SIST-TP CEN/CLC/TR 17603-31-16:2021
(Main)Space Engineering - Thermal design handbook - Part 16: Thermal Protection System
Space Engineering - Thermal design handbook - Part 16: Thermal Protection System
The thermal protection system (TPS) of a space vehicle ensures the structural integrity of the surface of the craft and maintains the correct internal temperatures (for crew, electronic equipment, etc.) when the vehicle is under the severe thermal loads of re-entry. These loads are characterised by very large heat fluxes over the relatively short period of re-entry.
The design of thermal protection systems for re-entry vehicles is very complex due to the number and complexity of phenomena involved: the flow around the vehicle is hypersonic, tridimensional and reactive, and its interaction with the vehicle’s surface may induce chemical reactions which are not fully understood.
Two TPS concepts for re-entry vehicles, ablative and radiative are examined and there is also an anlyisis of existing systems using them.
The Thermal design handbook is published in 16 Parts
TR 17603-31-01 Part 1A Thermal design handbook – Part 1: View factors
TR 17603-31-01 Part 2A Thermal design handbook – Part 2: Holes, Grooves and Cavities
TR 17603-31-01 Part 3A Thermal design handbook – Part 3: Spacecraft Surface Temperature
TR 17603-31-01 Part 4A Thermal design handbook – Part 4: Conductive Heat Transfer
TR 17603-31-01 Part 5A Thermal design handbook – Part 5: Structural Materials: Metallic and Composite
TR 17603-31-01 Part 6A Thermal design handbook – Part 6: Thermal Control Surfaces
TR 17603-31-01 Part 7A Thermal design handbook – Part 7: Insulations
TR 17603-31-01 Part 8A Thermal design handbook – Part 8: Heat Pipes
TR 17603-31-01 Part 9A Thermal design handbook – Part 9: Radiators
TR 17603-31-01 Part 10A Thermal design handbook – Part 10: Phase – Change Capacitors
TR 17603-31-01 Part 11A Thermal design handbook – Part 11: Electrical Heating
TR 17603-31-01 Part 12A Thermal design handbook – Part 12: Louvers
TR 17603-31-01 Part 13A Thermal design handbook – Part 13: Fluid Loops
TR 17603-31-01 Part 14A Thermal design handbook – Part 14: Cryogenic Cooling
TR 17603-31-01 Part 15A Thermal design handbook – Part 15: Existing Satellites
TR 17603-31-01 Part 16A Thermal design handbook – Part 16: Thermal Protection System
Raumfahrttechnik - Handbuch für thermisches Design - Teil 16: Wärmeschutzsystem
Ingénierie spatiale - Manuel de conception thermique - Partie 16: Protection Thermique des véhicules spatiaux
Vesoljska tehnika - Priročnik o toplotni zasnovi - 16. del: Sistem toplotne zaščite
General Information
Standards Content (Sample)
SLOVENSKI STANDARD
01-oktober-2021
Vesoljska tehnika - Priročnik o toplotni zasnovi - 16. del: Sistem toplotne zaščite
Space Engineering - Thermal design handbook - Part 16: Thermal Protection System
Raumfahrttechnik - Handbuch für thermisches Design - Teil 16: Wärmeschutzsystem
Ingénierie spatiale - Manuel de conception thermique - Partie 16: Protection Thermique
des véhicules spatiaux
Ta slovenski standard je istoveten z: CEN/CLC/TR 17603-31-16:2021
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 16:
Thermal Protection System
Ingénierie spatiale - Manuel de conception thermique - Raumfahrttechnik - Handbuch für thermisches Design -
Partie 16 : Protection Thermique des véhicules Teil 16: Thermalschutzsysteme
spatiaux
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 17603-31-16:2021 E
reserved worldwide for CEN national Members and for
CENELEC Members.
Table of contents
European Foreword . 5
1 Scope . 6
2 References . 7
3 Terms, definitions and symbols . 8
3.1 Terms and definitions . 8
3.2 Abbreviated terms. 8
4 Introduction . 9
4.1 General .9
4.2 Classification of thermal protection systems . 10
5 Ablative systems . 14
5.1 General . 14
5.2 Ablative materials . 14
5.3 Basic analysis . 15
5.3.1 Surface equilibrium . 16
5.4 Existing systems . 19
5.4.1 Galileo probe . 19
6 Radiative systems . 23
6.1 General . 23
6.2 Radiative materials . 23
6.3 Existing systems . 24
6.3.1 Space shuttle . 24
6.4 Other developments . 35
6.4.1 X-38 . 35
Bibliography . 54
Figures
Figure 4-1: Velocity-altitude map for the Space Shuttle. Lifting re-entry from orbit. . 9
Figure 4-2: Summary of re-entry trajectories. From East (1991) [6]. . 10
Figure 4-3: Sketch of an ablative thermal protection system. . 11
Figure 4-4: Sketch of a radiative thermal protection system. 11
Figure 4-5: Sketch of a transpiration thermal protection system. . 12
Figure 4-6: Typical transpiration cooling system . 13
Figure 5-1: Surface energy balance. 17
Figure 5-2: Galileo entry probe. . 20
Figure 5-3: Physical model and phenomena considered in material response analysis . 20
Figure 5-4: Temperature history at interfaces. . 22
Figure 5-5: Comparison of mass loss fluxes. . 22
Figure 6-1: Worst case peak predicted surface temperatures. [K] for STS-1. From Dotts
et al. (1983) [5]. . 25
Figure 6-2: Worst case peak predicted structure temperatures. [K] for STS-1. From
Dotts et al. (1983) [5]. . 25
Figure 6-3: Thermal protection subsystems. From Dotts et al. (1983) [5] . 26
Figure 6-4: RCC system components. From Curry et al. (1983) [3]. . 27
Figure 6-5: Nose cap system components. From Curry et al. (1983) [3]. . 27
Figure 6-6: Wing leading-edge system components. From Curry et al. (1983) [3]. . 28
Figure 6-7: Tile attachment and gap filler configuration. From Dotts et al. (1983) [5]. . 29
Figure 6-8: Nose cap RCC surface comparison between prediction and flight data.
From Curry et al. (1983) [3] . 30
Figure 6-9: Nose cap access door tile surface comparison between prediction and flight
data. From Curry et al. (1983) [3]. . 30
Figure 6-10: Wing leading-edge panel (stagnation area). Comparison between
prediction and flight data. From Curry et al. (1983) [3]. . 31
Figure 6-11: STS-1 flight data analysis comparison for lower mid-fuselage location.
From Dotts et al. (1983) [3]. 31
Figure 6-12: STS-1 flight data analysis comparison for lower wing location. From Dotts
et al. (1983) [3] . 32
Figure 6-13: STS-1 flight data analysis comparison for lower inboard elevon location.
From Dotts et al. (1983) [3]. 32
Figure 6-14: STS-1 flight data analysis comparison for lower mid-fuselage side
location. From Dotts et al. (1983) [3]. . 33
Figure 6-15: Comparison of STS-2 data with analytical predictions. From Normal et al.
(1983) [11]. . 33
Figure 6-16: Comparison of STS-2 data with analytical predictions. From Normal et al.
(1983) [11]. . 34
Figure 6-17: Comparison of STS-2 data with analytical predictions. From Normal et al.
(1983) [11]. . 34
Figure 6-18: In-depth comparison of STS-2 data with analytical predictions for
maximum temperatures. From Normal et al. (1983) [11]. . 35
Figure 6-19: X-39 TPS Configuration . 36
Figure 6-20: X-38 Reference Heating . 36
Figure 6-21: CMC Side Panels together with lower CMC Chin Panel . 37
Figure 6-22: Stand-off Position and Global Design . 38
Figure 6-23: Stand-off Positions and Global Design . 39
Figure 6-24: Max. Pressure Load . 40
Figure 6-25: Max. Thermal Load at Panel Surface . 40
Figure 6-26: Nose Skirt Assembly with Insulation Blankets . 41
Figure 6-27: Max. and min. Heat flux time lines applied on the NSK. 41
Figure 6-28: Simplified description of heat transfer modes within the nose skirt
assembly. . 42
Figure 6-29: Temperature distribution over a NSK side panel at t = 1100s. . 44
Figure 6-30: Carrier Panel TPS Design . 45
Figure 6-31: X-38 Aeroshell Panel and Blanket Distribution . 46
Figure 6-32: X-38 Parafoil System . 46
Figure 6-33: Parafoil Line Routing and Acreage Blankets . 46
Figure 6-34: FEI-450 Blanket equipped with Gray FEI-1000High Emittance Coating . 47
Figure 6-35: Typical look of FEI-650 and Blanket with Gray High Emittance . 47
Figure 6-36: Allocation of Blanket Types to the X-38 Lee-Side Surface . 49
Figure 6-37: Qualification Test Sequence for X-38 . 50
Figure 6-38: Parameters and Results of the Qualification Tests . 50
Figure 6-39: Computer controlled sewing of FEI blankets . 52
Figure 6-40: FEI-1000 blankets of the Forward Fuselage . 52
Figure 6-41: FEI Blankets Integrated on the X-38 V-201 . 53
European Foreword
This document (CEN/CLC/TR 17603-31-16:2021) has been prepared by Technical Committee
CEN/CLC/JTC 5 “Space”, the secretariat of which is held by DIN.
It is highlighted that this technical report does not contain any requirement but only collection of data
or descriptions and guidelines about how to organize and perform the work in support of EN 16603-
31.
This Technical report (TR 17603-31-16:2021) originates from ECSS-E-HB-31-01 Part 16A.
Attention is drawn to the possibility that some of the elements of this document may be the subject of
patent rights. CEN [and/or CENELEC] shall not be held responsible for identifying any or all such
patent rights.
This document has been prepared under a mandate given to CEN by the European Commission and
the European Free Trade Association.
This document has been developed to cover specifically space systems and has therefore precedence
over any TR covering the same scope but with a wider domain of applicability (e.g.: aerospace).
Scope
The thermal protection system (TPS) of a space vehicle ensures the structural integrity of the surface of
the craft and maintains the correct internal temperatures (for crew, electronic equipment, etc.) when
the vehicle is under the severe thermal loads of re-entry. These loads are characterised by very large
heat fluxes over the relatively short period of re-entry.
The design of thermal protection systems for re-entry vehicles is very complex due to the number and
complexity of phenomena involved: the flow around the vehicle is hypersonic, tridimensional and
reactive, and its interaction with the vehicle’s surface may induce chemical reactions which are not
fully understood.
Two TPS concepts for re-entry vehicles, ablative and radiative are examined and there is also an
anlyisis of existing systems using them.
The Thermal design handbook is published in 16 Parts
TR 17603-31-01 Thermal design handbook – Part 1: View factors
TR 17603-31-02 Thermal design handbook – Part 2: Holes,
...
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