.315

MLI24 0.774 0.003 0.223 0.458 0.001 0.541 0.318

MLI25 0.781 0 0.219 0.494 0 0.506 0.287

MLI26 0.787 0 0.213 0.491 0 0.509 0.296

A 276 0.694 0 0.306 0.378 0 0.622 0.316

OSR 0.935 0 0.065 0.904 0 0.096 0.031

100

80 -

60

20

500

Reflectance Curves for Sample MLI23

Pretest Posttest UV+LEO Electrons Posttest UV+GEO Electrons

1000 —I—I—I—I—

1500

Wavelength, nm

2000 T 2500

Figure 5. Reflectance curves for coated Tedlar sample.

4. Conclusion

The OCLI-coated Tedlar seems to be very stable for use at LEO orbits compared to other white thermal control materials. The End-of-Life for Ultraviolet exposure only was 0.22 and with LEO electron exposure, 0.24. The Low-Alpha coating reflects the Vacuum Ultraviolet radiation and prevents darkening of the underlying Cloud White Tedlar that would occur with solar radiation. The change in solar absorptance of 0.47 for the GEO exposure of the OCLI-coated Tedlar (0.47) was larger than expected. . A plot of the change in solar absorptance as a function of exposure is shown in Figure 6. For GEO orbits, the amount of degradation should be assessed in order to determine whether this effect results in unacceptable temperature at end-of-life conditions. Future work will involve the modeling of the plasma environment present at GEO and the laboratory simulation of this dose together with the trapped electron environment. Low-energy proton effects are also being studied.

0.50 -

0.45

0.40

a u c

0.35

o 0.30

0.25

0.20

J ■ ■ i i i i i i i I ■ < i i_ —I i i i i—i—* ■ ■ i I i i_

Tedlar Exposure Test Data UV + Electrons on Radome 22

UV+GEO Electrons

© ; UV+LEO ELectrons

T—i—|—i—I—I—I—]—I—I—I—I 1—I—I—I—i—j—I—I—I—I 1—I—I—I—I—|—I 1—I—I—|—I—I—r

1000 2000 3000

Time, Hours (EUVSH)

Figure 6. Solar absorptance degradation curve for coated Tedlar sample.

4000

I

The following are the Charts for the Poster Presentation of

Space Environmental Stability of Tedlar with Multi-Layer Coatings: Space Simulation Testing Results

Dr. Wayne Stuckey Dr. Michael Meshishnek

Space Materials Laboratory The Aerospace Corporation

El Segundb, CA

8th International Symposium on "Materials in a Space Environment"

5th International Conference on "Protection of Materials and Structures from the LEO Space Environment"

Arcachon, France June 8, 2000

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24

TECHNOLOGY OPERATIONS

The Aerospace Corporation functions as an "architect-engineer" for national security programs, specializing in advanced military space systems. The Corporation's Technology Operations supports the effective and timely development and operation of national security systems through scientific research and the application of advanced technology. Vital to the success of the Corporation is the technical staffs wide-ranging expertise and its ability to stay abreast of new technological developments and program support issues associated with rapidly evolving space systems. Contributing capabilities are provided by these individual organizations:

Electronics Technology Center: Microelectronics, VLSI reliability, failure analysis, solid-state device physics, compound semiconductors, radiation effects, infrared and CCD detector devices, data storage and display technologies; lasers and electro-optics, solid state laser design, micro-optics, optical communications, and fiber optic sensors; atomic frequency standards, applied laser spectroscopy, laser chemistry, atmospheric propagation and beam control, LIDAR/LADAR remote sensing; solar cell and array testing and evaluation, battery electrochemistry, battery testing and evaluation.

Mechanics and Materials Technology Center: Evaluation and characterizations of new materials and processing techniques: metals, alloys, ceramics, polymers, thin films, and composites; development of advanced deposition processes; nondestructive evaluation, component failure analysis and reliability; structural mechanics, fracture mechanics, and stress corrosion; analysis and evaluation of materials at cryogenic and elevated temperatures; launch vehicle fluid mechanics, heat transfer and flight dynamics; aerothermodynamics; chemical and electric propulsion; environmental chemistry; combustion processes; space environment effects on materials, hardening and vulnerability assessment; contamination, thermal and structural control; lubrication and surface phenomena.

Space and Environment Technology Center: Magnetospheric, auroral and cosmic ray physics, wave-particle interactions, magnetospheric plasma waves; atmospheric and ionospheric physics, density and composition of the upper atmosphere, remote sensing using atmospheric radiation; solar physics, infrared astronomy, infrared signature analysis; infrared surveillance, imaging, remote sensing, and hyperspectral imaging; effects of solar activity, magnetic storms and nuclear explosions on the Earth's atmosphere, ionosphere and magnetosphere; effects of electromagnetic and particulate radiations on space systems; space instrumentation, design fabrication and test; environmental chemistry, trace detection; atmospheric chemical reactions, atmospheric optics, light scattering, state-specific chemical reactions and radiative signatures of missile plumes.

Center for Microtechnology: Microelectromechanical systems (MEMS) for space applications; assessment of microtechnology space applications; laser micromachining; laser-surface physical and chemical interactions; micropropulsion; micro- and nanosatellite mission analysis; intelligent microinstruments for monitoring space and launch system environments.

Office of Spectral Applications: Multispectral and hyperspectral sensor development; data analysis and algorithm development; applications of multispectral and hyperspectral imagery to defense, civil space, commercial, and environmental missions.