V10 航空、航天材料基础标准 标准查询与下载

SAE AMS1625C-2010 脱氧剂,粉末状铝

This specification covers powered materials, solutions of which are used to remove smut from aluminum surfaces treated with etch-type oxidation and corrosion removers.

Desmutter, Aluminum Powdered

SAE AMS1626C-2010 脱氧剂,铝,液体

This specification covers materials in the form of a liquid used to remove smut from aluminum surfaces treated with etch-type oxidation and corrosion removers.

Desmutter, Aluminum Liquid

DIN EN 4632-005:2010 航空航天系列.航空航天结构用焊接及铜焊组件.材料的可焊接性和可铜焊接性.第005部分:耐热镍基或钴基合金均匀组件.德文和英文版本EN 4632-005-2009

Aerospace series - Weldability and brazeability of materials in aerospace constructions - Part 005: Homogeneous assemblies of heat resisting Ni or Co base alloys; German and English version EN 4632-005:2009

DIN 65046-6:2010 航空航天.表面防护的试验方法.第6部分:化学镀层和电镀层.不适用于新设计

Aerospace - Test methods for surface protection; Paints and varnishes - Part 6: Chemical and electroplated coatings - Inactive for new design

DIN 65046-1:2010 航空航天.表面保护层的试验方法.油漆和清漆.第1部分:概览和定义

Aerospace - Methods of test for surface protective coatings; Paints and varnishes - Part 1: Survey and identifications

BS EN 6072:2010 航空航天系列.金属材料.试验方法.横幅疲劳试验

This European Standard defines a method to determine constant amplitude fatigue data of metallic materials and the S-N curve (or Wöhler curve).

Aerospace series. Metallic materials. Test methods. Constant amplitude fatigue testing

SAE AMS1431C-2010 硬跑道和滑行道除冰/防冰用化学试剂

This specification covers a deicing and anti-icing compound in the form of a solid. This compound are intended for use at airports on aircraft maneuvering areas, such as aprons, runways, and taxiways, for the prevention and removal of frozen deposits of snow, frost, and ice..

Compound, Solid Runaway and Taxiway Deicing/Anti-Icing

BS ISO 11639:2010 航空航天.软组件零件号码

Aerospace - Part numbering for hose assemblies

SAE AIR5919A-2010 镉电镀层备选方案

This SAE Aerospace Information Report (AIR) is intended to document and provide access to information obtained by an industry survey. It summarizes and documents data regarding possible alternatives to the use of cadmium plating on general connectors and connector accessories typically used in the aerospace and military defense electrical interconnect systems.

Alternatives to Cadmium Plating

NF L06-394:2010 航空工业.航空航天结构的焊接件和钎焊件.用TIG法焊接的金属材料组件.焊接件质量

Weldments and brazements for aerospace structures - Assembly of metallic materials welded by TIG method - Quality of weldments.

BS EN 4638:2010 航空航天系列.喷砂介质.不含铁的褐色刚玉

This standard specifies the characteristics of brown corundum without iron used as blast media for aerospace applications.

Aerospace series - Blast media - Brown corundum, without iron

BS EN 4637:2010 航空航天系列.喷砂介质.白刚玉

This standard specifies the characteristics of white corundum used as blast media for aerospace applications.

Aerospace series - Blast media - White corundum

BS EN 4632-005:2009 航空航天系列.航空航天结构用材料的可焊接性和可铜焊性.耐热Ni 或Co基合金的类似组件

This European Standard defines degrees of weldability and brazeability for materials or families of materials used in the aerospace industry. It comprises a series of sheets, by materials or by material family, which:  indicate the main titles, the chemical composition and the main characteristics;  contain recommendations for welding and brazing;  indicate a degree of weldability or brazeability for a given process under defined conditions;  indicate a value of the mechanical strength coefficient of the welded joint for each welding process, when it could be extracted from bibliographic references referring to it. The joint coefficient is expressed as a ratio of the tensile strength of the welded joint to the tensile strength of the base alloy (to be in accordance with EN 4632-002). It is applicable without restriction for the manufacturing of new parts or for repair.

Aerospace series - Weldability and brazeability of materials in aerospace constructions - Homogeneous assemblies of heat resisting Ni or Co base alloys

SAE AMS2530-2010 较少粘合剂影响应用薄润滑油膜的二硫化钨涂层

This specification covers a coating consisting of tungsten disulfide without binders and not requiring a curing process.

Tungsten Disulfide Coating, Thin Lubricating Film, Binder-Less Impingement Applied

DIN EN 3987:2010 航空航天系列.金属材料试验方法.恒幅度可控力高循环疲劳试验.德文及英文版本EN 3987-2009

This standard applies to constant amplitude force-controlled high cycle fatigue (HCF) testing of metallic materials governed by EN Aerospace standards. It defines the mechanical properties that may need to be determined, the equipment, test pieces, methodology of test and presentation of results. It applies to uniaxially loaded tests carried out on plain or notched test pieces at ambient and elevated temperatures. It is not intended to cover the testing of more complex test pieces, full scale components or structures, although the methodology could well be adopted to provide for such tests.The purpose of this document is to ensure the compatibility and reproducibility of test results. It does not cover the evaluation or interpretation of results.

Aerospace series - Test methods for metallic materials - Constant amplitude force-controlled high cycle fatigue testing; German and English version EN 3987:2009

ASTM E2661/E2661M-10 航空航天设备用板状和平板复合结构的声发射检验的标准实施规程

This AE examination is useful to detect micro-damage generation, accumulation and growth of new or existing flaws. The examination is also used to detect significant existing damage from friction-based AE generated during loading or unloading of these regions. The damage mechanisms that can be detected include matrix cracking, fiber splitting, fiber breakage, fiber pull-out, debonding and delamination. During loading, unloading and load holding, damage that does not emit AE energy will not be detected. When the detected signals from AE sources are sufficiently spaced in time so as not to be classified as continuous AE, this practice is useful to locate the region(s) of the 2-D test sample where these sources originated and the accumulation of these sources with changing load and/or time. The probability of detection of the potential AE sources depends on the nature of the damage mechanisms, flaw characteristics and other aspects. For additional information see X1.4. Concentrated damage in fiber/polymer composites can lead to premature failure of the composite item. Hence, the use of AE to detect and locate such damage is particularly important. AE-detected flaws or damage concentrated in a certain region may be further characterized by other NDE techniques (for example, visual, ultrasonic, etc.) and may be repaired as appropriate. Repair procedure recommendations and the subsequent examination of the repair are outside the scope of this practice. For additional information see X1.5. This practice does not address sandwich core, foam core or honeycomb core plate-like composites due to the fact that currently there is little in the way of published work on the subject resulting in a lack of a sufficient knowledge base. Refer to Guide E2533 for additional information about types of defects detected by AE, general overview of AE as applied to polymer matrix composites, discussion of the Felicity ratio (FR) and Kaiser effect, advantages and limitations, AE of composite parts other than flat panels, and safety hazards.1.1 This practice covers acoustic emission (AE) examination or monitoring of panel and plate-like composite structures made entirely of fiber/polymer composites. 1.2 The AE examination detects emission sources and locates the region(s) within the composite structure where the emission originated. When properly developed AE-based criteria for the composite item are in place, the AE data can be used for nondestructive examination (NDE), characterization of proof testing, documentation of quality control or for decisions relative to structural-test termination prior to completion of a planned test. Other NDE methods may be used to provide additional information about located damage regions. For additional information see Appendix X1. 1.3 This practice can be applied to aerospace composite panels and plate-like elements as a part of incoming inspection, during manufacturing, after assembly, continuously (during structural health monitoring) and at periodic intervals during the life of a structure. 1.4 This practice is meant for fiber orientations that include cross-plies, angle-ply laminates or two-dimensional woven fabrics. This practice also applies to 3-D reinforcement (for example, stitched, z-pinned) when the fiber content in the third direction is less than 5 % (based on the whole composite). 1.5 This practice is directed toward composite materials that typically contain continuous high modulus greater than 20 GPa [3 Msi] fibers. 1.6 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combi......

Standard Practice for Acoustic Emission Examination of Plate-like and Flat Panel Composite Structures Used in Aerospace Applications

ASTM F520-10 航空航天用透明材料的环境耐受性的标准试验方法

This test method, when applied to aerospace transparencies of either monolithic glass/plastic or laminated combinations, is a measure of the ability of the transparency to withstand the effects of artificially induced environments. The test may be used on configurations employing electrically conductive coatings, and also to evaluate the integrity of noncoated materials. The resistance of the transparent enclosure to environmental effects may vary appreciably depending on the size, geometry, material of construction, coating integrity, coating density, and other factors.1.1 This test method covers determination of the effects of exposure to thermal shock, condensing humidity, and simulated weather on aerospace transparent enclosures. 1.2 This test method is not recommended for quality control nor is it intended to provide a correlation to actual service life. 1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard. 1.3.1 Exceptions8212;Certain inch-pound units are furnished in parentheses (not mandatory) and certain temperatures in Fahrenheit associated with other standards are also furnished. 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 and health practices and determine the applicability of regulatory limitations prior to use.

Standard Test Method for Environmental Resistance of Aerospace Transparencies

SAE AMS2475G-2009 镁合金防护处理

This specification establishes the requirements for chromate conversion coatings on magnesium alloys. This process has been used typically to improve corrosion resistance and adherence of organic finishes but usage is not limited to such applications. The dichromate treatment may not be suitable for alloys with high manganese content. The chrome pickle treatment has been used as touch-up for previously dichromate-treated surfaces and for improving corrosion protection temporarily, but usages are not limited to such applications.

Protective Treatments Magnesium Alloys

KS W ISO 7314:2009 航空航天.流体系统.金属软管组装品

Aerospace-Fluid systems-Metal hose assemblies

SAE AMS2769B-2009 真空部件的热处理

This specification establishes the requirements and procedures for heat treating parts in a vacuum/partial pressure. This process has been used typically for the heat treatment of carbon and alloy steels, tool steels, corrosion-resistant steels, precipitation -hardening steels, super alloys, titanium, and other nonferrous alloys, but usage is not limited to such applications. Heat treatment as used in this specification includes solution treatment, homogenizing, austenitizing, annealing, normalizing, hardening, tempering, aging, and stress relieving. This specification does not cover processes such as melting, brazing, diffusion bonding, coating, carburizing, or nitriding. The objective of this process is to produce heat treated parts which are free from surface contamination and alloy depletion. Such parts may not necessarily have a bright surface.

Heat Treatment of Parts in a Vacuum