49 - AIRCRAFT AND SPACE VEHICLE ENGINEERING
ICS 49 Details
AIRCRAFT AND SPACE VEHICLE ENGINEERING
LUFT- UND RAUMFAHRTTECHNIK
AERONAUTIQUE ET ESPACE
LETALSKA IN VESOLJSKA TEHNIKA
General Information
This document addresses the design process of a collocation and the basic contents of collocation design process which include considerations, initial collocation strategy design, simulation evaluation of collocation strategy, optimal collocation strategy selection and collocation agreement. This document gives guidelines for multi-geo spacecraft collocation, and it applies in particular to multi-geo constellation.
- Technical report21 pagesEnglish languagesale 15% off
- Draft21 pagesEnglish languagesale 15% off
This document provides the baseline standard on the subject of testing at the system, subsystem and unit levels for applicable unmanned spacecraft programmes. It also provides the requirements for documentation associated with testing activities. This document contains provisions for qualification and acceptance testing, or proto-flight testing (PFT). It assumes that hardware development is complete.
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- Draft34 pagesEnglish languagesale 15% off
The purpose of this document is to define the Space Link Extension (SLE) Return Channel Frames (RCF) service in conformance with the SLE Reference Model (reference [1]). The RCF service is an SLE transfer service that delivers to a mission user all telemetry frames from one master channel or one virtual channel. This document defines, in an abstract manner, the RCF service in terms of: the operations necessary to provide the service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to acquire telemetry frames from signals received from a spacecraft; the methods or technologies required to provide a suitable environment for communications; or the management activities required to schedule, configure, and control the RCF service. NOTE  –   Reference [1] defines the Return Master Channel Frames (Rtn MC Frames) service and the Return Virtual Channel Frames (Rtn VC Frames) service as two distinct services. Subsequent study has indicated that it is preferable to define one service that provides the functionality of both. The RCF service defined here does just that. It is anticipated that a future issue of reference [1] will take the same approach, deleting the Rtn MC Frames and Rtn VC Frames services and replacing them with the RCF service. Â
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This document defines, in an abstract manner, the RAF service in terms of: the operations necessary to provide the service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to acquire telemetry frames from signals received from a spacecraft; the methods or technologies required to provide a suitable environment for communications; or the management activities required to schedule, configure, and control the RAF service.
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- Draft136 pagesEnglish languagesale 15% off
The purpose of this document is to define the Space Link Extension (SLE) Return Operational Control Fields (ROCF) service in conformance with the SLE Reference Model (reference [1]). The ROCF service is an SLE transfer service that delivers to a mission user all operational control fields from one master channel or one virtual channel. This document defines, in an abstract manner, the ROCF service in terms of: the operations necessary to provide the service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to acquire telemetry frames from signals received from a spacecraft; the methods or technologies required to provide a suitable environment for communications; or the management activities required to schedule, configure, and control the ROCF service. NOTE  –   Reference [1] defines the Return Master Channel Operational Control Field (Rtn MC-OCF) service and the Return Virtual Channel Operational Control Field (Rtn VC-OCF) service as two distinct services. Subsequent study has indicated that it is preferable to define one service that provides the functionality of both. The ROCF service defined here does just that. It is anticipated that a future issue of reference [1] will take the same approach, deleting the Rtn MC-OCF and Rtn VC-OCF services and replacing them with the Rtn OCF service.
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This document specifies two standard message formats for use in transferring spacecraft attitude information between space agencies: the Attitude Parameter Message (APM) and the Attitude Ephemeris Message (AEM). Such exchanges are used for: - preflight planning for tracking or attitude estimation support; - scheduling attitude and data processing support; - carrying out attitude operations; - performing attitude comparisons; - carrying out attitude propagations and/or sensor predictions; - testing to initialize sub-system simulators (communications, power, etc.). This document includes sets of requirements and criteria that the message formats have been designed to meet. For exchanges where these requirements do not capture the needs of the participating agencies, another mechanism may be selected.
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This document defines the Application Program Interface in terms of: the components that provide the services of the API; the functionality provided by each of the components; the interfaces provided by each of the components; and the externally visible behavior associated with the interfaces exported by the components. It does not specify: individual implementations or products; the internal design of the components; and the technology used for communications. This document defines those aspects of the Application Program Interface, which are common for all SLE service types or for a subset of the SLE service types, e.g., all return link services or all forward link services. It also defines a framework for specification of service type-specific elements of the API. Service-specific aspects of the API are defined by supplemental Recommended Practice documents for SLE return link services (references [10], [11], and [12]) and SLE forward link services (references [13] and [14]). This document for the Application Program Interface responds to the requirements imposed on such an API by the CCSDS SLE transfer service Recommended Standards that were available when this document was released.
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The purpose of this document is to provide a common reference and framework of standards for digital motion video and imagery, and to provide recommendations for utilization of international standards for sharing or distributing motion video and imagery between spacecraft elements and ground systems. The scope of this document includes traditional real-time streaming video and television, including human and robotic spacecraft-to-spacecraft and spacecraft-to-ground systems, as well as video recorded and distributed later, either as a real-time stream or as a file transfer. In this context, real-time streaming includes all modes where video is sent from a spacecraft in a continuous stream and is intended for immediate use when received, regardless of the latency of the transmission path. Other specialized motion imagery applications, such as high-speed scientific motion imagery and multi-spectral motion imagery, are not addressed in this document. However, if a specialized imagery camera system has a requirement to interface to spacecraft systems in a video mode, it would be required to match these interfaces. Ground-systems-to-ground-systems video distribution is obviously a key component of the entire video system. However, this is not the primary focus of this document. Currently, there are significant differences in the ways mission video products are exchanged between the various space agencies on the ground. This is the result of differences in network topologies between space agencies, and agreements for video sharing. Those differences preclude there being a standard methodology for delivering video imagery between agencies. Prior to the commencement of video transmission between space agencies, system design reviews and performance testing should be done between the ground systems in use to assure operability when video imagery comes from spacecraft.
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- Draft34 pagesEnglish languagesale 15% off
This document defines the Communications Link Transmission Unit (CLTU) service in conformance with the transfer services specified in reference [1], Cross Support Reference Model—Part 1: SLE Services. The Forward CLTU service is a Space Link Extension (SLE) transfer service that enables a mission to send Communications Link Transmission Units (CLTUs) to a spacecraft. This document defines, in an abstract manner, the Forward CLTU service in terms of: the operations necessary to provide the transfer service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to radiate data to a spacecraft and to acquire telemetry frames from the signals received from that spacecraft for extraction of the Operational Control Field; the methods or technologies required for communications; or the management activities necessary to schedule, configure, and control the Forward CLTU service.
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- Draft143 pagesEnglish languagesale 15% off
This document defines the Forward Space Packet (FSP) service in conformance with the transfer services specified in reference [1], Cross Support Reference Model―Part 1: SLE Services. The FSP service is a Space Link Extension (SLE) transfer service that enables a mission to send Space Packets to a spacecraft in sequence-controlled or expedited mode. This document defines, in an abstract manner, the FSP service in terms of: the operations necessary to provide the transfer service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to radiate Space Packets to a spacecraft and to acquire telemetry frames from the signals received from that spacecraft for extraction of the Operational Control Field; the methods or technologies required for communications; or the management activities necessary to schedule, configure, and control the FSP service. NOTE  –   While the FSP service as described in reference [1] is conceived to handle a variety of packet data structures, this version of the FSP Recommended Standard is restricted to the handling of Space Packets as defined in reference [6]. This version of the FSP Recommended Standard is specific to the transfer of Space Packets to be transmitted via the Telecommand protocol stack as defined in references [3], [4], and [5]. The Cross Support Reference Model (reference [1]) specifies that the FSP service may also be used in conjunction with the Advanced Orbiting System protocol stack, but that mode of operation is outside the scope of this version of the Recommended Standard. The FSP service is provided in the online delivery mode, as defined in reference [1]. The offline delivery mode is the subject of further study.
- Standard190 pagesEnglish languagesale 15% off
- Draft190 pagesEnglish languagesale 15% off
This document specifies the characteristics of electrical cables for use in the on-board electrical systems of aircraft at operating temperatures between -55 °C and 260 °C for cross sections equal to and greater than 5 mm2.
- Standard10 pagesEnglish languagesale 10% offe-Library read for1 day
- Standard54 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies a common process for selecting and implementing meteoroid and space debris environment models used in the impact flux assessment for design and operation of spacecraft and other purposes. This document provides guidelines and requirements for the process.
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This document establishes a system for sealing the port connection of couplings used in the aerospace industry. It specifies dimensions to achieve interchangeability of the port connection, the fitting end and a seal. The seal can be a standard O‑ring or a special ring.
- Standard7 pagesEnglish languagesale 15% off
- Draft7 pagesEnglish languagesale 15% off
This document defines the geometry of the interface of removable 24° cone couplings for fluid systems in aircraft. The connection with the pipe of each one of the connecting elements can be of different design. This document specifies the dimensions which allow the interchangeability of the male and female elements and of the nut used for the connection. The dimensions define the maximum volume of the male fitting.
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- Draft5 pagesEnglish languagesale 15% off
This document defines the requirements for the ordering, manufacture, testing, inspection and delivery of steel and heat resisting alloy bars and sections. It shall be applied when referred to and in conjunction with the EN material standard unless otherwise specified on the drawing, order or inspection schedule.
- Standard34 pagesEnglish languagesale 10% offe-Library read for1 day
The document considers peculiarities of the space environment impact on a special kind of materials: nanostructured materials (i.e. materials with structured objects which size in at least one dimension lies within 1Â nm to 100Â nm) and specifies the methods of mathematical simulation of such processes. It emphasizes the necessity of applying multiscale simulation approach and does not include any special details concerning concrete materials, elements of spacecraft construction and equipment, etc. This document provides the general description of the methodology of applying computer simulation methods which relate to different space and time scales to modelling processes occurring in nanostructured materials under the space environment impact. The document can be applied as a reference document in spacecraft designing, forecasting the spacecraft lifetime, conducting ground-based tests, and analysing changes of material properties during operation.
- Technical specification29 pagesEnglish languagesale 15% off
- Draft29 pagesEnglish languagesale 15% off
This document specifies the requirements for producing and testing a general purpose chemical conversion coating on aluminium alloys. The chemical conversion coating is used in the manufacture of aerospace products in order to improve paint adhesion and resistance to corrosion. This process can also be used for touch-up of anodic coatings.
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- Standard6 pagesFrench languagesale 15% off
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This document specifies the requirements for producing and testing an unsealed anodic coating on titanium and titanium alloys. The anodic coating is produced by the sulfuric acid process. The coating is used with solid film lubricants for protection of titanium fasteners against galling, for limited protection of less noble metals against galvanic corrosion when in contact with titanium or for other approved uses.
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- Standard3 pagesFrench languagesale 15% off
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- Draft3 pagesFrench languagesale 15% off
This document specifies the requirements relating to:
Steel X12CrNiMoV12-3 (1.4938)
Air melted and consumable electrode remelted
Hardened and tempered
Bars
De ≤ 150 mm
900 MPa ≤ Rm ≤ 1 100 MPa
for aerospace applications.
- Standard9 pagesEnglish languagesale 10% offe-Library read for1 day
This document establishes the baseline requirements for the design, fabrication and testing of space flight pressure components. It also establishes the requirements for the assembly, installation, test, inspection, operation and maintenance of the pressure systems in spacecraft and launch vehicles. These requirements, when implemented on a particular space system, ensure a high level of confidence in achieving safe and reliable operation. This document applies to all pressure components other than pressure vessels and pressurized structures in a pressure system. It covers lines, fittings, valves, bellows, hoses and other appropriate components that are integrated to form a pressure system. The requirements for pressure vessels and pressurized structures are set forth in ISOÂ 14623. This document does not apply to engine components.
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- Draft27 pagesEnglish languagesale 15% off
This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris. This document provides information to engineers on the requirements and recommendations in the space debris mitigation standards to reduce the growth of space debris by ensuring that launch vehicle orbital stages are designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
- Technical report31 pagesEnglish languagesale 15% off
- Draft31 pagesEnglish languagesale 15% off
This document specifies the required characteristics, inspections and tests, quality assurance, conditions for qualification, acceptance and delivery of rod-ends with self-aligning bearings metal to metal designed to withstand slight swivelling under load. They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
This document applies to all rod-ends with self-aligning bearings metal to metal. It may be applied when referred to in a product standard or in a design specification.
- Standard22 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies the dimensions of a hose assembly which is in accordance with ISO 7313.
The hose assembly couples to the fittings specified in EN 3274, which are made out of titanium.
The hose is protected either by means of an anti-abrasive, anti-shock and anti-projection sleeve or by means of a fire resistant or fire proof sleeve in accordance with ISO 2685.
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This document specifies the dimensions of normal bihexagonal head bolts, with close or large tolerance normal shank and short or medium length MJ threads, in metallic material, coated or uncoated, with strength classes less than or equal to 1 100 MPa. This document is applicable to the compilation of aerospace product standards.
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- Draft4 pagesEnglish languagesale 15% off
This document specifies the dimensions and tolerances of plates in aluminium alloy 2024 with close-tolerance flatness, thickness 6 mm < a ≤ 55 mm, for aerospace applications.
- Standard9 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies the characteristics of adjustable rod ends with self-aligning double row ball bearing with reduced internal radial clearance and threaded shank in corrosion resisting steel, designed to withstand only slow rotations and oscillations under load.
They consist of:
- a rod end comprising:
- circumferential groove to identify location;
- either seals or shields;
- an optional longitudinal groove for locking purpose;
- an inner ring with balls.
These rod ends are intended for use with flight control rods or rods for aerospace structures.
They are intended to be used in the temperature range: −54 °C to 150 °C.
However, being lubricated with the following greases:
- very high pressure grease, ester type (code A), operational range −73 °C to 121 °C; or
- very high pressure grease, synthetic hydrocarbons, general purpose (code B), operational range −54 °C to 177 °C (see EN 2067);
their field of application when lubricated with code A grease is limited to 121 °C.
- Standard11 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies a method of testing flexure endurance of the cable when it is subjected to alternating flexing.
It shall be used together with EN 3475-100.
- Standard6 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies the characteristics of adjustable rod ends with self-aligning double row ball bearing in corrosion resisting steel with reduced internal radial clearance and threaded shank in titanium alloy, designed to withstand only slow rotations and oscillations under load.
They consist of:
- a rod end comprising:
- circumferential groove to confirm that the assembled rod-end is "in safety" emphasized with the application of red paint;
- either seals or shields;
- an optional longitudinal groove for locking purpose;
- an inner ring with balls.
These rod ends are intended for use with flight control rods or rods for aerospace structures.
They are intended to be used in the temperature range: −54 °C to 150 °C.
However, being lubricated with the following greases:
- very high pressure grease, ester type (code A), operational range −73 °C to 121 °C; or
- very high pressure grease, synthetic hydrocarbons, general purpose (code B), operational range −54 °C to 177 °C (see EN 2067);
their field of application when lubricated with code A grease is limited to 121 °C.
- Standard11 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies the requirements relating to:
Heat resisting alloy X6NiCrTiMoV26-15 (1.4980)
Softened and cold worked
Wires for forged fasteners
D ≤ 15 mm
900 MPa ≤ Rm ≤ 1 100 MPa
for aerospace applications.
W.nr: 1.4980.
ASD-STAN designation: FE-PA2601.
- Standard9 pagesEnglish languagesale 10% offe-Library read for1 day
This document specifies the technical requirements to minimize the hazards listed in Clause 4 which can arise during the commissioning, operation and maintenance of AFE when used as intended, including misuse reasonably foreseeable by the manufacturer, when carried out in accordance with the specifications given by the manufacturer or his authorized representative. It also takes into account some performance requirements recognized as essential by authorities, aircraft and ground support equipment (GSE) manufacturers as well as airlines, airports and fuelling companies.
This document applies to all types of aircraft fuelling equipment:
a) aircraft refuellers;
b) hydrant dispensers;
c) defuellers;
d) hydrant pit servicing vehicles;
e) pit cleaner vehicles;
f) stationary dispensing units,
intended to service aircraft with aviation fuels and to be operated on airfields, heliports and other aircraft refuelling related areas such as maintenance bases.
This document does not apply to:
g) AFE whose only power source for aircraft refuelling is directly applied manual effort;
h) hydrant systems, tank farms, pipework and underground tanks;
i) specific hazards due to the operation of the AFE in a potentially explosive atmosphere;
j) built-in fire extinguisher systems.
No extra requirements on noise and vibration are provided other than those in EN 1915-3 and EN 1915-4.
NOTE EN 1915-3 and EN 1915-4 provide the general GSE vibration and noise requirements.
This document does not deal with hazards in respect to a standard automotive chassis and from other vehicles on the apron.
This document is not applicable to AFE which are manufactured before the date of publication of this document by CEN.
This part of the EN 12312 series when used in conjunction with EN 1915-1, EN 1915-2, EN 1915-3 (for vehicles) and EN 1915-4 provides the requirements for AFE.
- Standard52 pagesEnglish languagesale 10% offe-Library read for1 day
This document establishes the requirements for simulation of the space control system, including the objective, architecture and procedure, etc. This document is applicable to four phases of control system development, including conceptual design, detailed design, prototype and integrated system. The control system referred to in this document is the flight control system for guidance, navigation and control (GNC) of space systems which include launch vehicle, satellite and spaceship, etc. This document establishes a minimum set of requirements for simulation of the flight control system, and provides guidance to engineers on what to simulate in each phase of control system development. The requirements are generic in nature because of their broad applicability to all types of simulations. Implementation details of the requirements are addressed in project-specific standards, requirements, and handbooks, etc.
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IEC PAS 63343:2021 specifies technical requirements, methods of test and required test results for equipment implementing ASM part of the VHF Data exchange system (VDES) as defined in ITU-R M.2092.
- Technical specification73 pagesEnglish languagesale 15% off
- Standard1 pageEnglish languagesale 15% off
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This document defines detailed space debris mitigation requirements and recommendations for the design and operation of launch vehicle orbital stages in Earth orbit. The requirements defined in this document are applicable for: — avoiding the release of space debris; — disposing of a launch vehicle orbital stage after the end of its mission so as to avoid a break-up in orbit; — disposing of a launch vehicle orbital stage after the end of its mission so as to minimize interference with the protected regions; — safely re-entering a launch vehicle orbital stage.
- Standard8 pagesEnglish languagesale 15% off
- Draft8 pagesEnglish languagesale 15% off
This document specifies the requirements for a two-components flexible polyurethane topcoat to be applied over EN 4687 and/or EN 4688 primers mainly for exterior aerospace applications.
The primer and the finish tested to this document will be from the same manufacturer applied in accordance with (i.a.w.) their instructions/Table 1.
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This document defines the requirements for a two-components, high corrosion inhibiting epoxy primer.
The coating shall be suitable for use on suitably prepared metallic substrates, chromic acid anodised, or conversion coated aluminium alloys and other suitably prepared substrates.
- Standard18 pagesEnglish languagesale 10% offe-Library read for1 day
This document establishes the general requirements for variable displacement uni-directional and bi-directional hydraulic motors, suitable for use in aircraft hydraulic systems at pressures up to 35 000 kPa (5 000 psi). These requirements include: — design requirements; — test requirements. Primary and secondary function motors (see Clause 4) are covered in this document; however, actuators with internal rotation angle limits and low-speed motors are not covered. This document is intended to be used in conjunction with the detail specification that is particular to each application.
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- Draft38 pagesEnglish languagesale 15% off
This document describes the procedures for training personnel who will be involved in the operation of unmanned aircraft systems (UAS). This document defines: a) knowledge, skill, attitude and qualification criteria that are needed for UAS pilots and training organizations that provides training to trainees of UAS remote pilots and other personnel involved in UAS operations; b) training curriculum and contents for specific learning courses; c) qualification and confirmation criteria for the training organizations; d) general procedures for providing training of UAS personnel. The requirements for a specific course as described in the annexes can be more restrictive in some cases.
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The following documents are referred to in the text in such a way that some or all of their content constitutes requirements of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 7500‑1, Metallic materials — Calibration and verification of static uniaxial testing machines — Part 1: Tension/compression testing machines — Calibration and verification of the force-measuring system
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- Draft17 pagesEnglish languagesale 15% off
This document defines the requirements for a two-components, chromate and lead-free primer.
The coating shall be suitable for use on fibre reinforced composite materials, titanium and corrosion resistant steels and other suitably prepared corrosion resistant substrates.
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- Draft3 pagesEnglish languagesale 15% off
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.
- Standard37 pagesEnglish languagesale 10% offe-Library read for1 day
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.
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This document specifies the lead and runout requirements for rolled external threads for aerospace construction, and the inspection method to be used in case of dispute. It is applicable whenever it is referenced in a definition document.
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- Draft10 pagesEnglish languagesale 15% off
This document specifies the lead and runout thread and undercut requirements for internal threads (blind tapped holes) for aerospace construction. It is applicable whenever it is referenced in a definition document.
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- Draft5 pagesEnglish languagesale 15% off
This document specifies the electrolytic cadmium plating of parts and fasteners in steel of tensile strength Rm (max.) 1 450 MPa, copper, copper alloys and nickel alloys, whose temperature in service does not exceed 235 °C.
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This document specifies requirements and test methods for the qualification of laser beam machines for metal powder bed additive manufacturing for aerospace applications.
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- Standard19 pagesEnglish languagesale 10% offe-Library read for1 day
This European standard specifies the characteristics of adjustable rod-ends consisting of:
- a spherical plain bearing, metal to metal, in corrosion resisting steel, wide series (EN 4265)
- a rod end with internal threaded shank
They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
- Standard15 pagesEnglish languagesale 10% offe-Library read for1 day
This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris. This document provides information to engineers on what are required or recommended in the family of space debris mitigation standards to reduce the growth of space debris by ensuring that spacecraft is designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.
- Technical report56 pagesEnglish languagesale 15% off
- Draft56 pagesEnglish languagesale 15% off