iTeh StandardsiTeh Standards
EURUSD
Your shopping cart is empty.
CEN

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: Existierende 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
Publication Date
10-Aug-2021
ICS
49.140 - Space systems and operations
Technical Committee
CEN/CLC/TC 5 - Space
Drafting Committee
CEN/CLC/TC 5/WG 6 - Upstream standards
Current Stage
6060 - Definitive text made available (DAV) - Publishing
Start Date
11-Aug-2021
Due Date
14-Jul-2022
Completion Date
11-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
SIST-TP CEN/CLC/TR 17603-31-15:2021 - Space Engineering - Thermal design handbook - Part 15: Existing Satellites

Buy Standard

TP CEN/CLC/TR 17603-31-15:2021TP CEN/CLC/TR 17603-31-15:2021
PreviousNext
Technical report
TP CEN/CLC/TR 17603-31-15:2021
English language
136 pages
sale 10% off
Preview
sale 10% off
Preview
e-Library read for
1 day

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.

---------------------- Page: 1 ----------------------
SIST-TP CEN/CLC/TR 17603-31-15:2021

---------------------- Page: 2 ----------------------
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.

---------------------- Page: 3 ----------------------
SIST-TP CEN/CLC/TR 17603-31-15:2021
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 .
...

Questions, Comments and Discussion

Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.

This May Also Interest You

CEN
EN 16603-20-40:2023(Main)
Space engineering - ASIC, FPGA and IP Core engineering
SIST EN 16603-20-40:2024

This activity w ill be the parallel development of EN 16603-20-40 and ECSS-E-ST-20-40C.
The scope shall cover the areas of existing ASIC and FPGA engineering chapter 5 of ECSS-Q-ST-60-02C, but w ith w ider breadth and greater depth, covering engineering requirements of end-to-end development flow s, from specification of requirements to validation of prototypes, of the follow ing monolithic devices for its use in space:
• ASICs (distinguishing digital, analogue and mixed-signal development flow s)
• FPGAs (distinguishing three technology families: SRAM, FLASH and anti-fuse technologies)
• ASIC and FPGA System-on-Chip embedding processor cores w hich have external “softw are programme” dependencies to be addressed during the SoC development, resulting in SW-HW co-design requirements.

  • Standard
    139 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16604-10:2023(Main)
Space sustainability - Space debris mitigation requirements (ISO 24113:2023, modified)
SIST EN 16604-10:2024

This document defines the primary space debris mitigation requirements applicable to all elements of unmanned systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations.

  • Standard
    20 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16603-20:2023(Main)
Space engineering - Electrical and electronic
SIST EN 16603-20:2024

Scope remains unchanged.
This Standard establishes the basic rules and general principles applicable to the electrical, electronic, electromagnetic, microwave and engineering processes. It specifies the tasks of these engineering processes and the basic performance and design requirements in each discipline.
It defines the terminology for the activities within these areas.
It defines the specific requirements for electrical subsystems and payloads, deriving from the system engineering requirements laid out in EN 16603-10 (equivalent of ECSS-E-ST-10 "Space engineering - System engineering general requirements".)

  • Standard
    135 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16603-20-08:2023(Main)
Space engineering - Photovoltaic assemblies and components
SIST EN 16603-20-08:2023

This Standard specifies the general requirements for the qualification, procurement, storage and delivery of photovoltaic assemblies, solar cell assemblies, bare solar cells, coverglasses and protection diodes suitable for space applications.
This standard does not cover the particular qualification requirements for a specific mission.
This Standard primarily applies to qualification approval for photovoltaic assemblies, solar cell assemblies, bare solar cells, coverglasses and protection diodes, and to the procurement of these items.
This standard is limited to crystaline Silicon and single and multi-junction GaAs solar cells with a thickness of more than 50 m and does not include thin film solar cell technologies and poly-crystaline solar cells.
This Standard does not cover the concentration technology, and especially the requirements related to the optical components of a concentrator (e.g. reflector and lens) and their verification (e.g. collimated light source).
This Standard does not apply to qualification of the solar array subsystem, solar panels, structure and solar array mechanisms.

  • Standard
    230 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16602-60:2023(Main)
Space product assurance - Electrical, electronic and electromechanical (EEE) components
SIST EN 16602-60:2023

The Scope of the Standard remains unchanged.
This standard defines the requirements for selection, control, procurement and usage of EEE components for space projects.
This standard differentiates between three classes of components through three different sets of standardization requirements (clauses) to be met.
The three classes provide for three levels of trade-off between assurance and risk. The highest assurance and lowest risk is provided by class 1 and the lowest assurance and highest risk by class 3. Procurement costs are typically highest for class 1 and lowest for class 3. Mitigation and other engineering measures may decrease the total cost of ownership differences between the three classes. The project objectives, definition and constraints determine which class or classes of components are appropriate to be utilised within the system and subsystems.
a.   Class 1 components are described in Clause 4.
b.   Class 2 components are described in Clause 5
c.   Class 3 components are described in Clause 6.
The requirements of this document apply to all parties involved at all levels in the integration of EEE components into space segment hardware and launchers.

  • Standard
    103 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16602-70-40:2023(Main)
Space product assurance - Processing and quality assurance requirements for hard brazing of metallic materials for flight hardware
SIST EN 16602-70-40:2023

2021-04-21: This EN is based on ECSS-Q-ST-70-40C

  • Standard
    39 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16602-60-13:2023(Main)
Space product assurance - Commercial electrical, electronic and electromechanical (EEE) components
SIST EN 16602-60-13:2023

2021-04-21: This EN is based on ECSS-Q-ST-60-13C Rev.1

  • Standard
    106 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16602-70-61:2022(Main)
Space product assurance - High-reliability soldering for surface mount, mixed technology and hand-mounted electrical connections
SIST EN 16602-70-61:2022

This standard defines:
- the basic requirements for the verification and approval of automatic machine w ave soldering for use in spacecraft hardware. The process requirements for w ave soldering of doublesided and multilayer boards are also defined.
- the technical requirements and quality assurance provisions for the manufacture and verification of manuallysoldered, high-reliability electrical connections.
- the technical requirements and quality assurance provisions for the manufacture and verification of high-reliability electronic circuits based on surface mounted device (SMD) and mixed technology.
- the acceptance and rejection criteria for high reliability manufacture of manually-soldered electrical connections intended to w ithstand normal terrestrial conditions and the vibrational g-loads and environment imposed by space flight.
- the proper tools, correct materials, design and w orkmanshipt. Workmanship standards are included to permit discrimination betw een proper and improper work.
SCOPE
This Standard defines the technical requirements and quality assurance provisions for the manufacture and verification of high-reliability electronic circuits of surface mount, through hole and solderless assemblies.
The Standard defines w orkmanship requirements, the acceptance and rejection criteria for high-reliability assemblies intended to withstand normal terrestrial conditions and the environment imposed by space flight.
The mounting and supporting of components, terminals and conductors specified in this standard applies only to assemblies designed to continuously operate over the mission w ithin the temperature limits of -55 °C to +85 °C at solder joint level.
Requirements related to printed circuit boards are contained in ECSS-Q-ST-70-60 (equivalent to EN 16602-70-60) and ECSS-Q-ST-70-12 (equivalent to EN 16602-70-12).
This Standard does not cover the qualification and acceptance of the EQM and FM equipment w ith high-reliability electronic circuits of surface mount, through hole and solderless assemblies.
This Standard does not cover verification of thermal properties for component assembly.
This Standard does not cover pressfit connectors.
The qualification and acceptance tests of equipment manufactured in accordance w ith this Standard are covered by ECSS-EST-10-03 (equivalent to EN 16603-10-03).

  • Standard
    253 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16603-10-03:2022(Main)
Space engineering - Testing
SIST EN 16603-10-03:2022

This standard addresses the requirements for performing verification by testing of space segment elements and space segment equipment on ground prior to launch. The document is applicable for tests performed on qualification models, flight models (tested at acceptance level) and protoflight models.
The standard provides:
• Requirements for test programme and test management,
• Requirements for retesting,
• Requirements for redundancy testing,
• Requirements for environmental tests,
• General requirements for functional and performance tests,
NOTE Specific requirements for functional and performance tests are not part of this standard since they are defined in the specific project documentation.
• Requirements for qualification, acceptance, and protoflight testing including qualification, acceptance, and protofight models’ test margins and duration,
• Requirements for test factors, test condition, test tolerances, and test accuracies,
• General requirements for development tests pertinent to the start of the qualification test programme,
NOTE Development tests are specific and are addressed in various engineering discipline standards.
• Content of the necessary documentation for testing activities (e.g. DRD).
Due to the specific aspects of the follow ing types of test, this Standard does not address:
• Space system testing (i.e. testing above space segment element), in particular the system validation test,
• In-orbit testing,
• Testing of space segment subsystems,
NOTE Tests of space segment subsystems are often limited to functional tests that, in some case, are run on dedicated models. If relevant, qualification tests for space segment subsystems are assumed to be covered in the relevant discipline standards.
Testing of hardware below space segment equipment levels (including assembly, parts, and components),
• Testing of stand-alone software,
NOTE For verification of flight or ground softw are, EN 16603-40 (ECSS-E-ST-40) and EN 16602-80 (ECSS-Q-ST-80) apply.
• Qualification testing of tw o-phase heat transport equipment,
NOTE For qualification testing of tw o-phase heat transport equipment, EN 16603-31-02 (ECSS-E-ST-31-02) applies.
• Tests of launcher segment, subsystem and equipment, and launch facilities,
• Tests of facilities and ground support equipment,
• Tests of ground segment.
This activity will be the update of EN16603-10-03:2014
NOTE: Parallel development of update of EN Standard and the new European TR17603-10-03.

  • Standard
    132 pages
    English language
    sale 10% off
    e-Library read for
    1 day
CEN
EN 16603-20-07:2022(Main)
Space engineering - Electromagnetic compatibility
SIST EN 16603-20-07:2022

EMC policy and general system requirements are specified in ECSS-E-ST-20 (equivalent to EN 16603-20).
This ECSS-E-ST-20-07 (equivalent to EN 16603-20-07) Standard addresses detailed system requirements (Clause 4), general test conditions, verification requirements at system level, and test methods at subsystem and equipment level (Clause 5) as w ell as informative limits (Annex A).
Associated to this standard is ECSS-E-ST-20-06 (equivalent to EN 16603-20-06) "Spacecraft charging", w hich addresses charging control and risks arising from environmental and vehicle-induced spacecraft charging w hen ECSS-E-ST-20-07 addresses electromagnetic effects of electrostatic discharges.
Annexes A to C of ECSS-E-ST-20 document EMC activities related to ECSS-E-ST-20-07: the EMC Control Plan (Annex A) defines the approach, methods, procedures, resources, and organization, the Electromagnetic Effects Verification Plan (Annex B) defines and specifies the verification processes, analyses and tests, and the Electromagnetic Effects Verification Report (Annex C) document verification results. The EMEVP and the EMEVR are the vehicles for tailoring this standard.

  • Standard
    103 pages
    English language
    sale 10% off
    e-Library read for
    1 day