SIST-TP CEN/CLC/TR 17603-31-15:2021
(Main)Space Engineering - Thermal design handbook - Part 15: Existing Satellites
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
Standards Content (Sample)
SLOVENSKI STANDARD
SIST-TP CEN/CLC/TR 17603-31-15:2021
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
SIST-TP CEN/CLC/TR 17603-31-15:2021 en,fr,de
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
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SIST-TP CEN/CLC/TR 17603-31-15:2021
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SIST-TP CEN/CLC/TR 17603-31-15:2021
TECHNICAL REPORT
CEN/CLC/TR 17063-31-
15
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.
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CEN/CLC/TR 17603-31-15:2021 (E)
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
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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
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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
4
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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 Control Subsystem temperature limits. From Stümpel (1978)a
[45]. . 35
Figure 5-5: OTS thermal control layout summary. From Stümpel (1978)a [45]. . 39
Figure 5-6: Insulation in the OTS hydrazine line system. From Stümpel (1978)a [45]. . 39
Figure 5-7: OTS heater switching diagram. . 40
Figure 5-8: Thermal insulation of the hydrazine tank. The tank is totally covered with
low emittance tape. Heaters are of the foil type (see ECSS-E-HB-31-01
Part 11, clause 4.2). The tank contacts the platform via a low conductance
amount. From Stümpel (1978)b [46]. . 40
Figure 5-9: Thermal decoupling of FCV from TCA onboard OTS. The heat barrier
maintains temperature differences up to 800 K via a length of 0,03 m. . 41
Figure 5-10: Histograms for ground and first orbit test. From Bouchez & Gülpen (1980)
[5]. The ordinates show the number of samples the temperature deviation
of which stays within the limits shown in abscissae. (∆T = T −T ). . 43
measured predicted
Figure 5-11: Histograms for orbit tests during different summer solstices. Data for 1978
and 1980 are from Bouchez & Gülpen (1981) [5] and those for 1981 from
Bouchez & Howle (1982) [7]. . 44
Figure 5-12: Temperature increases ∆T as a function of time, t elapsed since Jan 1,
1978. From Chalmers, Konzok, Bouchez & Howlw (1983) [13]. Circle:
Summer Solstice test points. Square: Winter Solstice test points. Triangle:
Equinox test points. . 46
Figure 5-13: Mean solar absorptance, α , on antenna dish white S-13 G/LO paint. From
s
Chalmers, Konzok, Bouchez & Howle (1983) [13]. Circle: Summer Solstice
test points. Square: Winter Solstice test points. Triangle: Equinox test
points. . 48
Figure 6-1: Landsat spacecraft in orbital flight. . 49
Figure 6-2: Exploded view of the Landsat D spacecraft before deployment. . 50
Figure 6-3: Assembled Wide Band Module. . 53
Figure 6-4: Thermal Control coatings used on Landsat D. . 54
Figure 7-1: IRAS spacecraft in orbital flight. See also Table 7-1. From Van Leeuwen
(1983) [53]. . 58
Figure 7-2: IRAS telescope subsystem. From Urbach et al. (1982) [52] . 61
Figure 7-3: IRAS attitude constraints during mission. From Van Leeuwen (1983) [53]. 63
Figure 7-4: IRAS spacecraft thermal control layout summary. From Van Leewen (1983,
1985) [53] & [54]. . 65
Figure 7-5: IRAS Telescope thermal control layout summary. From Urbach et al. (1982)
[52] and Sherman (1982) [41]. . 67
Figure 7-6: IRAS Test Configuration. a. Thermal model. b. Complete satellite in JPL
facility. From Van Leeuwen (1983) [53]. . 67
Figure 7-7: Effect of Critical parameters on heat load to cryogen. From Urbach,
Hopkins & Mason (1983) [50]. . 69
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Figure 7-8: Tilting of the MCT for porous plug submersion. From Petrac & Mason
(1984) [39]. . 70
Figure 7-9: Vapor mass flow rate, m, and heat transfer rate, Q, through the plug vs.
pressure drop, ∆p. From Petrac & Mason (1984) [39]. 70
Figure 7-10: Histogram for ground and orbit test just after launching. The temperature
deviation is ∆T = T − T . From Van Leeuwen (1983) [53]. . 71
measured predicted
Figure 7-11: FSSS temperature, T, as a function of time, t, elapsed after launch. From
Van Leeuwen (1983) [53]. A thermal misalignment phenomenon, occurred
during the experimental phase of the mission, has been reported by
Karsten & Teule (1984) [31]. This phenomenon, which was adequately
modelled and partially overcome, was responsible for the development of
cross-scan attitude errors of up to 100 arcsec. The origins of the
misalignment changes could be traced to both spacecraft structure and
FSSS brackets. . 72
Figure 7-12: Cryogenic System Equilibrium Temperatures. From Urbach & Mason
(1984) [51]. . 74
Figure 7-13: Cryogenic boil-off rate according to different models. From Urbach,
Hopkings & Mason (1983) [50]. . 75
Figure 8-1: SPOT 1 spacecraft in orbital flight. . 76
Figure 8-2: Exploded view of the SPOT 1 subsystems and components which require
thermal control. Drawn by the compiler after Alet & Foret (1983) [1],
Fagnoni (1983) [20], Courtois & Weill (1985) [16]. Encircled numbers in the
figure are the same as those of the clauses in the text. . 84
Figure 8-3: Battery assembly of the SPOT multimission platform. From Fagnoni (1983)
[20]. . 86
Figure 8-4: Exploded view of the HRVs. From Mauduyt, Bonnet & Toulemont (1983)
[34]. . 87
Figure 8-5: Design hot mission profile for HRV and TMCU. From Racaud, d’Antin &
Lelièvret (1983) [40]. . 88
Figure 8-6: Thermal control layout summary of the HRV. From Mauduyt, Bonnet &
Toulemont (1983) [34]. . 90
Figure 8-7: SPOT 1 Satellite as seen from the –Z side. From Racaud et al. (1983) [40]. . 91
Figure 8-8: Temperature limits of the SPOT 1 platform components. From Alet & Foret
(1983) [1]. . 93
Figure 8-9: Test configuration of the batteries compartment of the SPOT multimission
platform. From Fanoni (1983) [20]. . 94
Figure 9-1: Olympus-1 in orbital flight. From Bonhomme & Steels (1984) [4], Steels &
Baston (1986) [44]. . 97
Figure 9-2: Exploded view of Olympus-1 satellite. From ESA (1984), Bowles (1987)
[10], Paul (1989) [38]. . 98
Figure 9-3: Schematic of the different phases of the Olympus-1 solar array deployment.
Prepared by the compiler after Bonhome & Steels (1984) [4], Bowles
(1987) [10]. . 100
Figure 9-4: Olympus-1 satellite thermal control layout used for thermal vacuum tests.
From Boggiatto, Colizzi, Perotto & Tavera (1985) [3]. Explanation is given
in Table 9-3. . 103
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Figure 9-5: Olympus-1 satellite battery thermal control layout. a) Ni-Cd battery; b) Ni-H
2
battery. From Konzok, Gutschmidt, Stümpel, Schlitt & Dunbar (1987) [33]. . 105
Figure 9-6: Temperature Difference Histograms for the three test cases considered in
the Thermal Vacuum Tests of Olympus-1 satellite (see Table 9-6 above).
From Boggiatto, Colizzi, Perotto & Tavera (1985) [3]. 109
Figure 9-7: Infrared test related activities. From Messidoro & Colizzi (1986) [37]. . 111
Figure 9-8: Temperature vs. time profiles of Olympus-1 satellite as obtained from the
infrared test. North radiator, inner face. South radiator, outer
face. Communications Module – Service Module, central cylinder.
Communications Module, upper floor. From Messidoro & Colizzi
(1986) [37]. . 113
Figure 10-1: ERS-1 in flight configuration. From Francis et al. (1991) [21]. . 115
Figure 10-2: Exploded view of ERS-1 satellite. From Francis et al. (1991) [21]. . 116
Figure 10-3: Schematic of the different phases of ERS-1 SAR Antenna deployment.
From Francis et al. (1991) [21]. . 123
Figure 10-4: ERS-1 satellite. PEM external thermal design. From Haimler, Overbosch &
Pieper (1987) [24] . 124
Figure 10-5: ERS-1 satellite. PEM internal thermal design. From Haimler, Overbosch &
Pieper (1987) [24]. . 125
Figure 10-6: Temperature difference histograms for the PL-Off Phase. From Haimler,
Kamp & Pieper (1990). . 131
Figure 10-7: Transient temperature behaviour of IDHT TWT’s: a) Predicted, b)
measured. From Haimler, Kamp & Pieper (1990). . 131
Tables
Table 4-1: Characteristics of the IUE Main Subsystems . 19
Table 4-2: IUE Flight Segment Mass Summary . 21
Table 4-3: Thermal Design Requirements . 23
Table 4-4: Estimated and Measured Performance of Spacecraft Components and
Scientific Instrument Components with Nominal Power Dissipation. . 26
Table 5-1: Characteristics of the OTS main Subsystems . 30
Table 5-2: OTS Mass Summary . 33
Table 5-3: Sensor Distribution . 42
Table 5-4: In Orbit Measured Values and Curve Fitting Values . 45
Table 5-5: Change in Solar Absorptance, ∆αs, of OSR vs. Exposure Time as Deduced
from OTS Solstice Data . 47
Table 6-1: Landsat D Flight Segment Mass Summary . 51
Table 6-2: Thermal Design Requirements . 52
Table 6-3: Estimated on Orbit Performance of the Instrument Module Components . 55
Table 7-1: IRAS Main Subsystems . 59
Table 7-2: Thermal Design Requirements . 62
Table 7-3: Cryogenic System performance Summary . 72
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Table 8-1: Characteristics of the SPOT 1 Main Subsystems . 77
Table 8-2: SPOT 1 Mass Summary . 79
Table 8-3: Limiting Temperatures and Heat Dissipation Rates of Typical Components –
SPOT 1 Satellite . 81
Table 8-4: Estimated and Measured Performance of the SPOT Multimission Platform
Batteries Compartment (T in K). . 94
Table 9-1: Olympus-1 Main Subsystems . 99
Table 9-2: Olympus Payload . 100
Table 9-3: Payload Subsystems Identification in Figure 9-4. . 103
Table 9-4: Olympus-1 Battery Performance Characteristics . 104
Table 9-5: Olympus-1 Thermal Test . 105
Table 9-6: Representative Cases Considered in the Thermal Test . 106
Table 9-7: Subsystem Temperature [K] after Different Steps in the Test-Mathematical
Model Interaction. . 108
-2
Table 9-8: Winter Solstice Heat Transfer Rates, Qe[W.m ], Measured and Compared
with the Requirements . 112
Table 10-1: Payload Main Subsystems . 117
Table 10-2: Typical Design Temperature Limits and PEM Dissipations . 120
Table 10-3: ERS-1 Thermal Test . 126
Table 10-4: Thermal Balance Test Phases. From Haimler, Kamp and Pieper (1990) . 128
Table 10-5: Final Level Correlation Status. Average Measured Predicted Deviation for
Steady State Case . 132
8
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...
SLOVENSKI STANDARD
kSIST-TP FprCEN/CLC/TR 17603-31-15:2021
01-maj-2021
Vesoljska tehnika - Priročnik za toplotno zasnovo - 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: FprCEN/CLC/TR 17603-31-15
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
kSIST-TP FprCEN/CLC/TR 17603-31- en,fr,de
15:2021
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
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kSIST-TP FprCEN/CLC/TR 17603-31-15:2021
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kSIST-TP FprCEN/CLC/TR 17603-31-15:2021
TECHNICAL REPORT
FINAL DRAFT
FprCEN/CLC/TR 17603-
RAPPORT TECHNIQUE
31-15
TECHNISCHER BERICHT
March 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: Bestehende Satelliten
This draft Technical Report is submitted to CEN members for Vote. 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.
Recipients of this draft are invited to submit, with their comments, notification of any relevant patent rights of which they are
aware and to provide supporting documentation.
Warning : This document is not a Technical Report. It is distributed for review and comments. It is subject to change without
notice and shall not be referred to as a Technical Report.
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. FprCEN/CLC/TR 17603-31-15:2021 E
reserved worldwide for CEN national Members and for
CENELEC Members.
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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
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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
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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
4
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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 Control Subsystem temperature limits. From Stümpel (1978)a
[45]. . 35
Figure 5-5: OTS thermal control layout summary. From Stümpel (1978)a [45]. . 39
Figure 5-6: Insulation in the OTS hydrazine line system. From Stümpel (1978)a [45]. . 39
Figure 5-7: OTS heater switching diagram. . 40
Figure 5-8: Thermal insulation of the hydrazine tank. The tank is totally covered with
low emittance tape. Heaters are of the foil type (see ECSS-E-HB-31-01
Part 11, clause 4.2). The tank contacts the platform via a low conductance
amount. From Stümpel (1978)b [46]. . 40
Figure 5-9: Thermal decoupling of FCV from TCA onboard OTS. The heat barrier
maintains temperature differences up to 800 K via a length of 0,03 m. . 41
Figure 5-10: Histograms for ground and first orbit test. From Bouchez & Gülpen (1980)
[5]. The ordinates show the number of samples the temperature deviation
of which stays within the limits shown in abscissae. (T = T T ). . 43
measured predicted
Figure 5-11: Histograms for orbit tests during different summer solstices. Data for 1978
and 1980 are from Bouchez & Gülpen (1981) [5] and those for 1981 from
Bouchez & Howle (1982) [7]. . 44
Figure 5-12: Temperature increases T as a function of time, t elapsed since Jan 1,
1978. From Chalmers, Konzok, Bouchez & Howlw (1983) [13]. Circle:
Summer Solstice test points. Square: Winter Solstice test points. Triangle:
Equinox test points. . 46
Figure 5-13: Mean solar absorptance, , on antenna dish white S-13 G/LO paint. From
s
Chalmers, Konzok, Bouchez & Howle (1983) [13]. Circle: Summer Solstice
test points. Square: Winter Solstice test points. Triangle: Equinox test
points. . 48
Figure 6-1: Landsat spacecraft in orbital flight. . 49
Figure 6-2: Exploded view of the Landsat D spacecraft before deployment. . 50
Figure 6-3: Assembled Wide Band Module. . 53
Figure 6-4: Thermal Control coatings used on Landsat D. . 54
Figure 7-1: IRAS spacecraft in orbital flight. See also Table 7-1. From Van Leeuwen
(1983) [53]. . 58
Figure 7-2: IRAS telescope subsystem. From Urbach et al. (1982) [52] . 61
Figure 7-3: IRAS attitude constraints during mission. From Van Leeuwen (1983) [53]. 63
Figure 7-4: IRAS spacecraft thermal control layout summary. From Van Leewen (1983,
1985) [53] & [54]. . 65
Figure 7-5: IRAS Telescope thermal control layout summary. From Urbach et al. (1982)
[52] and Sherman (1982) [41]. . 67
Figure 7-6: IRAS Test Configuration. a. Thermal model. b. Complete satellite in JPL
facility. From Van Leeuwen (1983) [53]. . 67
Figure 7-7: Effect of Critical parameters on heat load to cryogen. From Urbach,
Hopkins & Mason (1983) [50]. . 69
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Figure 7-8: Tilting of the MCT for porous plug submersion. From Petrac & Mason
(1984) [39]. . 70
Figure 7-9: Vapor mass flow rate, m, and heat transfer rate, Q, through the plug vs.
pressure drop, p. From Petrac & Mason (1984) [39]. 70
Figure 7-10: Histogram for ground and orbit test just after launching. The temperature
deviation is T = T T . From Van Leeuwen (1983) [53]. . 71
measured predicted
Figure 7-11: FSSS temperature, T, as a function of time, t, elapsed after launch. From
Van Leeuwen (1983) [53]. A thermal misalignment phenomenon, occurred
during the experimental phase of the mission, has been reported by
Karsten & Teule (1984) [31]. This phenomenon, which was adequately
modelled and partially overcome, was responsible for the development of
cross-scan attitude errors of up to 100 arcsec. The origins of the
misalignment changes could be traced to both spacecraft structure and
FSSS brackets. . 72
Figure 7-12: Cryogenic System Equilibrium Temperatures. From Urbach & Mason
(1984) [51]. . 74
Figure 7-13: Cryogenic boil-off rate according to different models. From Urbach,
Hopkings & Mason (1983) [50]. . 75
Figure 8-1: SPOT 1 spacecraft in orbital flight. . 76
Figure 8-2: Exploded view of the SPOT 1 subsystems and components which require
thermal control. Drawn by the compiler after Alet & Foret (1983) [1],
Fagnoni (1983) [20], Courtois & Weill (1985) [16]. Encircled numbers in the
figure are the same as those of the clauses in the text. . 84
Figure 8-3: Battery assembly of the SPOT multimission platform. From Fagnoni (1983)
[20]. . 86
Figure 8-4: Exploded view of the HRVs. From Mauduyt, Bonnet & Toulemont (1983)
[34]. . 87
Figure 8-5: Design hot mission profile for HRV and TMCU. From Racaud, d’Antin &
Lelièvret (1983) [40]. . 88
Figure 8-6: Thermal control layout summary of the HRV. From Mauduyt, Bonnet &
Toulemont (1983) [34]. . 90
Figure 8-7: SPOT 1 Satellite as seen from the –Z side. From Racaud et al. (1983) [40]. . 91
Figure 8-8: Temperature limits of the SPOT 1 platform components. From Alet & Foret
(1983) [1]. . 93
Figure 8-9: Test configuration of the batteries compartment of the SPOT multimission
platform. From Fanoni (1983) [20]. . 94
Figure 9-1: Olympus-1 in orbital flight. From Bonhomme & Steels (1984) [4], Steels &
Baston (1986) [44]. . 97
Figure 9-2: Exploded view of Olympus-1 satellite. From ESA (1984), Bowles (1987)
[10], Paul (1989) [38]. . 98
Figure 9-3: Schematic of the different phases of the Olympus-1 solar array deployment.
Prepared by the compiler after Bonhome & Steels (1984) [4], Bowles
(1987) [10]. . 100
Figure 9-4: Olympus-1 satellite thermal control layout used for thermal vacuum tests.
From Boggiatto, Colizzi, Perotto & Tavera (1985) [3]. Explanation is given
in Table 9-3. . 103
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Figure 9-5: Olympus-1 satellite battery thermal control layout. a) Ni-Cd battery; b) Ni-H
2
battery. From Konzok, Gutschmidt, Stümpel, Schlitt & Dunbar (1987) [33]. . 105
Figure 9-6: Temperature Difference Histograms for the three test cases considered in
the Thermal Vacuum Tests of Olympus-1 satellite (see Table 9-6 above).
From Boggiatto, Colizzi, Perotto & Tavera (1985) [3]. 109
Figure 9-7: Infrared test related activities. From Messidoro & Colizzi (1986) [37]. . 111
Figure 9-8: Temperature vs. time profiles of Olympus-1 satellite as obtained from the
infrared test. North radiator, inner face. South radiator, outer
face. Communications Module – Service Module, central cylinder.
Communications Module, upper floor. From Messidoro & Colizzi
(1986) [37]. . 113
Figure 10-1: ERS-1 in flight configuration. From Francis et al. (1991) [21]. . 115
Figure 10-2: Exploded view of ERS-1 satellite. From Francis et al. (1991) [21]. . 116
Figure 10-3: Schematic of the different phases of ERS-1 SAR Antenna deployment.
From Francis et al. (1991) [21]. . 123
Figure 10-4: ERS-1 satellite. PEM external thermal design. From Haimler, Overbosch &
Pieper (1987) [24] . 124
Figure 10-5: ERS-1 satellite. PEM internal thermal design. From Haimler, Overbosch &
Pieper (1987) [24]. . 125
Figure 10-6: Temperature difference histograms for the PL-Off Phase. From Haimler,
Kamp & Pieper (1990). . 131
Figure 10-7: Transient temperature behaviour of IDHT TWT’s: a) Predicted, b)
measured. From Haimler, Kamp & Pieper (1990). . 131
Tables
Table 4-1: Characteristics of the IUE Main Subsystems . 19
Table 4-2: IUE Flight Segment Mass Summary . 21
Table 4-3: Thermal Design Requirements . 23
Table 4-4: Estimated and Measured Performance of Spacecraft Components and
Scientific Instrument Components with Nominal Power Dissipation. . 26
Table 5-1: Characteristics of the OTS main Subsystems . 30
Table 5-2: OTS Mass Summary . 33
Table 5-3: Sensor Distribution . 42
Table 5-4: In Orbit Measured Values and Curve Fitting Values . 45
Table 5-5: Change in Solar Absorptance, , of OSR vs. Exposure Time as Deduced
s
from OTS Solstice Data . 47
Table 6-1: Landsat D Flight Segment Mass Summary . 51
Table 6-2: Thermal Design Requirements . 52
Table 6-3: Estimated on Orbit Performance of the Instrument Module Components . 55
Table 7-1: IRAS Main Subsystems . 59
Table 7-2: Thermal Design Requirements . 62
Table 7-3: Cryogenic System performance Summary . 72
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Table 8-1: Characteristics of the SPOT 1 Main Subsystems . 77
Table 8-2: SPOT 1 Mass Summary . 79
Table 8-3: Limiting Temperatures and Heat Dissipation Rates of Typical Components –
SPOT 1 Satellite . 81
Table 8-4: Estimated and Measured Performance of the SPOT Multimission Platform
Batteries Compartment (T in K). . 94
Table 9-1: Olympus-1 Main Subsystems . 99
Table 9-2: Olympus Payload . 100
Table 9-3: Payload Subsystems Identification in Figure 9-4. . 103
Table 9-4: Olympus-1 Battery Performance Characteristics . 104
Table 9-5: Olympus-1 Thermal Test . 105
Table 9-6: Representative Cases Considered in the Thermal Test . 106
Table 9-7: Subsystem Temperature [K] after Different Steps in the Test-Mathematical
Model Interaction. . 108
-2
Table 9-8: Winter Solstice Heat Transfer Rates, Qe[W.m ], Measured and Compared
with the Requirements . 112
Table 10-1: Payload Main Subsystems . 117
Table 10-2: Typical Design Temperature Limits and PEM Dissipations .
...
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