Scope
This Standard specifies the structural design verification of metallic and non-metallic pressurized hardware which includes pressure vessels, pressurized structures, pressure components (such as valves, pumps, lines, fittings, and hoses), and special pressurized equipment (e.g. batteries, heat pipes, cryostats, sealed containers, hazardous fluid container). Pressurized hardware is defined as hardware that ‘primarily contains internal pressure’, and therefore pressurized hardware (other than pressurized structures) that are subjected to significant loads other than internal pressure can require tailoring of the standardized structural design verification approach.
This standard provides a minimum set of requirements. Some topics are not covered fully by this standard. Topics not fully covered by this standard include:
- External supports and structural interfaces;
- Solid propellant motor cases;
- The following launcher liquid propulsion equipment: combustion chamber, gas generator, pre burner, turbopump, nozzle extension, igniter, mechanisms (according to ECSS-E-ST-35-03C, Liquid propulsion for launchers);
- Expulsion devices, including bladders and diaphragms;
- Functional requirements like rapid expulsion, cleanliness;
NOTE To some extent, rapid expulsion can be considered as unique environment (see 5.4.1k). - Pressure components that experience significant non-pressure loads, for example bellows, flexible lines, thrusters;
NOTE For more information on bellows and flexible lines, see e.g. Goyal, V. et al (2021) and NASA-HDBK-5010A volume 2. - Relief devices, for example burst disks and relief valves;
- Pyro valves;
NOTE For more information, see e.g. ECSS-E-ST-33-11C and JSC-67723 (the latter for aspects specifically relevant for human spaceflight). - Pressure system passivation, including definition of safe pressure;
- Demisability during re-entry;
- Inflatable pressurized hardware;
- Composite pressure components and composite special pressurized equipment;
- Non-metallic, non-composite pressurized hardware, including windows;
NOTE Note that homogeneous non-metallic liners are covered to some extent. - Seals.
Objectives of the associated verification process are primarily to demonstrate the qualification of design and performance, as meeting all specified requirements, and to ensure that the flight hardware is free from workmanship defects and acceptable for flight.
This Standard applies to all space products and in particular to launch vehicles, transfer vehicles, re-entry vehicles, spacecraft, space station, landing probes and rovers, sounding rockets, payloads and instruments.
This standard, similar to other current pressurized hardware standards, does not cover in detail the requirements for application of additive manufacturing to pressurized hardware. The ECSS-Q-ST-70-80 is a good starting point, but the relevant structural standards, e.g. ECSS-E-ST-32 and ECSS-E-ST-32-01, and emerging standards at e.g. NASA indicate that the most critical applications, especially in case of applications in human spaceflight, can require more effort than currently required as minimum by ECSS-Q-ST-70-80 (for example NASA-STD-6030, NASA-HDBK-5026).
This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS-S-ST-00.
Tailoring can involve complementing or replacing requirements of this standard with those of other standards that are made applicable, like ANSI/AIAA S-080 and ANSI/AIAA S-081 and NASA-STD-5019 or similar fracture control requirements documents. This can be especially relevant for human spaceflight applications.
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