CEN/CLC/TR 17603-31-06:2021

Space Engineering - Thermal design handbook - Part 6: Thermal Control Surfaces

This Part 6 of the spacecraft thermal control and design data handbooks, provides information on coatings on spacecrafts for the purposes of thermal and thermo-optical regulation.
Properties of pigmented and contact coatings, are described and are classified according to their thermal radiation characteristics.
Also included in this Part are the properties and characteristics of foils and tapes with particular emphasis on their adhesive characteristics; these are not classified according to their thermal radiation properties.
The Thermal design handbook is published in 16 Parts
TR 17603-31-01 Part 1
Thermal design handbook – Part 1: View factors
TR 17603-31-01 Part 2
Thermal design handbook – Part 2: Holes, Grooves and Cavities
TR 17603-31-01 Part 3
Thermal design handbook – Part 3: Spacecraft Surface Temperature
TR 17603-31-01 Part 4
Thermal design handbook – Part 4: Conductive Heat Transfer
TR 17603-31-01 Part 5
Thermal design handbook – Part 5: Structural Materials: Metallic and Composite
TR 17603-31-01 Part 6
Thermal design handbook – Part 6: Thermal Control Surfaces
TR 17603-31-01 Part 7
Thermal design handbook – Part 7: Insulations
TR 17603-31-01 Part 8
Thermal design handbook – Part 8: Heat Pipes
TR 17603-31-01 Part 9
Thermal design handbook – Part 9: Radiators
TR 17603-31-01 Part 10
Thermal design handbook – Part 10: Phase – Change Capacitors
TR 17603-31-01 Part 11
Thermal design handbook – Part 11: Electrical Heating
TR 17603-31-01 Part 12
Thermal design handbook – Part 12: Louvers
TR 17603-31-01 Part 13
Thermal design handbook – Part 13: Fluid Loops
TR 17603-31-01 Part 14
Thermal design handbook – Part 14: Cryogenic Cooling
TR 17603-31-01 Part 15
Thermal design handbook – Part 15: Existing Satellites
TR 17603-31-01 Part 16
Thermal design handbook – Part 16: Thermal Protection System

Raumfahrttechnik - Handbuch für thermisches Design - Teil 6: Oberflächen zur Thermalkontrolle

Ingénierie spatiale - Manuel de conception thermique - Partie 6: Revêtements de Contrôle Thermique

Vesoljska tehnika - Priročnik o toplotni zasnovi - 6. del: Toplotne nadzorne površine

General Information

• Status: Published
• Publication Date: 03-Aug-2021
• ICS: 49.140 - Space systems and operations
• Technical Committee: CEN/CLC/TC 5 - Space
• Drafting Committee: CEN/CLC/TC 5/WG 6 - Upstream standards
• Current Stage: 6060 - Definitive text made available (DAV) - Publishing
• Start Date: 04-Aug-2021
• Due Date: 14-Jul-2022
• Completion Date: 04-Aug-2021
• Mandate: M/496 - Mandate addressed to CEN, CENELEC and ETSI to develop standardisation regarding space industry (Phase 3 of the process)
• Ref Project: SIST-TP CEN/CLC/TR 17603-31-06:2021 - Space Engineering - Thermal design handbook - Part 6: Thermal Control Surfaces

Standards Content (Sample)

SLOVENSKI STANDARD
01-oktober-2021
Vesoljska tehnika - Priročnik o toplotni zasnovi - 6. del: Toplotne nadzorne
površine
Space Engineering - Thermal design handbook - Part 6: Thermal Control Surfaces
Raumfahrttechnik - Handbuch für thermisches Design - Teil 6: Oberflächen zur
Thermalkontrolle
Ingénierie spatiale - Manuel de conception thermique - Partie 6: Revêtements de
Contrôle Thermique
Ta slovenski standard je istoveten z: CEN/CLC/TR 17603-31-06:2021
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.

TECHNICAL REPORT
CEN/CLC/TR 17603-31-
RAPPORT TECHNIQUE
TECHNISCHER BERICHT
August 2021
ICS 49.140
English version
Space Engineering - Thermal design handbook - Part 6:
Thermal Control Surfaces
Ingénierie spatiale - Manuel de conception thermique - Raumfahrttechnik - Handbuch für thermisches Design -
Partie 6: Revêtements de Contrôle Thermique Teil 6: Oberflächen zur Thermalkontrolle

This Technical Report was approved by CEN on 21 June 2021. It has been drawn up by the Technical Committee CEN/CLC/JTC 5.

CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium,
Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy,
Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Republic of North Macedonia, Romania, Serbia,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.

CEN-CENELEC Management Centre:
Rue de la Science 23, B-1040 Brussels
© 2021 CEN/CENELEC All rights of exploitation in any form and by any means Ref. No. CEN/CLC/TR 17603-31-06:2021 E
reserved worldwide for CEN national Members and for
CENELEC Members.
Table of contents
European Foreword . 14
1 Scope . 15
2 References . 16
3 Terms, definitions and symbols . 17
3.1 Terms and definitions . 17
3.2 Abbreviated terms. 17
3.3 Symbols . 18
4 General introduction . 21
5 Coatings . 23
5.1 General . 23
5.2 Solar reflectors . 25
5.2.1 Titanium Dioxide-Polymethyl Vinyl Siloxane . 25
5.2.2 Zinc Oxide-Potassium Silicate . 32
5.2.3 Zinc Orthotitanate-Potassium Silicate . 52
5.2.4 Zinc Oxide-Methylsilicone . 136
5.2.5 Zinc Oxide-Potassium Silicate . 163
5.2.6 Silver vacuum deposited on fused Silica . 196
5.2.7 Silver vacuum deposited on fused Silica with a conductive coating . 251
5.3 Total reflectors . 274
5.3.1 Leafing Aluminium-Silicone . 274
5.4 Total absorbers . 279
5.4.1 Carbon black-Acrylic resin . 279
6 Adhesive tapes . 283
6.1 General . 283
6.1.2 Adhesive properties . 283
6.1.3 Curing of adhesive tapes. 285
6.1.4 General purpose adhesive tapes. 286
6.2 Application and handling . 298
6.2.1 Application . 298
6.2.2 Cleaning . 298
6.2.3 Handling . 299
6.2.4 Repairing . 300
6.3 Degradation . 300
6.3.1 Introduction . 300
6.3.2 Terrestrial degradation . 300
6.3.3 Space degradation . 300
6.3.4 Blistering . 304
6.4 Relevant properties of thermal control tapes . 307
6.5 Past spatial use . 331
Bibliography . 333

Figures
Figure 4-1: Basic types of thermal control coatings. T [K] is the equilibrium
R
temperature of a coated isothermal sphere at 1 AU. From Touloukian,
DeWitt & Hernicz (1972) [126]. . 21
Figure 4-2: Range of solar absorptance, α , and hemispherical total emittance, ε,
s
covered by available thermal control coatings. From Touloukian, DeWitt &
Hernicz (1972) [126]. . 22
Figure 5-1: UV radiation effects on solar absorptance, α , of Thermatrol 2A-100 vs.
s
exposure time, t. From Breuch (1967) [22]. . 28
Figure 5-2: Change in solar absorptance, ∆α , of Thermatrol 2A-100, under various
s
radiation conditions, vs. exposure time, t. From McCargo et al. (1971) [82]. . 28
Figure 5-3: Normal-hemispherical spectral reflectance, ρ ', of Thermatrol 2A-100,
λ
measured by two different methods, vs. wavelength, λ. From Cunnington,
Grammer & Smith (1969) [33]. . 29
Figure 5-4: Effect of Ultra-Violet Radiation on spectral reflectance, ρ ', of Thermatrol
λ
2A-100 vs. wavelength, λ. Most of the data, concerning bidirectional
reflectance, are from Rittenhouse & Singletary (1969) [105], while dashed
line and dotted line, normal-hemispherical reflectance, are from
Cunnington, Grammer & Smith (1969) [33]. . 30
Figure 5-5: Variation of solar absorptance, α , with thickness, t . From Stevens (1971)
s c
[120]. . 36
Figure 5-6: Estimated changes in the solar absorptance, α , of Z-93 during the total
s
mission profile for a near-Earth orbit. From McCargo, Spradley, Greenberg
& McDonald (1971) [82]. . 45
Figure 5-7: Normal-hemispherical spectral reflectance, ρ ', of Z-93 vs. wavelength, λ.
λ
All data are from Touloukian, DeWitt & Hernicz (1972) [126] except solid
and dashed lines which are from Cunnington, Grammer & Smith (1969)
[33]. . 47
Figure 5-8: Effect of Ultra-Violet Radiation on normal-hemispherical spectral
reflectance, ρ ', of Z-93 vs. wavelength, λ. Data points are from Touloukian,
λ
DeWitt & Hernicz (1972) [126], while smooth curves are from Cunnington,
Grammer & Smith (1969) [33]. . 49
Figure 5-9: Effect of Proton Radiation on normal-hemispherical spectral reflectance, ρ ',
λ
of Z-93 vs. wavelength, λ. From Touloukian, DeWitt & Hernicz (1972) [126]. . 50
Figure 5-10: Hemispherical total emittance, ε, of Zinc Orthotitanate-Potassium Silicate
Coatings vs. temperature, T. : SSR pigment,> phosphated. From Keyte
(1975) [70]. : MOX pigment,> YB-71. From Harada & Wilkes (1979) [58].
: YB-71.> AESC. From Ahern & Karperos (1983) [4]. . 60
Figure 5-11: Solar absorptance, α , of YB-71 vs. thickness, t . : From Harada &
s c
Wilkes (1979) [58]. : From measurements on 16 panels by AESC.
Scatter is due to t variation. From Ahern & Karperos (1983) [4]. . 60
c
Figure 5-12: Solar absorptance, α , of Zinc Orthotitanate-Potassium Silicate coating vs.
s
incidence angle, β. SSR pigment, phosphated. From Keyte (1975) [70]. . 63
Figure 5-13: Solar absorptance, α , of several YB-71 coatings vs. exposure time, t, as
s
deduced from data of various spacecraft in geosynchronous orbits.
Numbers corresponds to sample designations. . 74
Figure 5-14: Normal-hemispherical spectral reflectance, ρ'λ, of Zinc Orthotinanate-
Potassium Silicate coatings vs. wavelength, λ. . 76
Figure 5-15: Effect of Ultra-Violet Radiation on normal-hemispherical spectral
reflectance, ρ' , of Zinc Orthotitanate- Potassium Silicate coatings vs.
λ
wavelength, λ. . 78
Figure 5-16: Effect of Protons Radiation on normal-hemispherical spectral reflectance,
ρ' , of Zinc Orthotitanate-Potassium Silicate coatings vs. wavelength, λ.
λ
From Gilligan & Zerlaut (1971) [46]. . 79
Figure 5-17: Hemispherical total emittance, ε, of S-13 G coating vs. temperature, T. 2 x
-4
10 m thick coating on molybdenum substrate. From Spisz & Jack (1971)
[119]. . 85
Figure 5-18: Hemispherical total emittance, ε, of S-13 and S-13 G coatings vs.
exposure time, t, at 1-Sun level and 395 K. From Cunnington, Grammer &
Smith (1969) [33]. Equal symbols correspond to the same sample. :>
Sample 27; :> Sample 43; :> Sample 28; :> Sample 44. . 87
Figure 5-19: Variation of solar absorptance, α , of S-13 coating with coating thickness, t
s
. :> Nominal composition. Sprayed on primed surface. Air dryed. T =
c
298 K. (Designation in the ref.: 119 to 127). :> ZnO in silicone binder. T =
298 K. (Designation in the ref.: 29, 30). From Touloukian, DeWitt & Hernicz
(1972) [126]. . 89
Figure 5-20: Solar absorptance, α , of S-13 G coating vs. incidence angle, β. From
s
Keyte (1975) [70]. . 90
Figure 5-21: Change in solar absorptance, ∆α , of S-13 and S-13 G coatings due to
s
Protons and Alpha Particles Radiation vs. integrated flux, n. . 94
Figure 5-22: Change in solar absorptance, ∆α , of S-13 G coating due to Electrons
s
Radiation vs. integrated flux, n. Data taken in situ. Compiled by Bourrieau,
Paillous & Romer (1976) [21]. . 96
Figure 5-23: Changes in solar absorptance of S-13 and S-13 G coatings. OSO III
experiment. From Millard (1969) [84]. . 98
Figure 5-24: Change in solar absorptance, ∆αs, of S-13 coatings vs. flight time in ESH
as measured in orbital flight. Prepared by the compiler after Touloukian,
DeWitt & Hernicz (1972) [126]. . 99
Figure 5-25: Change in solar absorptance, ∆α , of S-13 G coating vs. flight time in ESH
s
as measured in orbital flight. Prepared by the compiler after Touloukian,
DeWitt & Hernicz (1972) [126]. . 100
Figure 5-26: Position on the sample holder of the samples 1 and 2, for irradiation and
measurement. From Paillous (1976) [96]. . 104
Figure 5-27: Solar absorptance, α , of S-13 G/LO coating vs. flight time, . 105
s
Figure 5-28: Variation of absorptance to emittance ratio, α/ε, of S-13 coating vs. flight
time. Prepared by the compil
...