SIST EN 16603-35-01:2014
(Main)Space engineering - Liquid and electric propulsion for spacecraft
Space engineering - Liquid and electric propulsion for spacecraft
EN 16603-35-01 defines the regulatory aspects applicable to elements and processes for liquid, including cold gas, and electrical propulsion for spacecraft. It specifies the activities to be performed in the engineering of such propulsion systems, their applicability, and defines the requirements for the engineering aspects: functional, interfaces, environmental, design, quality factors, operational and verification. General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.
Raumfahrttechnik - Flüssige und elektrische Antriebe von Raumfahrzeugen
Ingénierie spatiale - Propulsion liquide et électrique pour satellites
La présente Norme définit les aspects réglementaires applicables aux éléments et aux techniques de propulsion liquide, y compris à gaz froid, et électrique pour engins spatiaux. Elle stipule les activités devant être exécutées dans le cadre de l'ingénierie de tels systèmes de propulsion, ainsi que leur applicabilité, et définit les exigences concernant les aspects liés à l'ingénierie : aspects fonctionnels, interfaces, aspects environnementaux, conception, facteurs de qualité, aspects opérationnels et vérification.
Les exigences générales qui s'appliquent à tous les types d'ingénierie de systèmes de propulsion sont définies dans l'ECSS-E-ST-35.
La présente norme peut être adaptée aux caractéristiques et contraintes spécifiques d'un projet spatial, conformément à la norme ECSS-S-ST-00.
Vesoljska tehnika - Pogon za vesoljska plovila
Standard EN 16603-35-01 določa regulatorne vidike, ki veljajo za elemente in postopke za tekočine, vključno s hladnim plinom in električnim pogonom za vesoljska plovila. Določa dejavnosti, ki se izvajajo v tehničnem delu teh pogonskih sistemov, in njihovo uporabnost ter zahteve za tehnične vidike: funkcionalne, vmesniške, okoljske, zasnovne in kakovostne dejavnike, zahteve med delovanjem in verifikacijo. Splošne zahteve, ki veljajo za vse vrste inženiringa pogonskih sistemov, so opredeljene v standardu ECSS-E-ST-35. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.
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2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Vesoljska tehnika - Pogon za vesoljska plovilaRaumfahrttechnik - Flüssige und elektrische Antriebe von RaumfahrzeugenIngénierie spatiale - Propulsion liquide et électrique pour satellitesSpace engineering - Liquid and electric propulsion for spacecraft49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:EN 16603-35-01:2014SIST EN 16603-35-01:2014en,fr,de01-november-2014SIST EN 16603-35-01:2014SLOVENSKI
STANDARDSIST EN 14607-5-1:20051DGRPHãþD
SIST EN 16603-35-01:2014
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-35-01
September 2014 ICS 49.140
Supersedes EN 14607-5-1:2004 English version
Space engineering - Liquid and electric propulsion for spacecraft
Ingénierie spatiale - Propulsion liquide et électrique pour satellites
Raumfahrttechnik - Flüssige und elektrische Antriebe von Raumfahrzeugen This European Standard was approved by CEN on 23 February 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 16603-35-01:2014 E
SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 2 Table of contents Foreword . 5 Introduction . 6 1 Scope . 7 2 Normative references . 8 3 Terms, definitions and abbreviated terms . 9 3.1 Terms from other standards . 9 3.2 Abbreviated terms. 9 4 Liquid propulsion systems for spacecraft . 10 4.1 Overview . 10 4.2 Functional . 10 4.2.1 Mission . 10 4.2.2 Functions . 11 4.3 Constraints . 11 4.3.1 Accelerations . 11 4.3.2 Pressure vessels and pressurized components . 12 4.3.3 Induced and environmental temperatures . 12 4.3.4 Thermal fluxes . 12 4.3.5 Thruster plume effects . 12 4.4 Interfaces . 12 4.5 Design . 13 4.5.1 General . 13 4.5.2 Selection . 14 4.5.3 Sizing . 15 4.5.4 Design development . 16 4.5.5 Contamination . 17 4.5.6 Draining . 17 4.5.7 Risk of explosion . 18 4.5.8 Components guidelines . 18 4.5.9 Filters . 20 SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 3 4.5.10 Pressure vessels . 20 4.5.11 Propellant tanks . 20 4.5.12 Blow-down ratio . 22 4.5.13 Flow calibration . 22 4.5.14 Thrusters . 22 4.5.15 Thrust-vector control (TVC) . 23 4.5.16 Pyrotechnic devices . 24 4.5.17 Mass imbalance . 24 4.5.18 Monitoring and failure detection . 24 4.5.19 Ground support equipment (GSE) . 24 4.6 Verification . 25 4.6.1 General . 25 4.6.2 Verification by analysis . 26 4.6.3 Verification by test . 28 4.6.4 Data exchange for models . 33 4.7 Quality factors . 33 4.7.1 Reliability . 33 4.7.2 Production and manufacturing process . 33 4.8 Operation and disposal . 33 4.8.1 General . 33 4.8.2 Operations on ground . 34 4.8.3 Tank operation . 34 4.8.4 Disposal . 34 4.9 Supporting documents . 35 5 Electric propulsion systems for spacecraft . 36 5.1 Overview . 36 5.2 Functional . 37 5.2.1 Mission . 37 5.2.2 Function . 37 5.2.3 Performance . 37 5.3 Constraints . 38 5.3.1 General . 38 5.3.2 Thermal fluxes . 38 5.3.3 Thruster plume effects . 39 5.3.4 High frequency current loops . 39 5.3.5 Electromagnetic compatibility . 39 5.3.6 Spacecraft charging . 39 SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 4 5.4 Interfaces . 40 5.4.1 Interface with the spacecraft . 40 5.4.2 Interface with the power bus . 40 5.5 Design . 41 5.5.1 General . 41 5.5.2 Selection . 42 5.5.3 Sizing . 43 5.5.4 Design development . 44 5.5.5 Contamination . 44 5.5.6 Propellant protection . 45 5.5.7 Components guidelines . 45 5.5.8 Propellant management assembly . 45 5.5.9 Pressure vessels . 46 5.5.10 Propellant tanks . 47 5.5.11 Blow-down ratio . 47 5.5.12 Thrusters . 47 5.5.13 Thrust-vector control . 50 5.5.14 Power supply, control and processing subsystem . 50 5.5.15 Electrical design . 51 5.5.16 Pyrotechnic devices . 52 5.5.17 Monitoring and failure detection . 52 5.5.18 Ground support equipment (GSE) . 53 5.6 Verification . 53 5.6.1 General . 53 5.6.2 Verification by analysis . 54 5.6.3 Verification by test . 55 5.6.4 Data exchange for models . 57 5.7 Quality factors . 57 5.7.1 Reliability . 57 5.7.2 Production and manufacturing . 57 5.8 Operation and disposal . 57 5.9 Supporting documents . 58 Bibliography . 59 Tables Table 4-1: Component failure modes . 18
SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 5 Foreword This document (EN 16603-35-01:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-35-01:2014) originates from ECSS-E-ST-35-01C. 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 2015, and conflicting national standards shall be withdrawn at the latest by March 2015. 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 supersedes EN 14607-5-1:2004. 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 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, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 6 Introduction The ECSS Propulsion standards structure is as follows. ECSS-E-ST-35 Propulsion general requirements • Standards, covering particular type of propulsion ECSS-E-ST-35-01
Liquid and electric propulsion for spacecrafts ECSS-E-ST-35-02 Solid propulsion for spacecrafts and launchers ECSS-E-ST-35-03 Liquid propulsion for launchers • Standard covering particular propulsion aspects ECSS-E-ST-35-06 Cleanliness requirements for spacecraft propulsion hardware ECSS-E-ST-35-10 Compatibility testing for liquid propulsion systems
SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 7 1 Scope This Standard defines the regulatory aspects applicable to elements and processes for liquid, including cold gas, and electrical propulsion for spacecraft. It specifies the activities to be performed in the engineering of such propulsion systems, their applicability, and defines the requirements for the engineering aspects: functional, interfaces, environmental, design, quality factors, operational and verification. General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 8 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 16601-01 ECSS-S-ST-00-01 ECSS system – Glossary of terms EN 16603-10 ECSS-E-ST-10 Space engineering – System engineering general requirements EN 16603-20 ECSS-E-ST-20 Space engineering – Electrical and electronic EN 16603-20-06 ECSS-E-ST-20-06 Space engineering – Spacecraft changing EN 16603-20-07 ECSS-E-ST-20-07 Space engineering – Electromagnetic compatibility 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 16603-35 ECSS-E-ST-35 Space engineering – Propulsion general requirements EN 16602-30 ECSS-Q-ST-30 Space product assurance – Dependability
SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 9 3 Terms, definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01 and ECSS-E-ST-35 apply. 3.2 Abbreviated terms For the purpose of this Standard, the abbreviated terms from ECSS-ST-00-01 apply. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 10 4 Liquid propulsion systems for spacecraft 4.1 Overview Liquid propulsion systems for spacecraft provide the forces and torques for orbit transfer, orbit maintenance and attitude control. For manoeuvrable spacecraft, capsules and transport vehicles, they provide in addition the forces and torques for rendez-vous and docking. Apart from what is specific for propellant combustion, liquid propulsion criteria are also applicable to cold gas propulsion systems. The present clause 4 covers also the design and use of propulsion ground support equipment (GSE), defined in ECSS-E-ST-70. 4.2 Functional 4.2.1 Mission a. The propulsion system shall conform to the spacecraft mission requirements including: 1. Ground operations NOTE
For example: functional control, testing, propellant, simulant loading and spacecraft transportation. 2. Pre-launch and launch activities NOTE
For example: integration, storage, ageing and transport. 3. In-orbit operations. NOTE
For example: orbit transfer, orbit maintenance and attitude control) and the complete in-orbit life. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 11 4.2.2 Functions a. The propulsion system shall provide the total impulse, minimum impulse bit, thrust levels and torques required by the AOCS. b. The following aspects shall be defined: 1. Thruster firing modes NOTE
For example: steady state, off-modulation, pulse mode. 2. Thrust level and orientation 3. Thrust-vector control 4. Thrust centroid time 5. Minimum impulse bit 6. Impulse reproducibility 7. Total impulse 8. Cycle life 9. Mission life 10. Reliability level 11. Thrust noise 12. Propellant gauging. c. The propulsion system shall fulfil its functions while subjected to the specified external loads during its mission, including: 1. mechanical loads; NOTE
For example: quasi-static loads, vibrations, transportation. 2. thermal loads; 3. electrical loads. 4.3 Constraints 4.3.1 Accelerations a. Limits on acceleration levels, induced or experienced by the propulsion system, shall be specified at spacecraft level. NOTE
This is in order to: • avoid perturbations, e.g. during possible observations or experiments; • protect sensitive equipments; • design adequate tank PMD. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 12 4.3.2 Pressure vessels and pressurized components a. Support structures of pressure vessels and pressurized components shall allow deformations of the vessels due to pressure or temperature changes and cycles to occur without causing stresses that exceed acceptable limits. 4.3.3 Induced and environmental temperatures a. The non-operating and operating temperature limitations of the propulsion system shall be specified. 4.3.4 Thermal fluxes a. Thruster surroundings shall conform to the radiative and conductive heat fluxes rejected by the thrusters. 4.3.5 Thruster plume effects
a. Elements of the spacecraft sensitive to plume effects shall be identified. b. The allowed plume effects on elements identified in clause 4.3.5a shall be specified at spacecraft level. c. The generation of perturbing torques, forces, thermal gradients, contamination and erosion of surfaces, due to plume effects, shall be defined and documented accordingly. d. The plume analysis specified in 4.3.5c shall be reported in conformance with the Plume analysis report DRD in ECSS-E-ST-35. 4.4 Interfaces a. The liquid propulsion system shall conform to its specified spacecraft interfaces, including: 1. Structure NOTE
For example: inserts, tank support structure and vibration levels. 2. Thermal NOTE
For example: conduction, radiation levels, tank, thruster and line thermal control. 3. Power NOTE
For example: valve drivers, pressure transducers, thermistors, heaters and thermocouples. 4. Electromagnetic compatibility 5. Pyrotechnics NOTE
For example: pyrotechnic valves. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 13 6. Mechanisms NOTE
For example: valves, regulators, actuators and actuation system. 7. AOCS, OBDH and TM/TC. NOTE
For example: commanding, handling of data for status and health monitoring and failure detection. b. Interfaces shall be defined: 1. For ground tests and loading activities, with the propulsion GSE. 2. For safety and prelaunch operation with the launcher authorities. 4.5 Design 4.5.1 General 4.5.1.1 Architecture a. The propulsion system architecture shall apply the requirements in ECSS-Q-ST-30. b. The propulsion system architecture shall provide evidence that fail safe, redundancy, reliability and safety requirements are met. 4.5.1.2 Replacement of parts a. For replacement of parts during development, testing and mission life pre-launch activities ECSS-E-ST-35, requirements 4.5.1c, d and e. shall be applied. 4.5.1.3 Water-hammer effect a. A water-hammer effects analysis shall be performed to support the
propulsion system design and ensure proper functioning. b. The analysis specified in 4.5.1.3a shall be reported in conformance with the Propulsion transient analysis report DRD in ECSS-E-ST-35. 4.5.1.4 Piping a. A pipework design analysis shall be performed including non-consumables, cross-coupling, leakage, pressure, eigenfrequencies, water-hammer. b. The consequences in terms of operational restrictions shall be identified. 4.5.1.5 Closed volumes a. The design of the propulsion system shall prevent hazardous pressure increase in closed volumes. b. The need for any pressure relief capability shall be identified and analysed. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 14 4.5.1.6 Pressure vessels and pressurized components a. The design of pressure vessels and pressurized components shall: 1. Apply margins and factors of safety (FOS) for proof, burst and component life cycle. NOTE
See ECSS-E-ST-32-02. 2. Conform to the environmental aspects, including but not limited to: (a) Temperature (b) Vibration (c) Humidity (d) Corrosive environment (e) Vacuum (f) Outgassing (g) Radiation. 4.5.1.7 Multi-tanks a. If a multi-tank layout is used, inadvertent propellant transfer between tanks shall be prevented by design. b. If PMD tanks are being used, the consequences of selecting parallel or series connections shall be analysed. 4.5.1.8 Cycles a. The system and its components shall be designed for the expected number of cycles during the whole mission life, for both on-ground and in-service operation. 4.5.2 Selection 4.5.2.1 Reporting a. The reporting shall be done in the DJF in conformance with ECSS-E-ST-10. 4.5.2.2 General a. The selection shall be based on trade-off analyses of: 1. The propulsion system. NOTE
For example: monopropellant, bipropellant, or cold gas. 2. The operating mode. NOTE
For example: pressure regulated and blow-down. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 15 b. Selected materials, propellants and test fluids shall be compatible for all components.
NOTE
Compatibility includes: • dissolution; • chemical reaction; • erosion; • corrosion. 4.5.2.3 Propellant selection 4.5.2.3.1 General a. The criteria to be used for propellant selection shall include: 1. Mission requirements 2. Resulting layout of the propulsion system 3. Availability of off-the-shelf components 4. Experience 5. Compatibility and contamination 6. Performance. b. The propellant shall be defined and specified including:
1. Chemical composition 2. Purity 3. Cleanliness. 4.5.2.3.2 Propellant for Thruster qualification a. Thruster qualification firing tests shall use the same propellant grade as the one selected for flight. 4.5.3 Sizing a. The sizing process shall begin with a definition of the life phases of each subsystem or component, including at least:
1. Pressure cycles combined with temperature cycles 2. Propellant, pressurant and leakage budgets 3. Establishment of the operational envelope 4. Minimum and maximum electrical supply voltages 5. Interfaces with GSE functions 6. Evolution of the operational conditions. b. The sizing process shall demonstrate margins based on: 1. Safety 2. Reliability requirements established by the customer SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 16 3. Industry and launch authorities, or agencies operational constraints 4. Thruster performance efficiency 5. Plume effects 6. Modelling errors and uncertainties. c. Pressurant, propellant and contaminants budgets
shall include: 1. Their impact on lifetime 2. Variation of performance during lifetime 3. Quantity for deorbiting 4. Residuals. 4.5.4 Design development 4.5.4.1 General a. The development shall allow for an incremental verification at component or block level, if a fully representative functional test (i.e. hot firing and gravity-dependent functions) cannot be performed after the integration of the system components on the spacecraft. b. If the flight version of the system is divided into independent blocks, they should be separated by safety barriers such as pyrovalves, latch valves or burst membranes.
4.5.4.2 Development tests a. Development tests of each block should be defined to represent the conditions foreseen during the operation of the complete system. b. At least the following characteristics of the propellant feed system shall be determined by hydraulic tests: 1. mass flow rate; 2. dynamic and static pressure; 3. temperature; 4. response time. c. The testability at integrated spacecraft level and the ability to return after test to safe and clean conditions shall be demonstrated for each of the system blocks. d. Design and procedures shall be defined according to 4.5.4.2c. SIST EN 16603-35-01:2014
EN 16603-35-01:2014 (E) 17 4.5.5 Contamination 4.5.5.1 External contamination a. The thruster design, layout and orientation should prevent contaminant deposition on elements sensitive to contamination identified in clause 4.3.5a. NOTE
Contaminants deposition on sensitive elements, such as solar panels, star trackers, and optics, depends on the propellants used, the thruster characteristics, the layout of the propulsion system, the thruster orientation and the thruster duty cycle. b. The potential hazard of contamination and the expected level of contamination due to thruster exhaust shall be included in the plume analysis. NOTE
See clause 4.3.5c. 4.5.5.2 Internal contamination
a. The propulsion system shall be designed to avoid the effects of internal contaminants, including propellant vapours, by: 1. Preventing intrusion, internal generation and circulation of contaminants. 2. Preventing or controlling accumulation of contaminants throughout the various parts of the system. 3. Preventing accumulation of contaminants during the various steps of production, verification and operation of the system. NOTE 1 The presence of contaminants inside the propulsion system can lead to the loss of performance of some components or even to catastrophic failures. NOTE 2 For example, propellant vapours can be considered as contaminants in a pressurisation system. b. The expected maximum level of contaminants inside the propulsion system shall be specified. c. The propulsion system design shall conform to the expected maximum level of contaminants. 4.5.6 Draining a. The system design shall allow for on-g
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