SIST EN 16602-70-06:2015

2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Zagotavljanje varnih proizvodov v vesoljski tehniki - Preskušanje delcev in UV sevanja za vesoljske materialeRaumfahrtproduktsicherung - Teilchen- und UV-Strahlungstests für RaumflugmaterialienAssurance produit des projets spatiaux - Essais d'irradiation aux particules et aux ultraviolets pour matériaux d'un projet spatialSpace product assurance - Particle and UV radiation testing for space materials49.140Vesoljski sistemi in operacijeSpace systems and operations49.025.01Materiali za letalsko in vesoljsko gradnjo na splošnoMaterials for aerospace construction in general17.240Merjenje sevanjaRadiation measurementsICS:Ta slovenski standard je istoveten z:EN 16602-70-06:2014SIST EN 16602-70-06:2015en,fr,de01-januar-2015SIST EN 16602-70-06:2015SLOVENSKI
STANDARD
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16602-70-06
October 2014 ICS 49.140
English version
Space product assurance - Particle and UV radiation testing for space materials
Assurance produit des projets spatiaux - Essais d'irradiation aux particules et aux ultraviolets pour matériaux d'un projet spatial
Raumfahrtproduktsicherung - Teilchen- und UV-Strahlungstests für Raumflugmaterialien This European Standard was approved by CEN on 20 March 2014.
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, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.
CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels © 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved worldwide for CEN national Members and for CENELEC Members. Ref. No. EN 16602-70-06:2014 E SIST EN 16602-70-06:2015

Figures Figure 4-1: Test process overview . 10 Figure 4-2: Degrading factors specification. 11
The environments covered are electromagnetic radiation and charged particles. This Standard defines the procedures for electromagnetic radiation and charged particles testing of spacecraft materials.
These materials include for instance thermal control materials, windows, coatings, and structural materials. The procedures include simulation of the environment and the properties to be verified. This Standard excludes electronic components. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
EN reference Reference in text Title EN 16601-00-01 ECSS-S-ST-00-01 ECSS system – Glossary of terms EN 16603-10-04 ECSS-E-ST-10-04 Space engineering – Space environment EN 16602-20 ECSS-Q-ST-20 Space product assurance – Quality assurance EN 16602-20-07 ECSS-Q-ST-20-07 Space product assurance – Quality assurance for test centres EN 16602-10-09 ECSS-Q-ST-10-09 Space product assurance – Nonconformance control system EN 16602-70-02 ECSS-Q-ST-70-02 Space product assurance – Thermal vacuum outgassing tests for the screening of space materials EN 16602-70-09 ECSS-Q-ST-70-09 Space product assurance – Measurements of thermo-optical properties of thermal control materials
ISO 15856:2003 Space systems – Space environment – Simulation guidelines for radiation exposure of non-metallic materials
ASTM-E-490
Standard Solar Constant and Zero Air Mass Solar Spectral Irradiance Tables SIST EN 16602-70-06:2015

The absorbed dose D is expressed in Gy (1 Gy = 1 j/kg = 100 rad). 3.2.2 acceleration factor
ratio of the intensity of a degrading factor applied to a material at the laboratory during a space simulation versus the intensity of the same degrading factor in space NOTE
It applies to any degrading factor. 3.2.3 bremsstrahlung high-energy electromagnetic radiation in the X-ray energy range emitted by charged particles slowing down by scattering off atomic nuclei NOTE 1 The primary particle is ultimately absorbed while the bremsstrahlung can be highly penetrating. In space, the most common source of bremsstrahlung is electron scattering. NOTE 2 Its energy is continuously distributed down from the energy of the incident particle. 3.2.4 contaminant unwanted molecular or particulate matter (including microbiological matter) on the surface or in the environment of interest, that can affect or degrade the relevant performance or life time SIST EN 16602-70-06:2015

For example: UV, charged particles. 3.2.6 dose profile distribution of the absorbed dose through the depth of the material 3.2.7 ex-situ measurement measurement performed outside the testing facility NOTE 1 Generally it means that these measurements are performed in air at ambient temperature.
NOTE 2 If specific conditions are applied ex-situ, they are described in a corresponding procedure. 3.2.8 fluence time-integration of the flux 3.2.9 flux amount of radiation crossing a surface per unit of time NOTE
It is often expressed in “integral form” as particles per unit area per unit time (e.g. electrons cm-2 s-1) above a certain threshold energy. 3.2.10 in-situ measurement measurement performed inside a chamber (in vacuum or pressurized) 3.2.11 induced space environment environmental factors that result from interactions of the space system with the natural space environment 3.2.12 irradiance quotient of the radiant flux incident on an element of the surface containing the point, by the area of that element NOTE
See also ISO 15856:2003 3.2.13 ionizing radiation form of radiation that has sufficient energy to remove electrons from atoms to produce ions NOTE
It can consist of high energy particles (electrons, protons or alpha particles) or short wavelength electromagnetic radiation (ultraviolet, X-rays and gamma rays). 3.2.14 mean free path average distance that a subatomic particle, ion, atom, or molecule travels between successive collisions with ions, atoms, or molecules SIST EN 16602-70-06:2015

This includes radiation, vacuum, residual atmosphere, and meteoroids. 3.2.16 near ultraviolet (NUV) radiation solar electromagnetic radiation with the wavelength in the range from 200 nm up to 400 nm 3.2.17 reciprocity law statement that the observed property change depends only on the fluence and is independent of the flux 3.2.18 synchrotron radiation continuous electromagnetic radiation created by the acceleration of relativistic charged particles NOTE
For example: this radiation can be generated in a synchrotron or storage ring. 3.2.19 synergism joint action of two or more stimuli whose combination induce a different effect (qualitative and quantitative) than the result of adding the effects of each stimulus taken separately 3.2.20 vacuum ultraviolet (VUV) radiation solar electromagnetic radiations in the wavelength range from 10 nm up to 200 nm NOTE
Also called “Far UV”. 3.3 Abbreviated terms and symbols For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01 and the following apply: Abbreviation Meaning ESH equivalent Sun hour FUV far ultraviolet QCM quartz crystal monitor NUV near ultraviolet UV ultraviolet VUV vacuum ultraviolet
low wavelength limit
high wavelength limit
Such approach is performed following the steps as described in Figure 4-1. Specifying test Preparing and performing testQuality RequirementsRecording and reporting
test Work Proposal for Radiation Test (including test specification and procedure (Annex B) Test results (including identified deviations, if any)Report for Radiation Test (Annex C) Request for Radiation Test
(Annex A) Go/NO Go from CustomerNCR (if any identified deviation) Figure 4-1: Test process overview
Clause 5.1 provides the specification of the radiation test related to given space simulation test requirements is based on the rationale of degrading factors definition, as described in Figure 4-2. SIST EN 16602-70-06:2015

5.1.1 General provision a. The customer shall provide a request for radiation test in conformance with the DRD in Annex A. b. ECSS-Q-ST-20 shall be made applicable in the request for a radiation test. c. ECSS-Q-ST-10-09 shall be made applicable in the request for a radiation test. d. The test centre shall comply with the safety and security requirements in ECSS-Q-ST-20-07. NOTE
For example, for hazard and health (safety) and for access control (security). e. The supplier shall provide a radiation test specification and procedure (Work proposal) in conformance with the DRD in Annex B. 5.1.2 Methodology for laboratory degrading factors definition
5.1.2.1 Specification of the general spacecraft environment
a. The customer shall identify, the spacecraft space environment, using models as defined in ECSS-E-ST-10-04. NOTE 1 The spacecraft space environment is natural and induced environments encountered during its specific missions. NOTE 2 The natural space environment of a given item is that set of environmental conditions defined by the external physical world for the given mission, e.g. residual atmosphere, meteoroids and electromagnetic and particle radiation. NOTE 3 The induced space environment is that set of environmental conditions created or modified by the presence or operation of the item and its mission or other manmade items, e.g. SIST EN 16602-70-06:2015

a. While determining the natural and induced space environment that a material encounters, the customer shall identify the location of this material on the spacecraft. b. The supplier shall identify the parameters that can influence the “seen” fluence. NOTE 1 These parameters can be shielding, view factors or mean sunlight incidence angle. NOTE 2 For example: During one year (8760 hours) the solar irradiation is:
• on a Geostationary cylindrical satellite whose axis is parallel to earth revolution axis, 1112 ESH on the N/S faces and about 2500 ESH on the periphery,
• on the LEO ISS orbit, 2500 ESH on Ram and anti Ram, 250 ESH on nadir, 2200 ESH on zenith, and 1500 ESH on the side faces. 5.1.2.3 Specification of the materials properties to be measured
a. The customer shall identify (in the request for radiation test), the materials properties to be investigated. NOTE 1 The most common examples of properties used in space technology are:
• optical (transmission, absorption of windows), • thermo-optical (spectral and solar absorptance, infrared emissivity),
• electrical properties (e.g. conductivity, charging). NOTE 2 It is often impossible to measure additional physical properties at the end of a test, if these are not included in the initial test definition. The proposed test conditions are not necessarily relevant for these additional properties. b. When thermo-optical properties are identified for measurement, ECSS-Q-ST-70-09 shall apply. 5.1.2.4 Specification of the laboratory degrading factors
a. The supplier shall identify (in the radiation test procedure proposal), the ground factors to be simulated by crossing or trading off the information given by the space environment, the specific material environment.
...