SIST-TP CEN/CLC/TR 17603-31-15:2021

Space Engineering - Thermal design handbook - Part 15: Existing Satellites

In this Part 15, existing satellites are described and examined from a thermal control and design view. The thermal control requirements are given and an assessment is made of the thermal control systems used against performance for each satellite.
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 15: Bestehende Satelliten

Ingénierie spatiale - Manuel de conception thermique - Partie 15: Véhicules spatiaux existants

Vesoljska tehnika - Priročnik o toplotni zasnovi - 15. del: Obstoječi sateliti

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 17603-31-15:2021 - Space Engineering - Thermal design handbook - Part 15: Existing Satellites

Standards Content (Sample)

SLOVENSKI STANDARD
01-oktober-2021
Vesoljska tehnika - Priročnik o toplotni zasnovi - 15. del: Obstoječi sateliti
Space Engineering - Thermal design handbook - Part 15: Existing Satellites
Raumfahrttechnik - Handbuch für thermisches Design - Teil 15: Bestehende Satelliten
Ingénierie spatiale - Manuel de conception thermique - Partie 15: Véhicules spatiaux
existants
Ta slovenski standard je istoveten z: CEN/CLC/TR 17063-31-15:2021
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 17063-31-
RAPPORT TECHNIQUE
TECHNISCHER BERICHT
August 2021
ICS 49.140
English version
Space Engineering - Thermal design handbook - Part 15:
Existing Satellites
Ingénierie spatiale - Manuel de conception thermique - Raumfahrttechnik - Handbuch für thermisches Design -
Partie 15 : Véhicules spatiaux existants Teil 15: Existierende Satelliten

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 17063-31-15:2021 E
reserved worldwide for CEN national Members and for
CENELEC Members.
Table of contents
European Foreword . 9
1 Scope . 10
2 References . 11
3 Terms, definitions and symbols . 12
3.1 Terms and definitions . 12
3.2 Abbreviated terms. 12
3.3 Symbols . 17
4 International ultraviolet explorer (IUE) . 18
4.1 Mission . 18
4.2 Main subsystems . 18
4.3 Main characteristics of the satellite . 20
4.4 Orbit . 21
4.5 Thermal design requirements . 22
4.6 Design tradeoffs . 24
4.7 Thermal control of various components . 24
4.8 Estimated on orbit performance . 25
5 Orbital test satellite (OTS) . 29
5.1 Mission . 29
5.2 Main subsystems . 29
5.3 Main characteristics of the satellite . 32
5.4 Orbit . 35
5.5 Thermal design requirements . 35
5.6 Design tradeoffs . 36
5.7 Thermal control of various components . 36
5.8 Estimated on orbit performance . 42
5.9 Measured in orbit performance . 42
6 Landsat D . 49
6.1 Mission . 49
6.2 Main subsystems . 49
6.3 Main characteristics of the satellite: . 50
6.4 Orbit . 51
6.5 Thermal design requirements . 51
6.6 Design tradeoffs . 52
6.7 Thermal control of various components . 52
6.8 Estimated on orbit performance . 54
6.9 Verification . 56
6.10 Measured on orbit performance . 57
7 Infrared astronomical satellite (IRAS) . 58
7.1 Mission . 58
7.2 Main subsystems . 58
7.3 Spacecraft main characteristics . 60
7.4 Orbit . 61
7.5 Thermal design requirements . 62
7.6 Design constraints . 63
7.7 Thermal control of various components . 64
7.8 Test of the spacecraft system . 67
7.9 Test of the superfluid Helium Dewar . 68
7.9.1 General . 68
7.9.2 Test of the plug . 69
7.9.3 Prelaunch preparations . 70
7.10 On orbit performance of the spacecraft . 71
7.11 On orbit performance of the cryogenic system . 72
8 Satellite probatoire d’observation de la terre (SPOT). 76
8.1 Mission . 76
8.2 Main subsystems . 76
8.3 Main characteristics of the satellite . 77
8.4 Orbit . 80
8.5 Thermal design requirements . 80
8.5.1 Functional modes . 80
8.5.2 Orbital constraints . 80
8.5.3 Limiting temperatures . 81
8.5.4 Thermal interfaces . 83
8.6 Design tradeoffs . 83
8.7 Thermal control of various components . 84
8.7.1 Platform . 84
8.7.2 Batteries compartment . 85
8.7.3 High-resolution visible range instruments . 87
8.7.4 Payload telemetry system . 90
8.8 Estimated on-orbit performance . 92
8.8.1 Platform . 92
8.8.2 Batteries compartment . 93
8.8.3 High-resolution visible range instrument . 95
8.8.4 Payload telemetry system . 95
9 Olympus-1 . 97
9.1 Mission . 97
9.2 Main subsystems . 97
9.3 Orbit . 102
9.4 Thermal design requirements . 102
9.5 Thermal control . 102
9.6 Thermal test of olympus-1 . 105
9.6.1 Thermal vacuum test . 106
9.6.2 Infrared test . 109
10 ERS-1 . 114
10.1 Mission . 114
10.2 Main subsystems . 115
10.3 Orbit . 119
10.4 Thermal design requirements . 119
10.5 Thermal control . 122
10.6 Thermal tests . 126
10.6.1 Thermal balance test of the engineering model . 126
10.6.2 Thermal vacuum test . 132
Bibliography . 133

Figures
Figure 4-1: IUE spacecraft in orbital flight. . 18
Figure 4-2: Exploded view of the IUE spacecraft. . 20
Figure 4-3: IUE orientation to the Sun and reference axes. . 22
Figure 4-4: Assembled IUE Spacecraft. From Skladany & Seivold (1976) [42]. Notice
that this figure, which corresponds to an earlier development, differs from
Figure 4-1 in minor details. . 23
Figure 4-5: IUE main equipment platform. From Skladany & Seivold (1976) [42]. . 24
Figure 5-1: OTS mission event sequence. From Collette & Stockwell (1976) [14]. . 29
Figure 5-2: Exploded view of the OTS spacecraft. From Bouchez, Howle & Stümpel
(1978) [9]. . 33
Figure 5-3: OTS main organic diagram. From Collette & Stockwell (1976) [14]. . 34
Figure 5-4: OTS Thermal Co
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