SIST-TP CEN/CLC/TR 17603-31-12:2021

Space Engineering - Thermal design handbook - Part 12: Louvers

Thermal louvers are thermal control surfaces whose radiation characteristics can be varied in order to
maintain the correct operating temperature of a component subject to cyclical changes in the amount
of heat that it absorbs or generates.
The design and construction of louvers for space systems are described in this Part 12 and a clause is
also dedicated to providing details on existing systems.
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 12: Luftschlitze

Ingénierie spatiale - Manuel de conception thermique - Partie 12: Persiennes

Vesoljska tehnika - Priročnik o toplotni zasnovi - 12. del: Žaluzije

General Information

• Status: Published
• Public Enquiry End Date: 26-May-2021
• Publication Date: 23-Aug-2021
• ICS: 49.140 - Space systems and operations
• Technical Committee: I13 - Imaginarni 13
• Current Stage: 6060 - National Implementation/Publication (Adopted Project)
• Start Date: 19-Aug-2021
• Due Date: 24-Oct-2021
• Completion Date: 24-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: CEN/CLC/TR 17603-31-12:2021 - Space Engineering - Thermal design handbook - Part 12: Louvers

Standards Content (Sample)

SLOVENSKI STANDARD
01-oktober-2021
Vesoljska tehnika - Priročnik o toplotni zasnovi - 12. del: Žaluzije
Space Engineering - Thermal design handbook - Part 12: Louvers
Raumfahrttechnik - Handbuch für thermisches Design - Teil 12: Luftschlitze
Ingénierie spatiale - Manuel de conception thermique - Partie 12: Persiennes
Ta slovenski standard je istoveten z: CEN/CLC/TR 17603-31-12:2021
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 12:
Louvers
Ingénierie spatiale - Manuel de conception thermique - Raumfahrttechnik - Handbuch für thermisches Design -
Partie 12 : Persiennes Teil 12: Blenden

This Technical Report was approved by CEN on 28 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 17603-31-12:2021 E
reserved worldwide for CEN national Members and for
CENELEC Members.
Table of contents
European Foreword . 7
1 Scope . 8
2 References . 9
3 Terms, definitions and symbols . 10
3.1 Terms and definitions . 10
3.2 Symbols . 10
4 General introduction . 15
5 Components of a louver . 16
5.1 Blades . 16
5.2 Actuators . 18
5.2.1 Bimetals . 18
5.2.2 Bellows . 24
5.2.3 Bourdons . 35
5.3 Sensors . 37
5.3.1 Sensor location . 37
5.3.2 Coupling options . 38
5.4 Structural elements . 38
5.4.1 Actuator housing . 38
5.4.2 Frames . 38
6 Ideal louvers . 40
6.1 Sun-light operation. 40
6.1.1 Introduction . 40
6.1.2 Heat rejection capability . 40
6.1.3 Effective absorptance . 43
6.1.4 Effective emittance . 46
6.2 Shadow operation . 52
6.2.1 Introduction . 52

6.2.2 Radiosity and temperature field of the blades. 53
6.2.3 Heat transfer through the louver . 55
7 Existing systems . 66
7.1 Summary table . 66
7.2 Ats louvers . 76
7.2.1 Introduction . 76
7.2.2 Analytical calculations . 76
7.2.3 Tests . 80
7.3 Nimbus louvers . 83
7.3.1 Introduction . 83
7.3.2 Louvers of the sensory subsystem . 83
7.3.3 Louver of the control subsystem . 84
7.3.4 Flight performance . 86
7.4 Snias louvers . 87
7.4.1 Introduction . 87
7.4.2 Analytical calculations . 88
7.4.3 Tests . 95
7.4.4 The Bourdon tube used as an actuator in the SNIAS Louver system . 98
Bibliography . 104

Figures
Figure 5-1: Relative linear thermal expansion vs. temperature in the case of Invar. T =
273 K. From THE MOND NICKEL CO [35]. . 19
Figure 5-2: Relative linear thermal expansion vs. temperature in the case of brasses. T
= 273 K. After Baldwin (1961) [3]. . 20
Figure 5-3: Relative linear thermal expansion vs. temperature in the case of austenitic
steels. T = 273 K. After Zapffe (1961) [39]. . 20
Figure 5-4: Relative linear thermal expansion vs. temperature in the case of Nimonic
alloys. T = 273 K. After WIGGIN & Co. (1967) [38]. 21
Figure 5-5: Relative linear thermal expansion vs. temperature for different alloys. T =
273 K. After Baldwin (1961) [3], Zapffe (1961) [39], WIGGIN Co. (1967)
[38]. . 21
Figure 5-6: Difference of temperature, ∆T, vs. angle of rotation of the free end, θ, for
several values of the sensitivity, X. After Martin & Yarworth (1961) [21],
KAMMERER (1971) [16]. . 22
Figure 5-7: Sensitivity vs. ratio L/t, for different values of K . After Martin & Yarworth
c
(1961) [21], KAMMERER (1971) [16]. . 23
Figure 5-8: Dimensionless ratio M/K F ∆TL vs. L/t, for several values of w/t. After
c c
Martin & Yarworth (1961) [21], KAMMERER (1971) [16]. . 24
Figure 5-9: Values of α and β vs. ratio a/b for different cross sections of the Bourdon
tube. After Trylinski (1971) [37]. . 36
Figure 5-10: Ratio F/F vs. Bourdon initial coiling angle, ψ . Calculated by the compiler. . 37
0 0
Figure 6-1: Geometry of the blade-baseplate system . 40
Figure 6-2: Heat rejection capability, q, vs. blade angle, θ, for several values of the sun
angle, φ. From FAIRCHILD HILLER (1972) [10]. . 42
Figure 6-3: Heat rejection capability, q, vs. blade angle, θ, for several values of the sun
angle, φ. From Parmer & Stipandic (1968) [27]. . 43
Figure 6-4: Effective absorptance, α , vs. blade angle, θ, for several values of the sun
eff
angle, φ. After FAIRCHILD HILLER (1972) [10]. . 45
Figure 6-5: Effective absorptance, α , vs. blade angle, θ, for several values of the sun
eff
angle, φ. After Parmer & Stipandic (1968) [27]. . 46
Figure 6-6: Effective emittance, ε , vs. blade angle, θ. After FAIRCHILD HILLER
eff
(1972) [10]. . 48
Figure 6-7: Effective emittance, ε , vs. blade angle, θ. After Parmer & Stipandic (1968)
eff
[27]. . 49
Figure 6-8: Effective emittance, ε , vs. blade angle, θ, for several values of the
eff
baseplate emittance, ε . ε has been numerically calculated by using the
BP eff
ε
BP
ε = (1−B *)dβ
following expression. . 50
eff
∫
1− ε
BP
Figure 6-9: Effective emittance, ε , vs. blade angle, θ, for several values of the blades
eff
emittance, ε . ε has been numerically calculated by using the following
B eff
ε
BP
expression. ε = (1−B *)dβ . 51
eff
∫
1− ε
BP
Figure 6-10: Effective emittance, ε , vs. blade angle, θ, for several b/L values. ε has
eff eff
been numerically calculated by using the following expression.
ε
BP
ε = (1−B *)dβ . 52
eff
∫
1− ε
BP 0
Figure 6-11: Schematic diagram of a louver for shadow operation. . 53
Figure 6-12: Schematic diagram of the louver array showing the coordinates and the
significant geometrical characteristics. . 54
Figure 6-13: Dimensionless radiosity, B*, of the blades for several values of the blade
angle, θ. From Plamondon (1964) [28]. . 55
Figure 6-14: Dimensionless temperature, T*, of the blades for several values of the
blade angle, θ. From Plamondon (1964) [28]. . 55
Figure 6-15: Function f(θ) vs. blade angle θ. After Parmer & Buskirk (1967)a [25]. . 57
Figure 6-16: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ. ε = 0,05, ε = ε = 0.87. Calculated
B BP I
by the compiler. . 58
Figure 6-17: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ. ε = 0,05, ε = ε = 0,87. Calculated
B BP I
by the compiler. . 59
Figure 6-18: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ. ε = 0,05, ε = ε = 0,87. Calculated
B BP I
by the compiler. . 60
Figure 6-19: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ. ε = 0,05, ε = ε = 0,87. Calculated
B BP I
by the compiler. . 61
Figure 6-20: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ. ε = 0,05, ε = ε = 0,87. Calculated
B BP I
by the compiler. . 62
Figure 6-21: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ. ε = 0,05, ε = ε = 0,87. Calculated
B BP I
by the compiler. . 63
Figure 6-22: Net heat transfer through the louver, q, vs. baseplate temperature, T , for
BP
several values of the blade angle, θ
...