EN 16603-35-02:2014
(Main)Space engineering - Solid propulsion for spacecrafts and launchers
Space engineering - Solid propulsion for spacecrafts and launchers
General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. For solid propulsion activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-02 are applied together.
This Standard defines the regulatory aspects that apply to the elements and processes of solid propulsion for launch vehicles and spacecraft. 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.
NOTE 1 Some solid propulsion systems use hot gas valves, for thrust or pressure modulation. The requirements applicable to these systems are not covered by the present document.
NOTE 2 For SRM with TVC, only moveable nozzle with flexseal are addressed.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
Raumfahrttechnik - Feststoffantriebe für Raumfahrzeuge und Trägerraketen
Ingénierie spatiale - Propulsion solide pour satellites et lanceurs
Vesoljska tehnika - Trdna pogonska goriva za vesoljska plovila in lansirnike
Splošne zahteve, ki veljajo za vse vrste inženiringa pogonskih sistemov, so opredeljene v standardu ECSS-E-ST-35. Za dejavnosti, povezane s trdnimi pogonskimi gorivi v okviru vesoljskega projekta, skupaj veljata standarda ECSS-E-ST-35 in ECSS-E-ST-35-02. Ta standard opredeljuje regulatorne vidike, ki se nanašajo na elemente in postopke za trdna pogonska goriva za vesoljska plovila in lansirnike. Določa dejavnosti, ki se izvajajo v tehničnem delu teh pogonskih sistemov in njihovo uporabnost. Določa zahteve za tehnične vidike, kot so funkcionalni, fizikalni, okoljski, kakovostni dejavniki, zahteve med delovanjem in verifikacijo.
General Information
- Status
- Published
- Publication Date
- 09-Sep-2014
- Withdrawal Date
- 30-Mar-2015
- Technical Committee
- CEN/CLC/TC 5 - Space
- Drafting Committee
- CEN/CLC/TC 5 - Space
- Current Stage
- 9060 - Closure of 2 Year Review Enquiry - Review Enquiry
- Start Date
- 03-Mar-2020
- Completion Date
- 03-Mar-2020
Relations
- Effective Date
- 28-Jan-2026
- Effective Date
- 28-Jan-2026
Overview
EN 16603-35-02:2014 (Space engineering - Solid propulsion for spacecrafts and launchers) is a European standard derived from ECSS guidance that defines regulatory and engineering requirements for solid propulsion used in launch vehicles and spacecraft. Applied together with ECSS‑E‑ST‑35, it covers the lifecycle activities for solid rocket motors (SRMs) and solid propulsion subsystems, including design, verification, production, in‑service operations and required deliverables. The standard is intended to be tailored to specific project constraints in conformance with ECSS‑S‑ST‑00.
Key topics and technical requirements
- Scope & applicability: Regulatory aspects and engineering activities for solid propulsion systems (large and small SRMs), noting limits (e.g., hot gas valve modulation not covered; SRM TVC limited to moveable nozzles with flexseal).
- Functional requirements: Mission-oriented thrust profile, total impulse, ignition/tail‑off behavior, end‑of‑flight mass and thrust orientation (fixed or with thrust vector control).
- Constraints: Dynamic phenomena (pressure/thrust oscillations), external life‑cycle loads (mechanical, thermal, radiation, humidity), acoustic noise, pollution control (e.g., HCl emissions considerations), ejected parts characterization, and safety per ECSS‑Q‑ST‑40.
- Interfaces & GSE: Mechanical, thermal, electrical and environmental interface definition with launcher/spacecraft and requirements for ground support equipment (GSE).
- Design & materials: Propulsion selection, motor components, insulation/abrasion considerations and material safety requirements.
- Verification & testing: Verification by analysis and by test (qualification and acceptance test regimes), mission-dependent verification matrices and verification deliverables.
- Deliverables: Defined reports and data packages such as the Dynamic Analysis Report (Annex A DRD) and Material Safety Data (Annex B DRD).
Practical applications
- Use EN 16603-35-02 to develop and qualify solid rocket motors, stage motors, separation and braking thrusters, and related components for launchers and spacecraft.
- Guide test planning (qualification/acceptance), safety cases, pollution mitigation strategies, and interface control documents between propulsion suppliers and system integrators.
- Inform GSE design, manufacturing process controls, and in‑service operational procedures for one‑shot solid propulsion hardware.
Who should use this standard
- Propulsion systems engineers, SRM designers and suppliers
- Spacecraft and launcher system engineers and integrators
- Test laboratories, AIT (assembly, integration, testing) teams and GSE designers
- Safety, quality assurance and compliance managers at space agencies and prime contractors
Related standards
- ECSS‑E‑ST‑35 (Propulsion general requirements)
- ECSS‑E‑ST‑35‑01 / 35‑03 (liquid/electric and launcher liquid propulsion)
- ECSS‑Q‑ST‑40 (Safety)
- ECSS‑S‑ST‑00 (Project tailoring) and other ECSS structural and materials standards
Keywords: EN 16603-35-02, solid propulsion, solid rocket motor (SRM), space engineering standards, propulsion systems engineering, thrust vector control (TVC), verification testing, ground support equipment (GSE), ECSS.
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Frequently Asked Questions
EN 16603-35-02:2014 is a standard published by the European Committee for Standardization (CEN). Its full title is "Space engineering - Solid propulsion for spacecrafts and launchers". This standard covers: General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. For solid propulsion activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-02 are applied together. This Standard defines the regulatory aspects that apply to the elements and processes of solid propulsion for launch vehicles and spacecraft. 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. NOTE 1 Some solid propulsion systems use hot gas valves, for thrust or pressure modulation. The requirements applicable to these systems are not covered by the present document. NOTE 2 For SRM with TVC, only moveable nozzle with flexseal are addressed. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
General requirements applying to all type of Propulsion Systems Engineering are defined in ECSS-E-ST-35. For solid propulsion activities within a space project the standards ECSS-E-ST-35 and ECSS-E-ST-35-02 are applied together. This Standard defines the regulatory aspects that apply to the elements and processes of solid propulsion for launch vehicles and spacecraft. 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. NOTE 1 Some solid propulsion systems use hot gas valves, for thrust or pressure modulation. The requirements applicable to these systems are not covered by the present document. NOTE 2 For SRM with TVC, only moveable nozzle with flexseal are addressed. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
EN 16603-35-02:2014 is classified under the following ICS (International Classification for Standards) categories: 49.140 - Space systems and operations. The ICS classification helps identify the subject area and facilitates finding related standards.
EN 16603-35-02:2014 has the following relationships with other standards: It is inter standard links to EN ISO 21225-1:2018, EN ISO 21225-2:2018. Understanding these relationships helps ensure you are using the most current and applicable version of the standard.
EN 16603-35-02:2014 is associated with the following European legislation: Standardization Mandates: M/496. When a standard is cited in the Official Journal of the European Union, products manufactured in conformity with it benefit from a presumption of conformity with the essential requirements of the corresponding EU directive or regulation.
EN 16603-35-02:2014 is available in PDF format for immediate download after purchase. The document can be added to your cart and obtained through the secure checkout process. Digital delivery ensures instant access to the complete standard document.
Standards Content (Sample)
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Vesoljska tehnika - Trdna pogonska goriva za vesoljska plovila in lansirnikeRaumfahrttechnik - Feststoffantriebe für Raumfahrzeuge und TrägerraketenIngénierie spatiale - Propulsion solide pour satellites et lanceursSpace engineering - Solid propulsion for spacecrafts and launchers49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:EN 16603-35-02:2014SIST EN 16603-35-02:2014en,fr,de01-november-2014SIST EN 16603-35-02:2014SLOVENSKI
STANDARD
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-35-02
September 2014 ICS 49.140
English version
Space engineering - Solid propulsion for spacecrafts and launchers
Ingénierie spatiale - Propulsion solide pour satellites et lanceurs
Raumfahrttechnik - Feststoffantriebe für Raumfahrzeuge und 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 16603-35-02:2014 E SIST EN 16603-35-02:2014
(AR-MSDS) - DRD . 32 Bibliography . 35
Tables Table 4-1: Coefficient values . 18 Table 4-2: Test for qualification of solid propulsion systems, subsystems and components . 22 Table 4-3: Examples of mission dependent verification tests for qualification . 24 Table 4-4: Test for acceptance of solid propulsion systems, subsystems and components . 25 Table 4-5: Examples of mission dependent verification tests for acceptance . 26
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 spacecraft • ECSS-E-ST-35-02 Solid propulsion for spacecraft and launchers • ECSS-E-ST-35-03 Liquid propulsion for launchers • ECSS-E-ST-35-06 Cleanliness requirements for spacecrafts propulsion hardware • 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. SIST EN 16603-35-02:2014
EN reference Reference in text Title EN 16601-00-01 ECSS-S-ST-00-01
ECSS System- Glossary of terms EN 16603-20 ECSS-E-ST-20 Space engineering - Electrical and electronic EN 16603-20-07 ECSS-E-ST-20-07 Space engineering - Electromagnetic compatibility EN 16603-32 ECSS-E-ST-32 Space engineering - Structural general requirements EN 16603-32-08 ECSS-E-ST-32-08 Space engineering - Materials EN 16603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for spaceflight hardware EN 16603-33-11 ECSS-E-ST-33-11 Space engineering - Explosive systems and devices EN 16603-35 ECSS-E-ST-35 Space engineering - Propulsion general requirements EN 16602-20 ECSS-Q-ST-20 Space product assurance – Quality assurance EN 16602-40 ECSS-Q-ST-40 Space product assurance - Safety EN 16602-70 ECSS-Q-ST-70 Space product assurance - Materials, mechanical parts and processes
ECSS-E-ST-35 ablated thickness (ea) burning time charred thickness (ec) corridor hump effect ignition time (tign)
insulation thickness (ei) non affected thickness(es) pre-heating time solid rocket motor thrust centroid time SIST EN 16603-35-02:2014
Abbreviation Meaning AIV assembly, integration and verification COG centre of gravity COM centre of mass DLAT destructive lot acceptance test EMC electromagnetic compatibility EMI electromagnetic interference ESD electrostatic discharge GSE ground support equipment HCl chloride acid
MCI mass, centre of mass, inertia MDP maximum design pressure MEOP maximum expected operating pressure NDI non-destructive inspection OBDH on-board data handling SRM solid rocket motor TBPM to be provided by manufacturer TBPU to be provided by user TM/TC telemetry/telecommand TVC thrust vector control SIST EN 16603-35-02:2014
4.1 Overview A solid propulsion system comprises the following main subsystems: • The gas generating system consisting of a solid propellant contained in a thermally protected case. • A nozzle with or without TVC. • An ignition system to ignite the solid propellant. This document applies to large and small systems; the latter usually have some different requirements to the large systems. Solid propulsion systems can either deliver a velocity increment in a fixed direction (with respect to the launcher or spacecraft) or in a variable direction, depending on whether TVC is present or not. Most solid propulsion systems use a single nozzle and roll control is usually provided by a separate system. Solid propulsion systems are “one-shot” systems and do not need a lot of preparation before use. Because a solid propellant motor is a ‘one shot’ item, an acceptance firing test cannot be performed with the actual flight motor.
4.2 Functional 4.2.1 Mission a. ECSS-E-ST-35 clause 4.2 ‘mission’ shall apply. 4.2.2 Functions
4.2.2.1 Steady state a. The propulsion system shall: 1. conform to the interfaces (see “interfaces” clause 4.4), 2. provide the specified total impulse, a thrust profile (nominal and dispersion) versus time. SIST EN 16603-35-02:2014
The “end-of-flight” mass of solid motors strongly depends on the internal ballistics, functional parameters and the applied technologies. 4.2.2.4 First stage a. The first stage configuration and thrust profile shall be thoroughly analysed and a trade-off made against system constraints and requirements. 4.2.2.5 Electrical a. The propulsion system shall have electrical continuity, including grounding and bonding. 4.2.2.6 Thrust orientation a. The propulsion system shall provide TVC or a thrust in a fixed orientation (with respect to the launcher or spacecraft) according to the system requirements. SIST EN 16603-35-02:2014
a. Pressure or thrust oscillation levels vs frequency range shall be specified at system and subsystem level. b. Pressure or thrust oscillation vs frequency range shall be characterised. c. The maximum allowable dynamic mechanical loads induced by the solid rocket motor during transient phases shall be specified vs frequency.
NOTE
For example shock during ignition and pressure wave. d. The dynamic mechanical loads induced by the solid rocket motor during transient phases shall be characterised. e. The Report for dynamic phenomena shall be delivered in conformance with the DRD of Annex A. 4.3.2 External loads during the life cycle of the propulsion system a. All external loads, static and dynamic (including mechanical, thermal, electrical, magnetic, humidity and radiation) shall be specified as input for the design. 4.3.3 Thrust centroid time a. For solid thrusters that provide thrust impulsion, the thrust centroid time shall be characterized.
NOTE
Examples of solid thrusters: separation or braking rockets, control systems. 4.3.4 Acoustic noise
a. The acoustic noise generated by the motor operating in the atmosphere shall be characterised. b. The Report for acoustic noise phenomena shall be delivered in conformance with the DRD of Annex A. 4.3.5 Pollution
a. Pollution constraints shall be specified.
NOTE
For example propellant without HCl emissions, space debris mitigation. b. The propulsion system shall conform to the pollution constraints specified in 4.3.5a. SIST EN 16603-35-02:2014
For example nozzle plugs and igniters. b. The propulsion system shall conform to the constraints specified in 4.3.6a. c. The ejected parts shall be characterized. 4.3.7 Safety a. For safety aspects, ECSS-Q-ST-40 shall apply. b. Constraints on safety due the regulation shall be specified. c. The propulsion system shall conform to the constraints specified in 4.3.7b. d. The propulsion system safety parameters shall be characterized and delivered in conformance with the DRD of Annex B. 4.4 Interfaces 4.4.1 General
a. All the following interfaces shall conform to the propulsion system requirements during the whole life of the system or subsystems and include the following: 1. Other stages of the launcher. 2. The launcher or spacecraft spaceonics. 3. Stage or spacecraft components: (a) skirts; (b) spaceonics (including hardware, OBDH, TM/TC, wiring and tunnels); (c) separation devices; (d) TVC; (e) explosive devices; (f) stage or spacecraft thermal protection; (g) contamination (e.g. plume effects); (h) termination and destruction devices; (i) environmental protection devices (e.g. rain, dust, and Sun). SIST EN 16603-35-02:2014
Refer to ECSS-E-ST-32-08. 5. Interfaces with GSE and transport, including: (a) definition of interfaces for launcher or spacecraft GSE and transport, with the launch authorities for safety; (b) capability for the electrical grounding of the systems and subsystems. 4.4.2 Induced and environmental temperature a. The temperature range during the mission shall be specified. b. The number and amplitude of the temperature variations (thermal cycling) during the motor life shall be specified. NOTE 1 E.g. motors which have a long in-orbit life before being operated. NOTE 2 The operating range of the motor can require a thermal control system. 4.4.3 General environment a. The motor shall comply with the specified and its self–induced loads (thermal, dynamic) environment. b. Measurement and control devices shall be protected against specified and self-induced adverse effects. 4.5 Design
4.5.1 Overview The following clauses define requirements applicable to the overall propulsion system derived from specific characteristics of each component of the system itself. Therefore they do not intend to cover the mayor requirements applicable to each component. SIST EN 16603-35-02:2014
1. demonstrate compatibility with materials, propellants and fluids; 2. be selected assessing safety, economics, reliability and environmental considerations and restrictions. NOTE
E.g. debris, pollution. c. The design and dimensioning of the SRM and the components shall be compliant with the manufacturing capabilities (available facilities, and processes, and reproducibility). d. The causes for potential dispersions shall be analysed in the project phases A and B. NOTE
Reproducibility requirements are provided by the customer. e. For PDR the following characteristics shall be provided: 1. the mass and COM of the propulsion system; 2. performance; 3. type of ignition system; 4. nozzle structure and configuration (e.g. thrust orientation); 5. propellant type. NOTE
If the requirements given by customer cannot be met, (including. target cost and industrial feasibility) either: • the requirements are reconsidered,
• the system or subsystem design modified, or • the manufacturing and control processes modified (see ECSS-E-ST-10). f. For PDR the technological choices of the design shall be performed, justified, and documented, assessing the mission requirements, interface with other systems or subsystems, lifetime, safety, availability, manufacturing process, performance, cost, environmental considerations and restrictions (e.g. pollution). g. It shall be ensure that the solid propulsion components, subsystems and systems can sustain without degradation the loads during manufacturing, handling, test and transport. SIST EN 16603-35-02:2014
NOTE
This is performed with an appropriate design of seals and mechanical parts. SIST EN 16603-35-02:2014
2. non ejected mass vs time; 3. MCI (mass, COM, inertia,) vs time; 4. thrust centroid time; 5. motor dynamic behaviour; 6. pressure and thrust oscillations; 7. plume effects to be reported in conformance with Annex D ‘Plume analysis report’ DRD in
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