NASA Technical Memorandum 107212

Atomic Oxygen Durability Testing of an

International Space Station Solar Array

Validation Coupon

Mark J. Forkapa and Curtis R. Stidham

NYMA, Inc.

Brook Park, Ohio

Bruce A. Banks and Sharon K. Rutledge

Lewis Research Center

Cleveland, Ohio

David H. Ma

Lockheed Martin Missiles & Space Company

Sunnyvale, California

Edward A. Sechkar

Cleveland State University

Cleveland, Ohio

Prepared for the

Third International Conference on Protection of Materials and Structures

from the Low Earth Orbit Space Environment

sponsored by the University of Toronto

Toronto, Canada, April 25–26, 1996

National Aeronautics and

Space Administration

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Figure 1.—Solar array validation coupon before exposure to atomic 

 oxygen and tensile loading: (a) solar side and (b) anti-solar side. 

(a)

(b)

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Glass cloth & CV2-2502 silicone adhesive (.002 in.)

Coverslide (.005 in.)

Silicone adhesive (<.001 in.)

Solar cell (.008 in.)

CV2-2502

Silicone

adhesive

CV1147 low block

silicone (.0015 in.)

Kapton (.001 in.)

Polyester adhesive (.0005 in.)

Solar

cell

assembly

FPC

Laminate

Kapton (.001 in.)

SiOx coated Kapton (.001 in.)

Figure 3.—Mounting rotisserie for the solar array validation coupon

 testing.

Copper (.0014 in.)

Figure 2.—Cross section of space station solar panel.

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Figure 4.—Apparatus for tensioning to the array.

Figure 5.—Solar array validation coupon

 mounted in the rotisserie and ready for

 testing in the NASA Lewis Research

 Center's atomic oxygen facility.

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Figure 6.—Solar array validation coupon after exposure to atomic

 oxygen and tensile loading: (a) solar side and (b) anti-solar side.

(a)

(b)

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Figure 7.—Photo of the solar array showing a close up of solar cell

 and diode prior to exposure to atomic oxygen and tensile loading.

Figure 8.—Photo of the solar array showing a close up of solar cell

 and diode after exposure to atomic oxygen and tensile loading.

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Figure 9.—Central hinge region of the solar array validation coupon

 prior to exposure to atomic oxygen and tensile loading.

Figure 10.—Central hinge region of the solar array validation coupon

 after to exposure to atomic oxygen and tensile loading.

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Figure 11.—Evidence of atomic oxygen attack on the anti-solar side of

 the array after full fluence exposure.

NASA/TM— 2001-107212
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Lewis Research Center

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April 1996

NASA TM–107212

E–10229

23

A03

Atomic Oxygen Durability Testing of an International Space Station Solar Array

Validation Coupon

Mark J. Forkapa, Curtis R. Stidham, Bruce A. Banks, Sharon K. Rutledge,

David H. Ma, and Edward A. Sechkar

Prepared for the Third International Conference on Protection of Materials and Structures from the Low Earth Orbit Space Environment sponsored by

the University of Toronto, Toronto, Canada, April 25–26, 1996. Mark J. Forkapa and Curtis R. Stidham, NYMA, Inc., 2001 Aerospace Parkway, Brook

Park, Ohio 44142 (work performed under NASA Contract NAS3–27186); Bruce A. Banks and Sharon K. Rutledge, NASA Lewis Research Center;

David H. Ma, Lockheed Martin Missiles & Space Company, Sunnyvale, California; Edward A. Sechkar, Cleveland State University, Cleveland, Ohio

44115. Responsible person, Mark J. Forkapa, organization code 5480, (216) 433–2299.

Unclassified -Unlimited

Subject Category 12

This publication is available from the NASA Center for AeroSpace Information, (301) 621–0390.

Atomic oxygen; Low Earth Orbit; International Space Station; Solar array; Protected

polymers; Kapton; Photovoltaic

WU–233–1A–1E

An International Space Station solar array validation coupon was exposed in a directed atomic oxygen beam for space environment

durability testing at the NASA Lewis Research Center. Exposure to atomic oxygen and intermittent tensioning of the solar array were

conducted to verify the solar array’s durability to low Earth orbital atomic oxygen and to the docking threat of plume loading both of

which are anticipated over its expected mission life of fifteen years. The validation coupon was mounted on a specially designed

rotisserie. The rotisserie mounting enabled the solar and anti-solar facing side of the array to be exposed to directed atomic oxygen in a

sweeping arrival process replicating space exposure. The rotisserie mounting also enabled tensioning, in order to examine the durability

of the array and its hinge to simulated plume loads. Flash testing to verify electrical performance of the solar array was performed with a

solar simulator before and after the exposure to atomic oxygen and tensile loading. Results of the flash testing indicated little or no

degradation in the solar array’s performance. Photographs were also taken of the array before and after the durability testing and are

included along with comparisons and discussions in this report. The amount of atomic oxygen damage appeared minor with the

exception of a very few isolated defects. There were also no indications that the simulated plume loadings had weakened or damaged

the array, even though there was some erosion of Kapton due to atomic oxygen attack. Based on the results of this testing, it is apparent

that the International Space Station’s solar arrays should survive the low Earth orbital atomic oxygen environment and docking threats

which are anticipated over its expected mission life.