49.025.01 - Materials for aerospace construction in general
ICS 49.025.01 Details
Materials for aerospace construction in general
Materialien der Luft- und Raumfahrttechnik im allgemeinen
Matériaux pour la construction aéronautique en général
Materiali za letalsko in vesoljsko gradnjo na splošno
General Information
Frequently Asked Questions
ICS 49.025.01 is a classification code in the International Classification for Standards (ICS) system. It covers "Materials for aerospace construction in general". The ICS is a hierarchical classification system used to organize international, regional, and national standards, facilitating the search and identification of standards across different fields.
There are 138 standards classified under ICS 49.025.01 (Materials for aerospace construction in general). These standards are published by international and regional standardization bodies including ISO, IEC, CEN, CENELEC, and ETSI.
The International Classification for Standards (ICS) is a hierarchical classification system maintained by ISO to organize standards and related documents. It uses a three-level structure with field (2 digits), group (3 digits), and sub-group (2 digits) codes. The ICS helps users find standards by subject area and enables statistical analysis of standards development activities.
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This document specifies requirements for the additive manufacturing of metallic parts with directed energy deposition (DED) in the aerospace industry.
Within the application scope of this document, wire is used as feedstock, and arc processes (gas-shielded metal arc processes (MIG/MAG/GMAW), tungsten inert gas processes (TIG/GTAW), plasma arc processes (PAW)) are used as the main energy source.
This document is to be used in conjunction with the engineering documents, if required by the engineering authority.
This document does not address health and safety issues.
- Standard21 pagesEnglish languagee-Library read for1 day
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".
- Standard28 pagesEnglish languagee-Library read for1 day
This document specifies the general organization of metallic material standards for aerospace applications, their links with other types of European standards and their use.
It corresponds to level 0 (see 4.2).
From the date of publication of this document, specifications for different welding and brazing products can be written in only one standard instead of separated material standards. Already existing material standards for filler metals for welding and for brazing can continue to follow this organization.
- Standard15 pagesEnglish languagee-Library read for1 day
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".
- Standard28 pagesEnglish languagee-Library read for1 day
This document specifies the general organization of metallic material standards for aerospace applications, their links with other types of European standards and their use.
It corresponds to level 0 (see 4.2).
From the date of publication of this document, specifications for different welding and brazing products can be written in only one standard instead of separated material standards. Already existing material standards for filler metals for welding and for brazing can continue to follow this organization.
- Standard15 pagesEnglish languagee-Library read for1 day
This document specifies requirements for the additive manufacturing of metallic parts with directed energy deposition (DED) in the aerospace industry.
Within the application scope of this document, wire is used as feedstock, and arc processes (gas-shielded metal arc processes (MIG/MAG/GMAW), tungsten inert gas processes (TIG/GTAW), plasma arc processes (PAW)) are used as the main energy source.
This document is to be used in conjunction with the engineering documents, if required by the engineering authority.
This document does not address health and safety issues.
- Standard21 pagesEnglish languagee-Library read for1 day
This document specifies a method for the determination of the flammability of aerospace materials by upward flame propagation. This test determines if a material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris which can ignite adjacent materials.
- Standard25 pagesEnglish languagesale 15% off
This document specifies a method for determining the identity and quantity of volatile off-gassed compounds from materials and assembled articles utilized in manned, pressurized spacecraft.
- Standard14 pagesEnglish languagesale 15% off
This document specifies two test methods for determining the flammability of electrical-wire insulation and accessory materials by exposure to an external ignition source in a static environment (test A) and in a gas-flow environment (test B). These tests determine if a wire insulation material, when exposed to a standard ignition source, will self-extinguish and not transfer burning debris which can ignite adjacent materials.
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SIGNIFICANCE AND USE
5.1 The procedures described in this practice have proven utility in the inspecting (1) monolithic polymer matrix composites (laminates) for bulk defects, (2) metals for corrosion during the service life of the part of interest, (3) thickness checks, (4) adhesive bonding of metals, composites, and sandwich core constructions, (5) coatings, and (6) composite filament windings. Both unpressurized, and with suitable precautions, pressurized materials and components are inspected.
5.2 This practice provides guidelines for the application of longitudinal wave examination to the detection and quantitative evaluation of damage, discontinuities, and thickness variations in materials.
5.3 This practice is intended primarily for the testing of parts to acceptance criteria most typically specified in a purchase order or other contractual document, and for testing of parts in-service to detect and evaluate damage.
5.4 MAUT search units provide near-surface resolution and detection of small discontinuities comparable to phased array transducers. They may or may not be capable of beam steering. The advantage of MAUT for straight-beam longitudinal wave inspections is the ability to provide real-time C-scan data, which facilitates data interpretation and shortens inspection time. Depending on inspection needs, data can be displayed as A-, B- or C-scans, or three-dimensional renderings. Toggling between pulse-echo and through transmission ultrasonic (TTU) modes without having to use another system or changing transducers is also possible.
5.5 The MAUT technique has proven utility in the inspection of multi-ply carbon-fiber reinforced laminates used in primary aircraft structures.11
5.6 For ultrasonic testing of laminate composites and sandwich core materials using conventional UT equipment consult Practice E2580. Consult Practice E114 for ultrasonic testing of materials by the pulse-echo method using straightbeam longitudinal waves introduced by a piezoelectric elemen...
SCOPE
1.1 This practice covers procedures for matrix array ultrasonic testing (MAUT) of monolithic composites, composite sandwich constructions, and metallic test articles. These procedures can be used throughout the life cycle of a part during product and process design optimization, on line process control, post-manufacturing inspection, and in-service inspection.
1.2 In general, ultrasonic testing is a common volumetric method for detection of embedded or subsurface discontinuities. This practice includes general requirements and procedures which may be used for detecting flaws and for making a relative or approximate evaluation of the size of discontinuities and part anomalies. The types of flaws or discontinuities detected include interply delaminations, foreign object debris (FOD), inclusions, disbond/un-bond, fiber debonding, fiber fracture, porosity, voids, impact damage, thickness variation, and corrosion.
1.3 Typical test articles include monolithic composite layups such as uniaxial, cross ply and angle ply laminates, sandwich constructions, bonded structures, and filament windings, as well as forged, wrought and cast metallic parts. Two techniques can be considered based on accessibility of the inspection surface: namely, pulse echo inspection for one-sided access and through-transmission for two-sided access. As used in this practice, both require the use of a pulsed straight-beam ultrasonic longitudinal wave followed by observing indications of either the reflected (pulse-echo) or received (through transmission) wave.
1.4 This practice provides two ultrasonic test procedures. Each has its own merits and requirements for inspection and shall be selected as agreed upon in a contractual document.
1.4.1 Test Procedure A, Pulse Echo (non-contacting and contacting) is at a minimum a single matrix array transducer transmitting and receiving longitudinal waves in the range of 0.5 MHz to 20 MHz (see Fig. 1). Th...
- Standard14 pagesEnglish languagesale 15% off
- Standard14 pagesEnglish languagesale 15% off
This document specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. It is applicable for determining interactive reactions between propellants and materials used in the design, construction, and operation of propellant storage, transfer, and flight systems.
- Standard10 pagesEnglish languagesale 15% off
SIGNIFICANCE AND USE
4.1 If not properly qualified, chemicals and chemical processes can attack metals used during aircraft maintenance and production. It is important to qualify only processes and chemical formulas that do not have any deleterious effects on aircraft metallic skins, fittings, components, and structures. This test procedure is used to detect and measure intergranular attack or pitting depth caused by aircraft maintenance chemical processes, hence, this test procedure is useful in selecting a process that will not cause intergranular attack or end grain pitting on aircraft alloys.
4.2 The purpose of this practice is to aid in the qualification or process conformance testing or production of maintenance chemicals for use on aircraft.
4.2.1 Actual aircraft processes in the production environment shall give the most representative results; however, the test results cannot be completely evaluated with respect to ambient conditions which normally vary from day to day. Additionally, when testing chemicals requiring dilutions, water quality and composition can play a role in the corrosion rates and mechanism affecting the results.
4.2.2 Some examples of maintenance and production chemicals include: organic solvents, paint strippers, cleaners, deoxidizers, water-based or semi-aqueous cleaners, or etching solutions and chemical milling solutions.
SCOPE
1.1 This practice covers the procedures for testing and measuring intergranular attack (IGA) and end grain pitting on aircraft metals and alloys caused by maintenance or production chemicals.
1.2 The standard does not purport to address all qualification testing parameters, methods, critical testing, or criteria for aircraft production or maintenance chemical qualifications. Specific requirements and acceptance testing along with associated acceptance criteria shall be found where applicable in procurement specifications, materials specifications, appropriate process specifications, or previously agreed upon specifications.
1.3 Units—The values stated in SI units are to be regarded as the standard. The values given in parentheses are for information only.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
- Standard3 pagesEnglish languagesale 15% off
- Standard3 pagesEnglish languagesale 15% off
ABSTRACT
This test method covers a technique for generating data to characterize the kinetics of the release of outgassing products from spacecraft materials. This technique will determine both the total mass flux evolved by a material when exposed to a vacuum environment and the deposition of this flux on surfaces held at various specified temperatures. The quartz crystal microbalances used in this test method provide a sensitive technique for measuring very small quantities of deposited mass. There are two test methods in this standard: Test Method A and Test Method B. The test apparatus shall consists of four main subsystems: a vacuum chamber, a temperature control system, internal configuration, and a data acquisition system. A test procedure for collecting data and a test method for processing and presenting the collected data are included.
SCOPE
1.1 This test method covers a technique for generating data to characterize the kinetics of the release of outgassing products from materials. This technique will determine both the total mass flux evolved by a material when exposed to a vacuum environment and the deposition of this flux on surfaces held at various specified temperatures.
1.2 This test method describes the test apparatus and related operating procedures for evaluating the total mass flux that is evolved from a material being subjected to temperatures that are between 298 and 398 K. Pressures external to the sample effusion cell are less than 7 × 10−3 Pa (5 × 10−5 torr). Deposition rates are measured during material outgassing tests. A test procedure for collecting data and a test method for processing and presenting the collected data are included.
1.3 This test method can be used to produce the data necessary to support mathematical models used for the prediction of molecular contaminant generation, migration, and deposition.
1.4 All types of organic, polymeric, and inorganic materials can be tested. These include polymer potting compounds, foams, elastomers, films, tapes, insulations, shrink tubing, adhesives, coatings, fabrics, tie cords, and lubricants.
1.5 There are two test methods in this standard. Test Method A uses standardized specimen and collector temperatures. Test Method B allows the flexibility of user-specified specimen and collector temperatures, material and test geometry, and user-specified QCMs.
1.6 The values stated in SI units are to be regarded as the standard. The values given in parentheses are for information only.
1.7 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.8 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
- Standard16 pagesEnglish languagesale 15% off
SIGNIFICANCE AND USE
3.1 This practice is a guideline for proper materials and process selection and application. The specific application of these guidelines must take into account contractual agreements, functional performance requirements for particular programs and missions, and the actual environments and exposures anticipated for each material and the equipment in which the materials are used. Guidelines are not replacements for careful and informed engineering judgment and evaluations and all possible performance and design constraints and requirements cannot be foreseen. This practice is limited to unmanned systems and unmanned or external portions of manned systems, such as the Space Station. Generally, it is applicable to systems in low earth orbit, synchronous orbit, and interplanetary missions. Although many of the suggestions and cautions are applicable to both unmanned and manned spacecraft, manned systems have additional constraints and requirements for crew safety which may not be addressed adequately in unmanned designs. Because of the added constraints and concerns for human-rated systems, these systems are not addressed in this practice.
SCOPE
1.1 The purpose of this practice is to aid engineers, designers, quality and reliability control engineers, materials specialists, and systems designers in the selection and control of materials and processes for spacecraft, external portion of manned systems, or man-tended systems. Spacecraft systems are very different from most other applications. Space environments are very different from terrestrial environments and can dramatically alter the performance and survivability of many materials. Reliability, long life, and inability to repair defective systems (or high cost and difficultly of repairs for manned applications) are characteristic of space applications. This practice also is intended to identify materials processes or applications that may result in degraded or unsatisfactory performance of systems, subsystems, or components. Examples of successful and unsuccessful materials selections and uses are given in the appendices.
1.2 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
- Standard17 pagesEnglish languagesale 15% off
This document provides a series of standard testing methods to determine the resistance of flat or curved surfaces against abrasion, scratch or punch under high dynamics as may occur for example by manually operating actuators or due to impacts of materials like shoes, cases, bags and other common objects of everyday’s usage inside an aircraft cabin. The method is also suitable to test the resistance of a surface against all other high dynamic strains.
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies the monitoring of mechanical tests and inspections performed both at the material (coupon) and at the structural scale by the implementation of kinematic field measurements by digital image correlation. This document describes an in situ method for evaluating the metrological performance of an extensometer system using image correlation for the delivery of displacement fields, and by extrapolation, of deformation fields. It can be implemented prior to the actual start of the test (or inspection). It will inform of the metrological performance in testing conditions.
This document allows the metrological performance of the measuring technology to be quantified. The methodology described herein is not to be considered as a calibration step. This reference document does not exhaustively specify the constitutive elements of a generic system of Digital Image Correlation measurement. This reference does not address the measurement of 3D shapes via stereocorrelation systems.
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SIGNIFICANCE AND USE
4.1 The goal of the NDT is to detect defects that have been implicated in the failure of the COPV metal liner, or have led to leakage, loss of contents, injury, death, or mission, or a combination thereof. Liner defects detected by NDT that require special attention by the cognizant engineering organization include through cracks, part-through cracks, liner buckling, pitting, thinning, and corrosion under the influence of cyclic loading, sustained loading, temperature cycling, mechanical impact and other intended or unintended service conditions.
Note 3: Liners made from stainless steel and nickel-based alloys exhibit a higher damage resistance to impact than those made from aluminum.
Note 4: Safe life is the goal for any COPV so that a through crack in the liner will not develop during the service life.
Note 5: The use a material with good fatigue and slow crack growth characteristics is important. For example, nickel-based alloys are better than precipitation-hardened stainless steel. Aluminum also has good ductility and crack resistance.
4.2 The COPVs covered in this guide consist of a metallic liner overwrapped with high-strength fibers embedded in polymeric matrix resin (typically a thermoset). Metallic liners may be spun formed from a deep drawn/extruded monolithic blank or may be fabricated by welding formed components. Designers often seek to minimize the liner thickness in the interest of weight reduction. COPV liner materials used can be aluminum alloys, titanium alloys, nickel-chromium alloys, and stainless steels, impermeable polymer liner such as high density polyethylene, or integrated composite materials. Fiber materials can be carbon, aramid, glass, PBO, metals, or hybrids (two or more types of fiber). Matrix resins include epoxies, cyanate esters, polyurethanes, phenolic resins, polyimides (including bismaleimides), polyamides and other high performance polymers. Common bond line adhesives are generally epoxies (FM-73, West 105, and Epon 86...
SCOPE
1.1 This guide discusses current and potential nondestructive testing (NDT) procedures for finding indications of discontinuities in thin-walled metallic liners in filament-wound pressure vessels, also known as composite overwrapped pressure vessels (COPVs). In general, these vessels have metallic liner thicknesses less than 2.3 mm (0.090 in.), and fiber loadings in the composite overwrap greater than 60 percent by weight. In COPVs, the composite overwrap thickness will be of the order of 2.0 mm (0.080 in.) for smaller vessels, and up to 20 mm (0.80 in.) for larger ones.
1.2 This guide focuses on COPVs with nonload sharing metallic liners used at ambient temperature, which most closely represents a Compressed Gas Association (CGA) Type III metal-lined COPV. However, it also has relevance to (1) monolithic metallic pressure vessels (PVs) (CGA Type I), and (2) metal-lined hoop-wrapped COPVs (CGA Type II).
1.3 The vessels covered by this guide are used in aerospace applications; therefore, examination requirements for discontinuities and inspection points will in general be different and more stringent than for vessels used in non-aerospace applications.
1.4 This guide applies to (1) low pressure COPVs and PVs used for storing aerospace media at maximum allowable working pressures (MAWPs) up to 3.5 MPa (500 psia) and volumes up to 2000 L (70 ft3), and (2) high pressure COPVs used for storing compressed gases at MAWPs up to 70 MPa (10 000 psia) and volumes down to 8 L (500 in.3). Internal vacuum storage or exposure is not considered appropriate for any vessel size.
Note 1: Some vessels are evacuated during filling operations, requiring the tank to withstand external (atmospheric) pressure.
1.5 The metallic liners under consideration include, but are not limited to, ones made from aluminum alloys, titanium alloys, nickel-based alloys, and stainless steels. In the case of COPVs, the composites through which the N...
- Guide29 pagesEnglish languagesale 15% off
- Guide29 pagesEnglish languagesale 15% off
SIGNIFICANCE AND USE
4.1 The COPVs covered in this guide consist of a metallic liner overwrapped with high-strength fibers embedded in polymeric matrix resin (typically a thermoset) (Fig. 1). Metallic liners may be spun-formed from a deep drawn/extruded monolithic blank or may be fabricated by welding formed components. Designers often seek to minimize the liner thickness in the interest of weight reduction. COPV liner materials used can be aluminum alloys, titanium alloys, nickel-chromium alloys, and stainless steels, impermeable polymer liner such as high density polyethylene, or integrated composite materials. Fiber materials can be carbon, aramid, glass, PBO, metals, or hybrids (two or more types of fibers). Matrix resins include epoxies, cyanate esters, polyurethanes, phenolic resins, polyimides (including bismaleimides), polyamides, and other high performance polymers. Common bond line adhesives are FM-73, urethane, West 105, and Epon 862 with thicknesses ranging from 0.13 mm (0.005 in.) to 0.38 mm (0.015 in.). Metallic liner and composite overwrap materials requirements are found in ANSI/AIAA S-080 and ANSI/AIAA S-081, respectively.
Note 6: When carbon fiber is used, galvanic protection should be provided for the metallic liner using a physical barrier such as glass cloth in a resin matrix, or similarly, a bond line adhesive.
Note 7: Per the discretion of the cognizant engineering organization, composite materials not developed and qualified in accordance with the guidelines in MIL-HDBK-17, Volumes 1 and 3 should have an approved material usage agreement.
FIG. 1 Typical Carbon Fiber Reinforced COPVs (NASA)
4.2 The as-wound COPV is then cured and an autofrettage/proof cycle is performed to evaluate performance and increase fatigue characteristics.
4.3 The strong drive to reduce weight and spatial needs in aerospace applications has pushed designers to adopt COPVs constructed with high modulus carbon fibers embedded in an epoxy matrix. Unfortunately, high modulus fiber...
SCOPE
1.1 This guide discusses current and potential nondestructive testing (NDT) procedures for finding indications of discontinuities and accumulated damage in the composite overwrap of filament wound pressure vessels, also known as composite overwrapped pressure vessels (COPVs). In general, these vessels have metallic liner thicknesses less than 2.3 mm (0.090 in.), and fiber loadings in the composite overwrap greater than 60 % by weight. In COPVs, the composite overwrap thickness will be of the order of 2.0 mm (0.080 in.) for smaller vessels and up to 20 mm (0.80 in.) for larger ones.
1.2 This guide focuses on COPVs with nonload-sharing metallic liners used at ambient temperature, which most closely represents a Compressed Gas Association (CGA) Type III metal-lined composite tank. However, it also has relevance to (1) monolithic metallic pressure vessels (PVs) (CGA Type I), (2) metal-lined hoop-wrapped COPVs (CGA Type II), (3) plastic-lined composite pressure vessels (CPVs) with a nonload-sharing liner (CGA Type IV), and (4) an all-composite, linerless COPV (undefined Type). This guide also has relevance to COPVs used at cryogenic temperatures.
1.3 The vessels covered by this guide are used in aerospace applications; therefore, the inspection requirements for discontinuities and inspection points will in general be different and more stringent than for vessels used in non aerospace applications.
1.4 This guide applies to (1) low pressure COPVs used for storing aerospace media at maximum allowable working pressures (MAWPs) up to 3.5 MPa (500 psia) and volumes up to 2 L (70 ft3), and (2) high pressure COPVs used for storing compressed gases at MAWPs up to 70 MPa (10 000 psia) and volumes down to 8 L (500 in.3). Internal vacuum storage or exposure is not considered appropriate for any vessel size.
Note 1: Some vessels are evacuated during filling operations, requiring the tank to withstand external (atmospheric) pre...
- Guide36 pagesEnglish languagesale 15% off
- Guide36 pagesEnglish languagesale 15% off
This document provides a series of standard testing methods to determine the resistance of flat or curved surfaces against abrasion, scratch or punch under high dynamics as may occur for example by manually operating actuators or due to impacts of materials like shoes, cases, bags and other common objects of everyday’s usage inside an aircraft cabin. The method is also suitable to test the resistance of a surface against all other high dynamic strains.
- Standard11 pagesEnglish languagee-Library read for1 day
This document specifies requirements and test methods for the qualification and re-qualification of laser beam machines for metal powder bed fusion additive manufacturing for aerospace applications.
It can also be used to verify machine features during periodic inspections or following maintenance and repair activities.
- Standard19 pagesEnglish languagee-Library read for1 day
- Standard19 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 The NVR determined by this test method is that amount that can reasonably be expected to exist on hardware exposed in environmentally controlled areas.
5.2 The evaporation of the solvent at or near room temperature is to quantify the NVR that exists at room temperature.
5.3 Numerous other methods are being used to determine NVR. This test method is not intended to replace methods used for other applications.
SCOPE
1.1 This test method covers the determination of nonvolatile residue (NVR) fallout in environmentally controlled areas used for the assembly, testing, and processing of spacecraft.
1.2 The NVR of interest is that which is deposited on sampling plate surfaces at room temperature: it is left to the user to infer the relationship between the NVR found on the sampling plate surface and that found on any other surfaces.
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.4 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
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ABSTRACT
This practice covers the proper procedures for handling, transporting, and installing sample plates used for the gravimetric determination of nonvolatile residue (NVR) within and between environmentally controlled facilities for spacecraft. This procedure shall appropriately require the following apparatuses and materials: Type 316 corrosion-resistant steel NVR plate; Type 316 corrosion-resistant steel NVR plate cover; noncontaminating nylon (polyamide bag); sealable aluminum NVR plate carrier; solvent compatible and resistant work gloves; oil-free aluminum foil; HEPA filters; and HEPA filtered workstation.
SCOPE
1.1 This practice covers the handling, transporting, and installing of sample plates used for the gravimetric determination of nonvolatile residue (NVR) within and between facilities.
1.2 The values stated in SI units are to be regarded as the standard.
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.4 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
- Standard6 pagesEnglish languagesale 15% off
This document specifies the dimensions and tolerances of cold rolled sheets and strips in heat resisting alloys used in aerospace construction.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard specifies the marking rules for aerospace products, semi-finished products, and ready to use parts, which need surface marking by discoloration using a laser source to identify the part and/or enhance its traceability.
This type of marking can be used on a wide range of materials (both metallic and non-metallic) and coatings (paints, varnishes…). It is in line with the part definition.
- Standard16 pagesEnglish languagee-Library read for1 day
SIGNIFICANCE AND USE
5.1 The significant features are typified by a discussion of the limitations of the technique. With the description and arrangement given in the following portions of this test method, the instrument will record directly the normal spectral emittance of a specimen. However, the following conditions must be met within acceptable tolerance, or corrections must be made for the specified conditions.
5.1.1 The effective temperatures of the specimen and blackbody must be within 1 K of each other. Practical limitations arise, however, because the temperature uniformities are often not better than a few kelvins.
5.1.2 The optical path length in the two beams must be equal, or, preferably, the instrument should operate in a nonabsorbing atmosphere, in order to eliminate the effects of differential atmospheric absorption in the two beams. Measurements in air are in many cases important, and will not necessarily give the same results as in a vacuum, thus the equality of the optical paths for dual-beam instruments becomes very critical.
Note 4: Very careful optical alignment of the spectrophotometer is required to minimize differences in absorptance along the two paths of the instrument, and careful adjustment of the chopper timing to reduce “cross-talk” (the overlap of the reference and sample signals) as well as precautions to reduce stray radiation in the spectrophotometer are required to keep the zero line flat. With the best adjustment, the “100 % line” will be flat to within 3 %.
5.1.3 Front-surface mirror optics must be used throughout, except for the prism in prism monochromators, and it should be emphasized that equivalent optical elements must be used in the two beams in order to reduce and balance attenuation of the beams by absorption in the optical elements. It is recommended that optical surfaces be free of SiO2 and SiO coatings: MgF2 may be used to stabilize mirror surfaces for extended periods of time. The optical characteristics of these coatings are...
SCOPE
1.1 This test method describes an accurate technique for measuring the normal spectral emittance of electrically nonconducting materials in the temperature range from 1000 to 1800 K, and at wavelengths from 1 to 35 μm. It is particularly suitable for measuring the normal spectral emittance of materials such as ceramic oxides, which have relatively low thermal conductivity and are translucent to appreciable depths (several millimetres) below the surface, but which become essentially opaque at thicknesses of 10 mm or less.
1.2 This test method requires expensive equipment and rather elaborate precautions, but produces data that are accurate to within a few percent. It is particularly suitable for research laboratories, where the highest precision and accuracy are desired, and is not recommended for routine production or acceptance testing. Because of its high accuracy, this test method may be used as a reference method to be applied to production and acceptance testing in case of dispute.
1.3 This test method requires the use of a specific specimen size and configuration, and a specific heating and viewing technique. The design details of the critical specimen furnace are presented in Ref (1),2 and the use of a furnace of this design is necessary to comply with this test method. The transfer optics and spectrophotometer are discussed in general terms.
1.4 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.6 This international standard was developed in accordance with internationally recognized principles on standardization established in t...
- Standard9 pagesEnglish languagesale 15% off
This document specifies the dimensions and tolerances of cold rolled sheets and strips in heat resisting alloys used in aerospace construction.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard specifies the marking rules for aerospace products, semi-finished products, and ready to use parts, which need surface marking by discoloration using a laser source to identify the part and/or enhance its traceability.
This type of marking can be used on a wide range of materials (both metallic and non-metallic) and coatings (paints, varnishes…). It is in line with the part definition.
- Standard16 pagesEnglish languagee-Library read for1 day
This European Standard specifies the dimensions and tolerances of heat resisting alloys wire used in aerospace construction.
- Standard6 pagesEnglish languagee-Library read for1 day
This European Standard specifies the dimensions and tolerances of heat resisting alloys wire used in aerospace construction.
- Standard6 pagesEnglish languagee-Library read for1 day
This test method defines the procedure for the determination of the curing-characteristic and glass transition temperature of non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use by Differential Scanning Calorimetry (DSC).
The results obtained by this method may be useful for:
- derivation of the optimum cure cycle (only together with other test methods e.g. Tg determination)
- assessment of the condition of the resin
- assessment of the ageing behavior of the resin
This European Standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this European Standard to adopt appropriate health and safety precautions.
- Standard13 pagesEnglish languagee-Library read for1 day
This test method defines the procedure for the estimation of the extent of cure of certain non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use. The extent of cure is estimated by Differential Scanning Calorimetry (DSC) measurements of uncured (reference) and cured materials. Additional evidence on the extent of cure may be gained by combining results from this method with those obtained by other techniques.
This standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this standard to adopt appropriate health and safety precautions.
- Standard11 pagesEnglish languagee-Library read for1 day
This European Standard defines the determination of density according to displacement method for metallic materials.
- Standard4 pagesEnglish languagee-Library read for1 day
This test method defines the procedure for the determination of the curing-characteristic and glass transition temperature of non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use by Differential Scanning Calorimetry (DSC).
The results obtained by this method may be useful for:
- derivation of the optimum cure cycle (only together with other test methods e.g. Tg determination)
- assessment of the condition of the resin
- assessment of the ageing behavior of the resin
This European Standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this European Standard to adopt appropriate health and safety precautions.
- Standard13 pagesEnglish languagee-Library read for1 day
This test method defines the procedure for the estimation of the extent of cure of certain non-metallic materials (e.g. preimpregnated and neat resin systems, adhesives) for aerospace use. The extent of cure is estimated by Differential Scanning Calorimetry (DSC) measurements of uncured (reference) and cured materials. Additional evidence on the extent of cure may be gained by combining results from this method with those obtained by other techniques.
This standard does not give any directions necessary to meet the health and safety requirements. It is the responsibility of the user of this standard to adopt appropriate health and safety precautions.
- Standard11 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to:
Heat resisting alloy NI-PH2601 (NiCr19Fe19Nb5Mo3)
Solution treated and precipitation treated
Bar and section
De 200 mm
for aerospace applications.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to:
Heat resisting alloy NI-PH2601 (NiCr19Fe19Nb5Mo3)
Solution treated and precipitation treated
Bar and section
De 200 mm
for aerospace applications.
- Standard9 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to:
Heat resisting alloy NiCr19Fe19Nb5Mo3 (2.4668)
Non heat treated
Forging stock
a or D <= 300 mm
for aerospace applications.
- Standard7 pagesEnglish languagee-Library read for1 day
This European Standard specifies the requirements relating to:
Heat resisting alloy NiCr19Fe19Nb5Mo3 (2.4668)
Non heat treated
Forging stock
a or D <= 300 mm
for aerospace applications.
- Standard7 pagesEnglish languagee-Library read for1 day
Several classes of materials depend on a chemical reaction for their application and their final properties are sensitive to the exact composition of the reactants. The final properties vary with the reactants’ age and storage condition.
This Standard defines the requirements for the identification, handling, storage and control of limited shelflife materials employed in the fabrication of spacecraft and associated equipment.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard13 pagesEnglish languagee-Library read for1 day
This document defines the requirements for the evaluation of the susceptibility of the SCC resistance.
It defines the preferred way to determine the susceptibility of metals and weldments to stress-corrosion cracking by alternate immersion
in 3.5 % sodium chloride under constant load.
The results obtained from test programmes made according to this specification are used to classify alloys, weldments and their individual heat treatment conditions. When sufficient stress-corrosion data exists, the alloy designations can be submitted for inclusion into the
various tables contained in ECSS-Q-ST-70-36.
In this document, the supplier is identified as the entity that performs the test.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard32 pagesEnglish languagee-Library read for1 day
This Standard covers the following processes of the general materials, mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
• The selection of metal alloys for which preference is given to approved data sources (Table 5 1 to Table 5 3)
• The criticality analysis to determine if a stress corrosion cracking (SCC) evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for spacecraft and associated equipment and facilities so that failure resulting from stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking control, which begins during design thanks to a methodological material selection.
This document does not intend to include all factors and criteria necessary for the total control of stresscorrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected stainless steels in the 300 series and alloys listed in Table 5 1.
This Standard is not applicable to listed materials whose behaviour differs at elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard39 pagesEnglish languagee-Library read for1 day
This Standard specifies requirements for mechanical testing of metallic materials to be used in the fabrication of spacecraft hardware.
This Standard establishes the requirements for most relevant test methods carried out to assess the tensile, fatigue and fracture
properties of metallic materials. It does not give a complete review of all the existing test methods for the evaluation of mechanical
properties of metallic materials.
Furthermore, this Standard specifies requirements for the evaluation, presentation and reporting of test results.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard32 pagesEnglish languagee-Library read for1 day
This Standard defines a multitest procedure for the determination of the flammability characteristics of nonmetallic materials under a set of closely controlled conditions. The test procedure covers both individual materials and materials used in configuration. This Standard describes a series of tests to provide data for aid in the evaluation of the suitability of materials for use in a space vehicle crew compartment. The data obtained are in respect to the ease of ignition and the flame propagation characteristics of materials.
All nonmetallic materials are inherently flammable, the degree to which this is true is dependant on the chemical nature of the material itself and the environment to which the material is exposed. In the closed environment of a manned spacecraft this can lead to a potentially dangerous situation and close control is therefore required.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard47 pagesEnglish languagee-Library read for1 day
This Standard describes a thermal vacuum test to determine the outgassing screening properties of materials proposed for use in the fabrication of spacecraft and associated equipment, for vacuum facilities used for flight hardware tests and for certain launcher hardware.
This Standard covers the following:
• critical design parameters of the test system;
• critical test parameters such as temperature, time, pressure;
• material sample preparation;
• conditioning parameters for samples and collector plates;
• presentation of the test data;
• acceptance criteria;
• certification of test systems and their operators by audits and round robin tests.
The test described in this Standard is applicable for all unmanned spacecraft, launchers, payloads, experiments. The test is also valid for external hardware of inhabited space systems and for hardware to be used in terrestrial vacuum test facilities.
The outgassing and condensation acceptance criteria for a material depend upon the application and location of the material and can be more severe than the standard requirements as given in clause 5.5.3.1.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS‐S‐ST‐00. 7
- Standard44 pagesEnglish languagee-Library read for1 day
This Standard describes a thermal vacuum test to determine the outgassing screening properties of materials proposed for use in the fabrication of spacecraft and associated equipment, for vacuum facilities used for flight hardware tests and for certain launcher hardware.
This Standard covers the following:
• critical design parameters of the test system;
• critical test parameters such as temperature, time, pressure;
• material sample preparation;
• conditioning parameters for samples and collector plates;
• presentation of the test data;
• acceptance criteria;
• certification of test systems and their operators by audits and round robin tests.
The test described in this Standard is applicable for all unmanned spacecraft, launchers, payloads, experiments. The test is also valid for external hardware of inhabited space systems and for hardware to be used in terrestrial vacuum test facilities.
The outgassing and condensation acceptance criteria for a material depend upon the application and location of the material and can be more severe than the standard requirements as given in clause 5.5.3.1.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS‐S‐ST‐00. 7
- Standard44 pagesEnglish languagee-Library read for1 day
Materials used in space applications need to be evaluated for their behaviour under Particle and UV Radiation. As part of this evaluation often an exposure to a simulated space environment is performed that can raise questions regarding its accuracy and representativeness. The role of this Standard is to establish a baseline for the testing specification. NOTE 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.
- Standard27 pagesEnglish languagee-Library read for1 day
This Standard covers the following processes of the general materials, mechanicals parts and processes (MMPP) flow of ECSS-Q-ST-70:
• The selection of metal alloys for which preference is given to approved data sources (Table 5 1 to Table 5 3)
• The criticality analysis to determine if a stress corrosion cracking (SCC) evaluation is necessary
This Standard sets forth the criteria to be used in the selection of materials for spacecraft and associated equipment and facilities so that failure resulting from stress-corrosion is prevented.
It is intended to provide general criteria to be used in stress-corrosion cracking control, which begins during design thanks to a methodological material selection.
This document does not intend to include all factors and criteria necessary for the total control of stresscorrosion cracking in all alloys.
The criteria established in this Standard are only applicable to designs for service involving exposure conditions similar to testing conditions
As regards weldments, this Standard is applicable to aluminium alloys, selected stainless steels in the 300 series and alloys listed in Table 5 1.
This Standard is not applicable to listed materials whose behaviour differs at elevated temperature and in specific chemical.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard39 pagesEnglish languagee-Library read for1 day
Several classes of materials depend on a chemical reaction for their application and their final properties are sensitive to the exact composition of the reactants. The final properties vary with the reactants’ age and storage condition.
This Standard defines the requirements for the identification, handling, storage and control of limited shelflife materials employed in the fabrication of spacecraft and associated equipment.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard13 pagesEnglish languagee-Library read for1 day
This Standard defines a multitest procedure for the determination of the flammability characteristics of nonmetallic materials under a set of closely controlled conditions. The test procedure covers both individual materials and materials used in configuration. This Standard describes a series of tests to provide data for aid in the evaluation of the suitability of materials for use in a space vehicle crew compartment. The data obtained are in respect to the ease of ignition and the flame propagation characteristics of materials.
All nonmetallic materials are inherently flammable, the degree to which this is true is dependant on the chemical nature of the material itself and the environment to which the material is exposed. In the closed environment of a manned spacecraft this can lead to a potentially dangerous situation and close control is therefore required.
This standard may be tailored for the specific characteristics and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard47 pagesEnglish languagee-Library read for1 day
This Standard specifies requirements for mechanical testing of metallic materials to be used in the fabrication of spacecraft hardware.
This Standard establishes the requirements for most relevant test methods carried out to assess the tensile, fatigue and fracture
properties of metallic materials. It does not give a complete review of all the existing test methods for the evaluation of mechanical
properties of metallic materials.
Furthermore, this Standard specifies requirements for the evaluation, presentation and reporting of test results.
This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
- Standard32 pagesEnglish languagee-Library read for1 day