SIST EN 16603-35-03:2014
(Main)Space engineering - Liquid propulsion for launchers
Space engineering - Liquid propulsion for launchers
General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. For Liquid propulsion for launchers activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-03 are applied together. This Standard defines the specific regulatory aspects that apply to the elements and processes of liquid propulsion for launch vehicles. It specifies the activities to be performed in the engineering of these propulsion systems and their applicability. It defines the requirements for the engineering aspects such as functional, physical, environmental, quality factors, operational and verification. Other forms of propulsion (e.g. nuclear, nuclear-electric, solar-thermal and hybrid propulsion) are not presently covered in this issue of the Standard. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
Raumfahrttechnik - Flüssigantriebe für Trägerraketen
Ingénierie spatiale - Propulsion liquide pour lanceurs
Vesoljska tehnika - Tekoča pogonska goriva za lansirnike
Splošne zahteve, ki veljajo za vse vrste inženiringa pogonskih sistemov, so opredeljene v standardu ECSS-E-ST-35. Za dejavnosti, povezane s tekočimi pogonskimi gorivi v okviru vesoljskega projekta, skupaj veljata standarda ECSS-E-ST-35 in ECSS-E-ST-35-02. Ta standard opredeljuje posebne regulatorne vidike, ki se nanašajo na elemente in postopke za tekoča pogonska goriva za lansirnike. Določa dejavnosti, ki se izvajajo v tehničnem delu teh pogonskih sistemov in njihovo uporabnost. Določa zahteve za inženirske vidike, kot so funkcionalni, fizikalni, okoljski, kakovostni dejavniki, zahteve med delovanjem in verifikacijo. Druge oblike pogonov (npr. jedrski, jedrsko-električni, solarno-termalni in hibridni pogon) trenutno niso zajeti v tej izdaji standarda. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.
General Information
Standards Content (Sample)
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Raumfahrttechnik - Flüssigantriebe für TrägerraketenIngénierie spatiale - Propulsion liquide pour lanceursSpace engineering - Liquid propulsion for launchers49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:EN 16603-35-03:2014SIST EN 16603-35-03:2014en,fr,de01-november-2014SIST EN 16603-35-03:2014SLOVENSKI
STANDARD
SIST EN 16603-35-03:2014
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-35-03
September 2014 ICS 49.140
English version
Space engineering - Liquid propulsion for launchers
Ingénierie spatiale - Propulsion liquide pour lanceurs
Raumfahrttechnik - Flüssigantriebe für Trägerraketen 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 16603-35-03:2014 E SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 2 Table of contents Foreword . 4 Introduction . 5 1 Scope . 6 2 Normative references . 7 3 Terms, definitions and abbreviated terms . 8 3.1 Terms from other standards . 8 3.2 Abbreviated terms. 8 4 Overview of a liquid propulsion system . 9 5 Functional . 11 5.1 Overview . 11 5.2 Mission . 11 5.3 Functions . 11 6 Constraints . 12 6.1 Acceleration . 12 6.2 Geometrical constraints . 12 6.3 Electrical constraints . 12 6.4 Safety . 12 7 Development . 13 7.1 Overview . 13 7.2 Development logic . 13 8 Interfaces . 16 8.1 Overview . 16 8.2 General . 16 9 Design. 17 9.1 General . 17 9.2 Specification . 17 9.3 Propulsion system selection . 17 SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 3 9.3.1 Overview . 17 9.3.2 System selection . 17 9.3.3 Propellant selection . 18 9.3.4 Engine selection . 18 9.3.5 Selection of the TVC system . 18 9.4 Propulsive system detailed design . 19 9.4.1 Overview . 19 9.4.2 General . 19 9.4.3 Filling and draining system . 19 9.4.4 Propellant tanks and management . 20 9.4.5 Propellant feed system . 23 9.5 Liquid engines . 24 9.5.1 General . 24 9.5.2 Performance . 25 9.5.3 Functional system analysis . 25 9.5.4 Thrust chamber assembly (TCA) . 29 9.5.5 Gas generator and pre-burner . 36 9.5.6 Turbomachinery subsystem . 36 9.5.7 Control and monitoring systems . 38 9.5.8 Auxiliary functions supplied by the stage . 40 9.5.9 Components. 41 9.6 Mechanical design . 44 10 Ground support equipment . 48 11 Materials . 49 12 Verification . 50 13 Production and manufacturing . 51 14 In-service . 52 14.1 General . 52 14.2 Operation . 52 15 Deliverables . 53 Bibliography . 54
SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 4 Foreword This document (EN 16603-35-03:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-35-03:2014) originates from ECSS-E-ST-35-03C. 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 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 16603-35-03:2014
EN 16603-35-03:2014 (E) 5 Introduction The requirements in this Standard ECSS-E-ST-35-03 (and in the 3 other space propulsion standards ECSS-E-ST-35, ECSS-E-ST-35-01 and ECSS-E-ST-35-02) are organized with a typical structure as follows: • functional; • constraints; • development; • interfaces; • design; • GSE; • materials; • verification; • production and manufacturing; • in-service (operation and disposal); • deliverables.
This standard forms parts of ECSS-E-ST-35 series which has the following structure; • ECSS-E-ST-35 Propulsion general requirements • 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 • ECSS-E-ST-35-06 Cleanliness requirements for spacecraft propulsion components, subsystems, and systems • ECSS-E-ST-35-10 Compatibility testing for liquid propulsion components, subsystems, and systems ECSS-E-ST-35 contains all the normative references, terms, definitions, abbreviated terms, symbols and DRD that are applicable for ECSS-E-ST-35, ECSS-E-ST-35-01, ECSS-E-ST-35-02 and ECSS-E-ST-35-03. In the use of this standard, the term ‘propulsion system’ is intended to be read and interpreted only and specifically for ‘liquid prolusion system’. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 6 1 Scope General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. For Liquid propulsion for launchers activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-03 are applied together. This Standard defines the specific regulatory aspects that apply to the elements and processes of liquid propulsion for launch vehicles. It specifies the activities to be performed in the engineering of these propulsion systems and their applicability. It defines the requirements for the engineering aspects such as functional, physical, environmental, quality factors, operational and verification. Other forms of propulsion (e.g. nuclear, nuclear-electric, solar-thermal and hybrid propulsion) are not presently covered in this issue of the Standard. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 7 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 ECSS-E-ST-10 Space engineering - System engineering general requirements EN 16603-10-02 ECSS-E-ST-10-02 Space engineering - Verification EN 16603-10-06 ECSS-E-ST-10-06 Space engineering - Technical requirements specification EN 16603-32 ECSS-E-ST-32 Space engineering - Structural general requirements EN 16603-32-02 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 16603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for spaceflight hardware EN 16603-35 ECSS-E-ST-35 Space engineering - Propulsion general requirements EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts and processes
ISO 15389:2001 Space systems - Flight-to-ground umbilicals
SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 8 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-S-ST-00-01, ECSS-E-ST-35 and the following apply:
Abbreviation Meaning LPS liquid propulsion system
SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 9 4 Overview of a liquid propulsion system • Main functions of a liquid propulsion system are: To provide thrust To provide thrust vector control To provide multiple burn capability if necessary To supply pressurized gas for auxiliary functions (e.g. roll control, stage orientation ) To supply fluid for pneumatic control (e.g. Helium) To provide thrust for propellant settling To provide information concerning its status (e.g. measurement)
• The liquid propulsion system generally consists in: the engine the tank the feed system the pressurisation system the command system the TVC auxiliary systems such as the anti-POGO device, roll control system
• The typical life of a liquid propulsion system is the following: Manufacturing and assembly Acceptance test (if any) Storage and transport Launcher integration Pre-launch activities (e.g. flushing, leak tightness checks) Tanks filling Main stage Chill down (for cryogenic liquid propulsion system) Launch chronology (including launch-abort activities) SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 10 Lift-off Chill-down (for cryogenic liquid propulsion upper stages) Boost phases Stage separation Ballistic phase Passivation De-orbiting, reaching a graveyard orbit, or both NOTE
The way how to write the technical specification is given in ECSS-E-ST-10-06. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 11 5 Functional 5.1 Overview The general functional specification coming from mission optimisation at system level provides values for: • Thrust • Isp • Burning time
The additional functional requirements are: • thrust level versus time (throttling) • propellant budget management (e.g. mixture ratio variation) • TVC (e.g. maximum angle, acceleration, response time) • start-up and shutdown transient requirements (e.g. duration, impulse scatter) • auxiliary power to be delivered to the launcher (e.g. electrical and fluids) • re-startability • propellant depletion 5.2 Mission a. ECSS-E-ST-35 clause 4.2 shall apply. 5.3 Functions a. The technical specification shall provide the values of thrust, Isp and burning time with their deviations. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 12 6 Constraints 6.1 Acceleration a. Accelerations in the axial and lateral directions, assessed at launch vehicle level, shall be specified as an input for the propulsion system. NOTE
The acceleration has an impact on the: • functioning of the vortex suppression devices in the tank outlets; • pressure at the pump inlets; • flow pattern in the tank; • mechanical loads. 6.2 Geometrical constraints a. The dimensioning of the liquid propulsion system and its components shall conform to the overall launch vehicle dimensions, interfaces between stages, ground infrastructure and requirements for transportation. 6.3 Electrical constraints a. The design of the prop system shall be such that the electrical continuity is ensured. 6.4 Safety a. The design of the liquid propulsion system shall conform to the safety requirements of the launch system. NOTE
For Example, ground safety requirements, flight safety requirements. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 13 7 Development 7.1 Overview The phases of development for a liquid propulsion system are as follows: • definition of system and subsystem requirements conforming to mission requirements • establishment of the general concepts • trade-off of various concepts • preliminary design • risk analysis of the preliminary design and trade-off of various options • detailed design and definition • manufacturing and assembly of components, subsystems. • integration of subsystem and system • testing of: components, subsystems, engines, and system (functional stage). • selection of the design to be qualified • qualification process • review of first article 7.2 Development logic a. The development logic shall include a requirement verification plan in conformance with ECSS-E-ST-10-02 ‘verification plan’. NOTE
Example of verification methods are analyses, tests. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 14 b. The development logic shall be structured into phases with a goal assigned to each phase. c. Mathematical models shall be implemented during the preliminary design phase and used for system trade-off analysis. NOTE 1 See clause 9.3. NOTE 2
Preliminary design phase is Phase B of ECSS-M-ST-10. d. Mathematical models shall be updated using component and subsystem results at milestones agreed by the customer. e. Mathematical models shall be validated using test results. f. Mathematical models shall be used to determine the design margins. g. The development logic shall list the activities that are submitted to cross-check. NOTE
See ECSS-E-ST-35 clause 4.8.1. h. The sequence of development activities shall include components and subsystem tests prior to system tests. i. The development logic shall mention the difficulties and critical activities of the development. NOTE
In particular major development critical path. j. The development logic shall include risk management activities for project and technical risks. k. The development activities shall include verification that manufacturing and control processes lead to products that satisfy specified product-to-product variation limit. l. Lessons learned from previous programs shall be introduced in the design development plan. m. The critical technologies, manufacturing and control processes shall be listed and their qualification process described. NOTE
See ECSS-Q-ST-20. n. Liquid propulsion system verification shall be obtained by testing the liquid propulsion system in conditions representative of flight. NOTE
Following the typical approach “Test as you fly”. o. Through the measurement plan of the qualification flight the LPS qualification shall be checked by post flight analysis. p. The development test plan shall include limit testing and failure cases. q. At the end of the development, the testing of the integrated system in its final configuration, including the electrical system, shall include tests with representative interfaces. NOTE
For example, typical interfaces are control computer, electrical interface, flight instrumentation. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 15 r. Phase by phase analyses of the life cycle of the liquid propulsion system shall be performed in relationship with the launch vehicle system in support of the failure mode analysis and the mechanical and thermal load case selection. s. A matrix of configuration of engine hardware versus subsystem hardware shall be produced. t. An integrated schedule for subsystem hardware deliveries, engine integration, engine testing for all development and qualification hardware shall be produced. u. The output of all the requirement of clause 7.2 shall be detailed in the SEP (System Engineering Plan) as defined in the ECSS-E-ST-10 Annex D DRD. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 16 8 Interfaces 8.1 Overview The interfaces of the liquid propulsion system are generally the following: • Stage components (e.g. skirt, stage thermal protection) • Other stages of the launch vehicle • Launch vehicle on-board computer • Electrical supply system • Interfaces with GSE (including the flushing, venting, filling and draining systems) • Transport 8.2 General a. For interface requirements ECSS-E-ST-35 clause 4.4 shall apply. b. The environmental conditions imposed to the liquid propulsion system shall be specified. NOTE
For example, temperature, humidity, salt content of the atmosphere, inter stage conditioning). c. The loads induced by the liquid propulsion system acting on the launch vehicle and the payload shall be identified, evaluated and reported in the design definition file as defined in the ECSS-E-ST-10 Annex G DRD. NOTE
Examples of these loads are chugging, side loads, vibrations, blast wave, thermal radiation. d. Interface requirements shall be derived from the extreme operating envelope. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 17 9 Design 9.1 General a. The statement of work shall provide a ranking and weights of the design criteria. NOTE
Criteria are for example performance, reliability and development cost and recurring cost. b. The design resulting from the optimisation of the above criteria 9.1a shall be provided and justified. 9.2 Specification a. The specification of a liquid propulsion system or subsystem shall be in conformance with ECSS-E-ST-10-06. 9.3 Propulsion system selection 9.3.1 Overview The mixture ratio is derived from a system optimization analysis, taking into account the characteristics of the envisaged liquid propulsion system and rocket engines. The mixture ratio and the total amount of propellants, is the determining factor for the sizing of the tanks, together with the pressure and temperature. 9.3.2 System selection a. For the selection of the liquid propulsion system architecture, a trade-off analysis shall be performed using the following parameters: 1. type of propellants; 2. engine architecture and thermodynamic cycle; 3. propellant mixture ratio; 4. propellant storage; 5. pressurization and feed system; 6. any additional parameters specified by the customer. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 18 9.3.3 Propellant selection a. For the selection of the propellant, a trade-off analysis shall be performed using the following parameters: 1. conformance to the launch vehicle system requirements; 2. performance; 3. availability; 4. handling; 5. storage; 6. safety; 7. cost; 8. impact on the environment; 9. any additional parameters specified by the customer. 9.3.4 Engine selection a. For the selection of the engine, a trade-off analysis shall be performed using the following parameters: 1. global stage performance (e.g. Isp, mass budget); 2. development costs; 3. recurring cost; 4. industrial infra structure; 5. test infra structure; 6. reliability; 7. strength; 8. architecture and overall dimensions; 9. the technical readiness level of the technologies; 10. any additional parameters specified by the customer. 9.3.5 Selection of the TVC system a. For the selection of the TVC, a trade-off analysis shall be performed using the following parameters: 1. global mass; 2. strength; 3. performance losses; 4. power consumption; 5. costs; 6. reliability; SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 19 7. control loop stability; 8. geometrical constraints; 9. any additional parameters specified by the customer. 9.4 Propulsive system detailed design 9.4.1 Overview The propulsive system is the part of the liquid propulsion system that deals with the: • filling and draining system; • feeding system from the tank to the engine inlets; • pressurisation system; • functional aspect of the tanks (e.g. propellant budget, propellant management). The function of the propulsive system is to deliver the propellants to the engine in the specified thermodynamic conditions (e.g. aggregation state, pressure and temperature) and specified flow conditions (e.g. vorticity, and velocity distribution). 9.4.2 General a. At liquid propulsion system level, functional and mechanical models shall be established and used to derive propulsive system components specifications and engine inlet conditions. b. Propulsive system components shall provide inputs to the functional and mechanical models at various steps of the development. c. The liquid propulsion system shall allocate reliability objective for each propulsive system component. d. The liquid propulsion system test plan and instrumentation plan shall be established such that it can be demonstrated that the test objectives of propulsive system components are reached. e. The liquid propulsion system shall assign pollution objective for each propulsive system component, in terms of distribution of size and numbers of incoming and exiting particles. 9.4.3 Filling and draining system 9.4.3.1 Filling and draining system on ground a. The filling and draining subsystems shall conform to ISO 15389:2001(E) subclauses 4.4 to 4.7, and subclauses 4.9 and 4.20. SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 20 b. For cryogenic propellants, if the nominal draining lines between the liquid propulsion system and the GSE are disconnected before lift-off, the liquid propulsion system shall be provided with emergency draining possibilities that enable draining after a launch abort. NOTE
The filling subsystem can be combined with the draining functions. 9.4.3.2 Draining system in flight (passivation and degassing) a. In-flight draining shall not create conditions that can lead to loss of performance of the launch vehicle. b. If in-flight draining cannot be performed through the flow paths for the normal operation of the propulsion system, specific lines or valves shall be incorporated in the liquid propulsion system to enable in-flight draining. 9.4.3.3 Flushing, purging and venting a. The subsystems or components of the liquid propulsion system for which flushing, purging or venting is performed during ground tests, launch activities (including launch-abort) and flight, shall be identified. b. The liquid propulsion system shall provide valves and lines to flush, purge or vent the subsystems or components identified in 9.4.3.3a. c. On ground, the flushed and purged fluids shall be collected. d. The flushing and purging systems shall neither create hazards to personnel nor harm the environment. e. Provisions shall be taken to ensure that vented fluids do not create hazards. NOTE
For example, burn-off of vented hydrogen. f. Flushing, purging and venting in flight shall not create unwanted propulsive effects. NOTE
For example, non-propulsive venting. 9.4.4 Propellant tanks and management 9.4.4.1 General a. the tank volume shall be designed using at least the following: 1. The amount of propellant to be used during nominal propulsion operations; 2. the amount of propellant provisions covering the liquid propulsion system and launch vehicle deviations; 3. losses and ejected propellants; 4. the amount of unusable propellant; 5. the ullage volume; SIST EN 16603-35-03:2014
EN 16603-35-03:2014 (E) 21 6. equipment and lines within the tank. b. The tank volume shall be determined at the extreme temperature and pressure ranges. c. The propellant loaded mass shall be measured with the accuracy requested by TS. d. The tank shall be protected against over pressurisation. 9.4.4.2 Tank pressure and temperature and pressurisation system 9.4.4.2.1 General a. The management of the tank pressure shall be such that the engine inlet thermodynamic conditions comply with the engine requirements for all phases of the mission. b. The tank pressure analysis shall consider during all phases of t
...
Questions, Comments and Discussion
Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.