NASA/TM—2014–218195

Optical Properties of Nanosatellite Hardware

M.M. Finckenor and R.F. Coker

Marshall Space Flight Center, Huntsville, Alabama

June 2014
	




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i

NASA/TM—2014–218195

Optical Properties of Nanosatellite Hardware

M.M. Finckenor and R.F. Coker

Marshall Space Flight Center, Huntsville, Alabama

June 2014

National Aeronautics and

Space Administration

Marshall Space Flight Center • Huntsville, Alabama 35812
ii

Available from:

NASA STI Information Desk

Mail Stop 148

NASA Langley Research Center

Hampton, VA 23681–2199, USA

757–864–9658

This report is also available in electronic form at

<http://www.sti.nasa.gov>

Acknowledgments

 The authors would like to acknowledge the contributions of Bart Graham and Emily Willis to this effort. 

Thanks to Curtis Bahr for laboratory support.

TRADEMARKS

Trade names and trademarks are used in this report for identification only. This usage does not constitute an official 

endorsement, either expressed or implied, by the National Aeronautics and Space Administration.
iii

TABLE OF CONTENTS

1. INTRODUCTION ............................................................................................................. 1

2. ANTENNAS ...................................................................................................................... 3

3. PRINTED CIRCUIT BOARDS ......................................................................................... 4

 3.1 Uncoated Circuit Boards .............................................................................................. 4

 3.2 Coated Circuit Boards .................................................................................................. 6

4. SOLAR CELLS .................................................................................................................. 11

5. BATTERIES ....................................................................................................................... 12

6. MISCELLANEOUS MATERIALS ................................................................................... 13

7. DISCUSSION AND CONCLUSIONS .............................................................................. 14

REFERENCES ....................................................................................................................... 15
iv
v

LIST OF FIGURES

 1. CubeSats deployed from the J-SSOD and photographed against an ISS 

 solar array background ............................................................................................. 1

 2. Uncoated EDSN white circuit board G115 ............................................................... 4

 3. Uncoated EDSN G116 green circuit board, numbered side ....................................... 5

 4. Reverse side of G116-B3_v1 board ............................................................................ 5

 5. Coated EDSN white circuit board, numbered side .................................................... 6

 6. Reverse side of G114 circuit board ............................................................................ 6

 7. Coated EDSN green circuit board G111, numbered side ........................................... 7

 8. Reverse side of G111 circuit board ............................................................................ 7

 9. Coated EDSN green circuit board G112, numbered side ........................................... 8

10. Reverse side of G112 circuit board ............................................................................ 8

11. Coated EDSN green circuit board G113, numbered side ........................................... 9

12. Reverse side of G113 circuit board ............................................................................ 9

13. EDSN battery with green plastic wrapping ............................................................... 12
vi

LIST OF TABLES 

1. Optical property measurements of antenna parts ...................................................... 3

2. Optical properties of uncoated EDSN G115 white circuit board ............................... 4

3. Optical properties of uncoated EDSN G116 green circuit board .............................. 5

4. Optical properties of coated EDSN white circuit board ............................................ 10

5. Optical properties of coated EDSN green circuit board ............................................ 10

6. Optical properties of solar cells ................................................................................. 11

7. Optical properties of miscellaneous nanosatellite materials. ....................................... 13
vii

LIST OF ACRONYMS

ASTM American Society for Testing and Materials

COTS commerical off-the-shelf (components)

EDSN Edison Demonstration of Smallsat Networks

GPS Global Positioning System

ISS International Space Station

JEM Japanese Experiment Module

J-SSOD JEM Small Satellite Orbital Deployer

LDEF Long Duration Exposure Facility

LPSR Laboratory Portable Spectroreflectometer

MISSE Materials on International Space Station Experiment

SMDC-ONE Space Missile Defense Command-Operational Nanosatellite Effect
viii
1

TECHNICAL MEMORANDUM

OPTICAL PROPERTIES OF NANOSATELLITE HARDWARE

1. INTRODUCTION

 Over the last decade, a number of very small satellites have been launched into space. These 

have been called nanosatellites (generally of a weight between 1 and 10 kg) or picosatellites (weight 

<1 kg). This also includes CubeSats, which are based on 10-cm cube units. With the addition of 

the Japanese Experiment Module (JEM) Small Satellite Orbital Deployer (J-SSOD) to the International Space Station (ISS), CubeSats are easily cycled through the JEM airlock and deployed into 

space (fig. 1). The number of CubeSats launched since 2003 was approaching 100 at the time of 

publication, and the authors expect this trend in research to continue, particularly for high school 

and college flight experiments.

Figure 1. CubeSats deployed from the J-SSOD and photographed against 

an ISS solar array background.
2

 Because these spacecraft are so small, there is usually no allowance for shielding or active 

heating or cooling of the avionics and other hardware. Parts that are usually ignored in the thermal analysis of larger spacecraft may contribute significantly to the heat load of a tiny satellite. In 

addition, many small satellites have commercial-off-the-shelf (COTS) components. To reduce costs, 

many providers of COTS components do not include the optical and physical parameters necessary 

for accurate thermal analysis.

 Marshall Space Flight Center participated in the development and analysis of the Space 

Missile Defense Command-Operational Nanosatellite Effect (SMDC-ONE) and the Edison Demonstration of Smallsat Networks (EDSN) nanosatellites. These optical property measurements are 

documented here in hopes that they may benefit future nanosatellite and picosatellite programs and 

aid thermal analysis to ensure project goals are met, with the understanding that material properties may vary by vendor, batch, manufacturing process, and preflight handling. Where possible, 

complementary data are provided from ground simulations of the space environment and flight 

experiments, such as the Materials on International Space Station Experiment (MISSE) series. 

NASA gives no recommendation, endorsement, or preference, either expressed or implied, concerning materials and vendors used. 

 Solar absorptance (αs) was calculated from spectral reflectance measurements made from 

250 to 2,800 nm with an AZ Technology Laboratory Portable Spectroreflectometer (LPSR) 

model 300. ASTM E-903 was the test method used under normal laboratory conditions,1 and 

ASTM E-490 was the solar spectral irradiance data used to calculate αs.

2 Most of the samples were 

flat, but stray light was minimized as much as possible with either a blackbody or black cloth as 

sample background. The LPSR has repeatability of approximately ±1%, where αs is given as range, 

that is, from actual measurements taken across the sample. 

 Infrared emittance (εIR) measurements were made with an AZ Technology TEMP 2000A 

infrared reflectometer. This instrument measures the total hemispheric reflectance averaged over 

3–35 μm wavelengths. ASTM E-408 was the test method used under normal laboratory conditions.3 Stray light was minimized as much as possible. The TEMP 2000A has repeatability of 

approximately ±0.5%, where εIR is given as a range, that is, from actual measurements taken across 

the sample. 
3

2. ANTENNAS

 The antenna for the SMDC-ONE satellite had exposed 301 stainless steel and Kapton®. 

The antenna for the EDSN satellite was a Digi-Key 1575.42 MHz ceramic patch, part number 

931-1141-ND for Global Positioning System communication. Two EDSN antennas indicated quite 

different results, which was unexpected given the lack of visual differences. Data for these can be 

found in table 1. Also included are preflight optical properties of an antenna consisting of directwrite copper on Tedlar® film that was flown on the MISSE-8 experiment.

Table 1. Optical property measurements of antenna parts.

Sample

Solar 

Absorptance

Infrared 

Emittance

SMDC-ONE antenna 301 stainless steel 0.41 0.14

Kapton 0.58 0.84

EDSN GPS antenna No. 1 0.20 0.13–0.15

No. 2 0.24 0.28–0.31

Direct-write on Tedlar Copper 0.61 0.32
4

3. PRINTED CIRCUIT BOARDS

 The printed circuit boards for this study are as-built rather than blank. Some were conformal coated, and some were left uncoated. Measurements were taken of areas with the fewest connections and areas with many connections to allow the thermal designer to calculate an overall 

average for their particular surface. 

3.1 Uncoated Circuit Boards

 Figure 2 shows the uncoated G115-SP1.5_v1 board for EDSN, grooved side up. Solar 

absorptance and infrared emittance are given for each area of the board in table 2. The reverse side 

was mostly sections of solder for attaching solar cells, so only typical properties are presented here. 

A

B

E

D

C

Figure 2. Uncoated EDSN white circuit board G115.

Table 2. Optical properties of uncoated EDSN 

G115 white circuit board.

Area

Solar

Absorptance

Infrared

Emittance

Obverse A 0.45 0.88

Obverse B 0.49 0.90

Obverse C 0.47 0.88

Obverse D 0.46 0.89

Obverse E 0.45 0.89

Reverse 0.31 0.05
5

 Figures 3 and 4 are of an uncoated green circuit board for EDSN. Solar absorptance and 

infrared emittance are given for each area of the board in table 3. Three measurements were made 

around the center of the obverse side that were identical in solar absorptance and infrared emittance.

Figure 3. Uncoated EDSN G116 green circuit board, numbered side. 

A

B

Figure 4. Reverse side of G116-B3_v1 board.

Table 3. Optical properties of uncoated EDSN 

G116 green circuit board.

Area

Solar

Absorptance

Infrared

Emittance

G116 obverse 0.65 0.86

G116 reverse –A 0.77 0.89

G116 reverse –B 0.81 0.90
6

3.2 Coated Circuit Boards

 Four coated EDSN circuit boards were measured. The only white board was G114 (figs. 5 

and 6). The Arathene 5750-A/B (LV) urethane conformal coating varied by the amount of thinner added, but this did not appear to have any impact on the optical properties. For completeness, 

the coating for the G111 board for 18 g of part A, 100 g of part B, and 20 g thinner (figs. 7 and 8); 

G112 was 18 g of part A, 100 g of part B, and 30.5 g thinner (figs. 9 and 10); G113 and G114 were 

18g of part A, 100 g of part B, and 45 g thinner (figs. 11 and 12). Optical properties for the white 

and green coated circuit boards are in tables 4 and 5, respectively.

B

A

Figure 5. Coated EDSN white circuit board, numbered side.

A

B

Figure 6. Reverse side of G114 circuit board.
7

A

B

Figure 7. Coated EDSN green circuit board G111, numbered side.

A

B

Figure 8. Reverse side of G111 circuit board. 
8

A

B

Figure 9. Coated EDSN green circuit board G112, numbered side. 

A

B C

Figure 10. Reverse side of G112 circuit board.
9

B

A

Figure 11. Coated EDSN green circuit board G113, numbered side.

A B

C

Figure 12. Reverse side of G113 circuit board.
10

Table 4. Optical properties of coated EDSN 

white circuit board. 

Area

Solar

Absorptance

Infrared

Emittance

G114 obverse A 0.48 0.89

G114 obverse B 0.44 0.91

G114 reverse A 0.36 0.89

G114 reverse B 0.50 0.77

Table 5. Optical properties of coated EDSN 

green circuit board.

Area

Solar

Absorptance

Infrared

Emittance

G111 obverse A 0.71 0.89

G111 obverse B 0.74 0.90

G111 reverse A 0.69 0.86

G111 reverse B 0.61 0.77

G112 obverse A 0.59 0.89

G112 obverse B 0.70 0.90

G112 reverse A 0.60 0.84

G112 reverse B 0.67 0.82

G112 reverse C 0.51 0.80

G113 obverse A 0.61 0.88

G113 obverse B 0.68 0.88

G113 reverse A 0.68 0.81

G113 reverse B 0.70 0.64

G113 reverse C 0.72 0.85
11

4. SOLAR CELLS

 Solar cells by their very nature absorb sunlight. As the efficiency of solar cells has improved 

over the years, the solar absorptance has increased. Table 6 contains the data for the SMDC-ONE 

nanosatellite triple-junction, high-efficiency solar cells. Optical properties are included for older, 

less efficient silicon solar cells after exposure on the Long Duration Exposure Facility for 5.8 years. 

Other single-junction and multi-junction solar cells should fall between these two extremes; thin 

film photovoltaics under development at the time of publication may have very different properties.

Table 6. Optical properties of solar cells.

Sample

Solar

Absorptance

Infrared

Emittance

SMDC-ONE triple 

junction 

0.93 0.85

LDEF silicon 0.74–0.75 0.83–0.84
12

5. BATTERIES

 An EDSN lithium-ion battery with the plastic wrapping removed had infrared emittance 

of 0.11. This is typical of bare metal. A battery with intact plastic wrapping (fig. 13) had infrared 

emittance of 0.85.

Figure 13. EDSN battery with green plastic wrapping.
13

6. MISCELLANEOUS MATERIALS

 Other materials measured in support of SMDC-ONE and EDSN can be found in table 7. 

It should be noted that chemical conversion coatings such as Alodine have highly variable optical 

properties dependent on the substrate metal, surface finish, and application method.

Table 7. Optical properties of miscellaneous 

nanosatellite materials.

Area

Solar

Absorptance

Infrared

Emittance

Copper tape 0.48 0.80

Tin plate 0.49–0.51 0.15–0.20

Alodine on 

6061-T6 aluminum

0.33 0.07
14

7. DISCUSSION AND CONCLUSIONS

 The information presented here was gathered to support nanosatellite and picosatellite 

missions that may not be able to perform their own thermal property measurements. Some margin 

should be included in a design for unexpected degradation or contamination events. The specific 

conditions for the spacecraft must be considered when choosing materials.

 The authors would also like to note the concurrent development of “Spacecraft Surface 

Charging Analysis of a CubeSat,” a document on NASA Charging Analyzer Program (NASCAP) 

analysis for EDSN by Emily Willis that may be useful for other nanosatellite developers.
15

REFERENCES 

1. ASTM E-903, Standard Test Method for Solar Absorptance, Reflectance, and Transmittance 

of Materials Using Integrating Spheres, Book of Standards, Vol. 12.02, December 1, 2012.

2. ASTM E-490-00a, Standard Solar Constant and Zero Air Mass Solar Spectral Irradiance 

Tables, Book of Standards, Vol. 15.03, 2014.

3. ASTM E-408, Standard Test Methods for Total Normal Emittance of Surfaces Using Inspection-Meter Techniques, Book of Standards, Vol. 15.03, June 1, 2013.
16

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Optical Properties of Nanosatellite Hardware

M.M. Finckenor and R.F. Coker

George C. Marshall Space Flight Center

Huntsville, AL 35812

National Aeronautics and Space Administration

Washington, DC 20546–0001

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Prepared by the Materials & Processes Laboratory, Engineering Directorate

M–1384

Technical Memorandum

NASA/TM—2014–218195

optical properties, thermal, nanosatellite, picosatellite, CubeSat, avionics, antenna, solar cell

01–06–2014

UU 28

NASA

UUU

This Technical Memorandum documents the optical property measurements to support thermal analyses of the 

Space Missile Defense Command-Operational Nanosatellite Effect (SMDC-ONE) and Edison Demonstration 

of Smallsat Networks nanosatellites. These measurements including hardware not usually included in thermal 

analyses, but due to the small size of the satellites, circuit boards, antennas, etc. must be included. These measurements may be helpful to other nanosatellite, picosatellite, and CubeSat programs. 

STI Help Desk at email: help@sti.nasa.gov

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