SIST EN 16603-31-02:2018
(Main)Space engineering - Two-phase heat transport equipment
Space engineering - Two-phase heat transport equipment
This standard defines requirements for two-phase heat transportation equipment (TPHTE), for use in spacecraft thermal control.
This standard is applicable to new hardware qualification activities.
Requirements for mechanical pump driven loops (MPDL) are not included in the present version of this Standard.
This standard includes definitions, requirements and DRDs from ECSS-E-ST-10-02, ECSS-E-ST-10-03, and ECSS-E-ST-10-06 applicable to TPHTE qualification. Therefore, these three standards are not applicable to the qualification of TPHTE.
This standard also includes definitions and part of the requirements of ECSS-E-ST-32-02 applicable to TPHTE qualification.
ECSS-E-ST-32-02 is therefore applicable to the qualification of TPHTE.
This standard does not include requirements for acceptance of TPHTE.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
Raumfahrttechnik - Ausrüstung für Zwei-Phasen-Wärmetransport
Ingénierie spatiale - Equipements de transfert de chaleur à deux phases
Vesoljska tehnika - Oprema za dvofazni toplotni transport
Ta standard določa zahteve za opremo za dvofazni toplotni transport (TPHTE) za uporabo pri toplotnem nadzoru vesoljskih plovil. Ta standard se uporablja za dejavnosti, povezane s kvalifikacijo nove strojne opreme. Zahteve za zanke s pogonom prek mehanskih črpalk (MPDL) niso vključene v trenutno različico tega standarda. Ta standard vključuje definicije, zahteve in dokumente z definicijami zahtev iz standardov ECSS-E-ST-10-02, ECSS-E-ST-10-03 in ECSS-E-ST-10-06, ki se uporabljajo za kvalifikacijo TPHTE. Zato se ti trije standardi ne uporabljajo za kvalifikacijo TPHTE. Ta standard vključuje tudi definicije in del zahtev standarda ECSS-E-ST-32-02, ki se uporabljajo za kvalifikacijo TPHTE. ECSS-E-ST-32-02 se zato uporablja za kvalifikacijo TPHTE. Ta standard ne vključuje zahtev za sprejetje TPHTE. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.
General Information
Relations
Standards Content (Sample)
SLOVENSKI STANDARD
SIST EN 16603-31-02:2018
01-november-2018
1DGRPHãþD
SIST EN 16603-31-02:2015
Vesoljska tehnika - Oprema za dvofazni toplotni transport
Space engineering - Two-phase heat transport equipment
Raumfahrttechnik - Ausrüstung für Zwei-Phasen-Wärmetransport
Ingénierie spatiale - Equipements de transfert de chaleur à deux phases
Ta slovenski standard je istoveten z: EN 16603-31-02:2018
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
SIST EN 16603-31-02:2018 en,fr,de
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
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SIST EN 16603-31-02:2018
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SIST EN 16603-31-02:2018
EUROPEAN STANDARD
EN 16603-31-02
NORME EUROPÉENNE
EUROPÄISCHE NORM
September 2018
ICS 49.140
Supersedes EN 16603-31-02:2015
English version
Space engineering - Two-phase heat transport equipment
Ingénierie spatiale - Equipements de transfert de Raumfahrttechnik - Ausrüstung für Zwei-Phasen-
chaleur à deux phases Wärmetransport
This European Standard was approved by CEN on 11 July 2018.
CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for
giving this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical
references concerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to
any CEN and CENELEC member.
This European Standard exists in three official versions (English, French, German). A version in any other language made by
translation under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC
Management Centre has the same status as the official versions.
CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium,
Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany,
Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania,
Serbia, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.
CEN-CENELEC Management Centre:
Rue de la Science 23, B-1040 Brussels
© 2018 CEN/CENELEC All rights of exploitation in any form and by any means Ref. No. EN 16603-31-02:2018 E
reserved worldwide for CEN national Members and for
CENELEC Members.
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Table of contents
European Foreword . 5
Introduction . 6
1 Scope . 7
2 Normative references . 8
3 Terms, definitions and abbreviated terms . 9
3.1 Terms defined in other standards . 9
3.2 Terms specific to the present standard . 10
3.3 Abbreviated terms. 13
4 TPHTE verification principles . 15
4.1 TPHTE categorization . 15
4.2 Involved organizations . 15
4.3 Generic requirements in this standard . 16
4.4 TPHTE qualification principles . 17
4.4.1 Processes, number of qualification units . 17
4.4.2 Thermal and mechanical qualification . 17
4.5 TPHTE acceptance principles . 21
5 Requirements for qualification activity . 22
5.1 Technical specification (TS) . 22
5.1.1 General . 22
5.1.2 Requirements to the TS . 22
5.1.3 Requirements for formulating technical requirements . 23
5.2 Materials, parts and processes . 23
5.3 General qualification requirements . 24
5.3.1 Qualification process . 24
5.3.2 Supporting infrastructure – Tools and test equipment . 24
5.4 Qualification process selection . 24
5.5 Qualification stage . 26
5.5.1 Qualification requirements . 26
5.5.2 Quality audits . 27
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5.5.3 Qualification methods . 27
5.5.4 Full and delta qualification programme . 29
5.5.5 Performance requirements . 29
5.6 Qualification test programme . 32
5.6.1 Number of qualification units . 32
5.6.2 Test sequence . 32
5.6.3 Test requirements . 35
5.6.4 Physical properties measurement . 38
5.6.5 Proof pressure test . 39
5.6.6 Pressure cycle test . 39
5.6.7 Burst pressure test . 39
5.6.8 Leak test . 40
5.6.9 Thermal performance test . 41
5.6.10 Mechanical tests . 43
5.6.11 Thermal cycle test . 45
5.6.12 Aging and life tests . 45
5.6.13 Gas plug test . 46
5.6.14 Reduced thermal performance test . 46
5.7 Operating procedures . 47
5.8 Storage . 47
5.9 Documentation . 47
5.9.1 Documentation summary . 47
5.9.2 Specific documentation requirements. 47
6 Requirements for acceptance activity . 50
6.1 General . 50
6.2 Acceptance process . 50
6.2.1 Materials, parts and processes. 50
6.2.2 General acceptance requirements . 50
6.2.3 Supporting infrastructure – Tools and test equipment . 51
6.2.4 Acceptance test programme . 51
6.2.5 Operating procedures . 51
6.2.6 Storage . 51
6.2.7 Documentation . 52
Bibliography . 53
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Figures
Figure 3-1: Tilt definition for HP . 12
Figure 3-2: Tilt definition for LHP . 12
Figure 4-1: Categories of TPHTE (two-phase heat transport equipment) . 16
Figure 4-2: Figure-of-merit (G) for some TPHTE fluids . 18
Figure 4-3: Definition of temperature and performance ranges for a HP . 19
Figure 5-1: Selection of qualification process . 26
Figure 5-2: Qualification test sequence for HP . 33
Figure 5-3: Qualification test sequence for CDL . 34
Tables
Table 4-1: Examples of allowed design modifications for acceptance hardware . 21
Table 5-1: Categories of two-phase heat transport equipment according to heritage
(adapted from ECSS-E-ST-10-02C, Table 5-1) . 24
Table 5-2: Allowable tolerances . 36
Table 5-3: Measurement accuracy . 38
Table 5-4: Equipment resonance search test levels . 44
Table 5-5: Sinusoidal vibration qualification test levels . 44
Table 5-6: Random vibration qualification test levels . 45
Table 5-7: TPHTE documentation . 49
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European Foreword
This document (EN 16603-31-02:2018) has been prepared by Technical
Committee CEN-CENELEC/TC 5 “Space”, the secretariat of which is held by
DIN.
This standard (EN 16603-31-02:2018) originates from ECSS-E-ST-31-02C Rev.1.
This document supersedes EN 16603-31-02:2015.
The main changes with respect to EN 16603-31-02:2015 are listed below:
• Implementation of Change Requests
• Clause 3 Terms, definition and abbreviated terms" updated and
Nomenclature added
• Titles of clauses 4, 5, 5.1, 5.5.1; updated
• Clause 4 updated to include TPHTE acceptance requirements in new
clause 4.5 "TPHTE acceptance principles"
• Merge of former clauses 4.4 and 4.5 to new clause 4.4 "TPHTE
qualification principles"
• DRDs in Annex A to H deleted. Requirements calling the DRDs updated
to the DRD in the dedicated ECSS Standard
This European Standard shall be given the status of a national standard, either
by publication of an identical text or by endorsement, at the latest by March
2019, and conflicting national standards shall be withdrawn at the latest by
March 2019.
Attention is drawn to the possibility that some of the elements of this document
may be the subject of patent rights. CEN shall not be held responsible for
identifying any or all such patent rights.
This document has been prepared under a standardization request 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 EN covering the same scope but with a wider
domain of applicability (e.g. : aerospace).
According to the CEN-CENELEC Internal Regulations, the national standards
organizations of the following countries are bound to implement this European
Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic,
Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France,
Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania,
Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Serbia,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United
Kingdom.
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Introduction
This Standard replaces ESA PSS-49, Issue 2 “Heat pipe qualification
requirements”, written in 1983, when the need for heat pipes in several ESA
projects had been identified. At that time a number of European development
activities were initiated to provide qualified heat pipes for these programmes,
which culminated in a first heat pipe application on a European spacecraft in
1981 (MARECS, BR-200, ESA Achievements - More Than Thirty Years of
Pioneering Space Activity, ESA November 30, 2001), followed by a first major
application on a European communication satellite in 1987 (TV-SAT 1, German
Communication Satellites).
ESA PSS-49 was published at a time, when knowledge of heat pipe technology
started to evolve from work of a few laboratories in Europe (IKE, University
Stuttgart, EURATOM Research Centre, Ispra). Several wick designs, material
combinations and heat carrier fluids were investigated and many process
related issues remained to be solved. From today’s view point the qualification
requirements of ESA PSS-49 appear therefore very detailed, exhaustive and in
some cases disproportionate in an effort to cover any not yet fully understood
phenomena. As examples the specified number of qualification units (14), the
number of required thermal cycles (800) and the extensive mechanical testing
(50 g constant acceleration, high level sine and random vibration) can be cited.
The present Standard takes advantage of valid requirements of ESA PSS-49, but
reflects at the same time today’s advanced knowledge of two-phase cooling
technology, which can be found with European manufacturers. This includes
experience to select proven material combinations, reliable wick and container
designs, to apply well-established manufacturing and testing processes, and
develop reliable analysis tools to predict in-orbit performance of flight
hardware. The experience is also based on numerous successful two-phase
cooling system applications in European spacecraft over the last 20 years.
Besides streamlining the ESA PSS-49, to arrive at today’s accepted set of heat
pipe qualification requirements, the following features have also been taken
into account:
• Extension of PSS-49 heat pipe qualification requirements to include heat
pipe acceptance requirements;
• Inclusion of qualification and acceptance requirements for two-phase
loops (CPL, LHP);
• Reference to applicable requirements in other ECSS documents;
• Formatting to recent ECSS template in order to produce a document,
which can be used in business agreements between customer and
supplier.
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1
Scope
This standard defines qualification and acceptance requirements for two-phase
heat transportation equipment (TPHTE), for use in spacecraft thermal control.
This standard is applicable to qualification and acceptance activities of new
hardware.
However, acceptance requirements of this Standard can be used for existing
hardware, which has been qualified previously to other requirements than
listed herein.
Requirements for mechanical pump driven loops (MPDL) are not included in
the present version of this Standard.
This standard also includes definitions and part of the requirements of ECSS-E-
ST-32-02 applicable to TPHTE qualification and acceptance.
This standard may be tailored for the specific characteristics and constraints of a
space project in conformance with ECSS-S-ST-00.
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2
Normative references
The following normative documents contain provisions which, through
reference in this text, constitute provisions of this ECSS Standard. For dated
references, subsequent amendments to, or revision of any of these publications
do not apply. However, parties to agreements based on this ECSS Standard are
encouraged to investigate the possibility of applying the more recent editions of
the normative documents indicated below. For undated references, the latest
edition of the publication referred to applies.
EN reference Reference in text Title
EN 16601-00-01 ECSS-S-ST-00-01 ECSS system - Glossary of terms
EN 16603-10-02 ECSS-E-ST-10-02 Space engineering - Verification
EN 16603-10-03 ECSS-E-ST-10-03 Space engineering - Testing
EN 16603-10-06 ECSS-E-ST-10-06 Space engineering - Technical requirements
specification
EN 16603-31 ECSS-E-ST-31 Space engineering - Thermal control general
requirements
EN 16603-32 ECSS-E-ST-32 Space engineering - Structural general requirements
EN 16603-32-01 ECSS-E-ST-32-01 Space engineering- Fracture control
EN 16603-32-02 ECSS-E-ST-32-02 Space engineering - Structural design and
verification of pressurized hardware
EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical
parts and processes
EN 9100:2009 Aerospace series - Quality management systems -
Requirements for Aviation, Space and Defense
Organizations
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3
Terms, definitions and abbreviated terms
3.1 Terms defined in other standards
a. For the purpose of this Standard, the terms and definitions from ECSS-E-
ST-00-01 apply, and in particular the following:
1. acceptance
2. certification
3. component
4. customer
5. equipment
6. product assurance
7. qualification
8. supplier
b. For the purpose of this standard, the following terms and definitions
from ECSS-E-ST-10-02 apply:
1. acceptance stage
2. analysis
3. inspection
4. qualification stage
5. review-of-design (ROD)
6. test
c. For the purpose of this standard, the following terms and definitions
from ECSS-E-ST-32-02 apply:
1. burst pressure
2. internal pressure
3. leak-before-burst (LBB)
4. pressure vessel (PV)
5. pressurized hardware (PH)
6. proof test
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3.2 Terms specific to the present standard
3.2.1 capillary driven loop (CDL)
TPL in which fluid circulation is accomplished by capillary action
NOTE See TPL definition in 3.2.21.
3.2.2 capillary pumped loop (CPL)
CDL with the fluid reservoir separated from the evaporator and without a
capillary link to the evaporator
NOTE See CDL definition in 3.2.1.
3.2.3 constant conductance heat pipe (CCHP)
heat pipe with a fixed thermal conductance between evaporator and condenser
at a given saturation temperature
NOTE See heat pipe definition in 3.2.7.
3.2.4 dry-out
depletion of liquid in the evaporator section at high heat input when the
capillary pressure gain becomes lower than the pressure drop in the circulating
fluid
3.2.5 effective length
heat pipe length between middle of evaporator and middle of condenser for
configurations with one evaporator and one condenser only
NOTE Used to determine the heat pipe transport
capability (see 3.2.10).
3.2.6 exposure temperature range
maximum temperature range to which a TPHTE is exposed during its product
life cycle and which is relevant for thermo-mechanical qualification
NOTE 1 The internal pressure at the maximum temperature
of this range defines the MDP for the pressure
vessel qualification of a TPHTE.
NOTE 2 The extreme temperatures of this range can be
below freezing or above critical temperatures of
the working fluid.
NOTE 3 In other technical domains, this temperature range
is typically called non-operating temperature
range (see clause 4 for additional explanation).
3.2.7 heat pipe (HP)
TPHTE consisting of a single container with liquid and vapour passages
arranged in such a way that the two fluid phases move in counter flow
NOTE 1 See TPHTE definition in 3.2.20.
NOTE 2 The capillary structure in a heat pipe extends over
the entire container length.
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3.2.8 heat pipe diode (HPD)
heat pipe which transports heat based on evaporation and condensation only in
one direction
NOTE See heat pipe definition in 3.2.7.
3.2.9 loop heat pipe (LHP)
CDL with the fluid reservoir as integral part of the evaporator
NOTE 1 See CDL definition in 3.2.1.
NOTE 2 The reservoir can be separated, but has a capillary
link to the evaporator.
3.2.10 heat transport capability
maximum amount of heat, which can be transported in a TPHTE from the
evaporator to the condenser
NOTE For heat pipes it is the maximum heat load
expressed in [Wm] (transported heat times
effective length).
3.2.11 maximum design pressure (MDP)
maximum allowed pressure inside a TPHTE during product life cycle
3.2.12 mechanical pump driven loop (MPDL)
TPL in which fluid circulation is accomplished by a mechanical pump
NOTE See TPL definitions in 3.2.21.
3.2.13 product life cycle
product life starting from the delivery of the TPHTE hardware until end of
service live
NOTE The product life cycle starts after acceptance of
the product for flight.
3.2.14 reflux mode
operational mode where the liquid is returned from the condenser to the
evaporator by gravitational forces and not by capillary forces
3.2.15 start-up
operational phase starting with initial supply of heat to the evaporator until
nominal operating conditions of the device are established
3.2.16 sub-cooling
temperature difference between average CDL reservoir temperature and the
temperature of the liquid line at the inlet to the reservoir
NOTE The average CDL reservoir temperature
represents the saturation temperature inside the
reservoir.
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3.2.17 thermal performance temperature range
temperature range for which a TPHTE is thermally qualified
NOTE In the thermal performance temperature range
a thermal performance map exists.
3.2.18 tilt for HP
height of the evaporator above the condenser during ground testing
NOTE 1 This definition is valid for a configuration with one
evaporator and one condenser (see Figure 3-1).
NOTE 2 The tilt is measured from the highest point to the
lowest point in Figure 3-1.
evaporator
condenser
Figure 3-1: Tilt definition for HP
3.2.19 tilt for LHP
height of the evaporator above the reservoir during ground testing
NOTE 1 See Figure 3-2.
NOTE 2 The tilt is measured from the highest point of the
evaporator to the lowest point of the condenser in
Figure 3-2.
Figure 3-2: Tilt definition for LHP
3.2.20 two-phase heat transport equipment (TPHTE)
hermetically closed system filled with a working fluid and transporting thermal
energy by a continuous evaporation and condensation process using the latent
heat of the fluid
NOTE 1 A fluid evaporates in the heat input zone
(evaporator) and condenses in the heat output
zone (condenser).
NOTE 2 This is in contrast to a single-phase loop where the
sensible heat of a liquid is transported (a liquid
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heats up in the heat input zone and cools down in
the heat output zone).
3.2.21 two-phase loop (TPL)
TPHTE with physically separated vapour and liquid transport lines forming a
closed loop
NOTE See TPHTE definition in 3.2.20.
3.2.22 variable conductance heat pipe (VCHP)
heat pipe with an additional non-condensable gas reservoir allowing a variable
thermal conductance between evaporator and condenser
NOTE 1 See heat pipe definition in 3.2.7.
NOTE 2 The variation in thermal conductance is generally
accomplished by regulating the volume of a non-
condensable gas plug reaching into the condenser
zone, which in turn varies the effective condenser
length.
NOTE 3 The variation of the gas volume can be performed
by active or passive means.
3.3 Abbreviated terms
For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01
and the following apply:
Abbreviation Meaning
constant conductance heat pipe
CCHP
capillary driven loop
CDL
capillary pumped loop
CPL
coefficient of thermal expansion
CTE
document requirements definition
DRD
heat pipe
HP
heat pipe diode
HPD
leak before burst
LBB
loop heat pipe
LHP
maximum design pressure
MDP
mechanical pump driven loop
MPDL
metallic special pressurized equipment
MSPE
non-destructive inspection
NDI
pressurized hardware
PH
review-of-design
ROD
Qmax maximum heat transport capability
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Abbreviation Meaning
special pressurized equipment
SPE
thermal control (sub)system
TCS
two-phase heat transport equipment
TPHTE
two-phase loop
TPL
technical requirement specification
TS
variable conductance heat pipe
VCHP
verification plan
VP
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4
TPHTE verification principles
4.1 TPHTE categorization
TPHTE as defined in 3.2.20 of this Standard are considered ‘special
pressurized equipment’ (SPE), as per definition of ECSS-E-ST-32-02.
Requirements of ECSS-E-ST-32-02 are included in this Standard for this reason.
The TPHTE are categorized in Figure 4-1 according to their design and
functional principle.
HP’s, LHP’s and CPL’s are categorized as MSPE (Metallic Special Pressurized
Equipment) as described in section 4.1.2 ECSS-E-ST-32-02
Heat pipes consist of a single container with a capillary structure extending
over the entire container length. Liquid and vapour passages are arranged in
such a way that the two fluid phases move in counter flow.
Capillary driven loops (CDL) have separate evaporator and condenser sections,
which are connected by dedicated vapour and liquid tubing. At least one
capillary structure is located in the evaporator section, which serves as capillary
pump to circulate the fluid in a true loop configuration.
The mechanically pumped two-phase loop (MPDL) has a configuration, which
is similar to the CDL, except that the circulation of the fluid is accomplished by
a mechanical pump.
NOTE Requirements for MPDL are not included in the
present version of this Standard.
4.2 Involved organizations
The verification process of TPHTE is generally carried out by a specialized
equipment manufacturer (called in this document “supplier”) and controlled by
the verification authority (called in this document the “customer”).
The verification activity is embedded in the supplier’s product assurance and
quality organization and in most cases the supplier's quality assurance plan has
been established and approved for space activities independently from the
TPHTE verification process specified in this document. It is the task of the
supplier’s PA authority to introduce and approve adequate product assurance
provisions at his subcontractor(s). The existence of an approved PA Plan is
precondition for commencing verification activities.
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Figure 4-1: Categories of TPHTE (two-phase heat trans
...
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