航空航天制造用材料

摘要： 本文件规定了低氧高碳型连续碳化硅纤维（以下简称“纤维”）的分类和标记、要求、检验方法、检验规则、标志、标签和随行文件、包装运输和贮存。本文件适用于丝束规格为0.5 K和1 K的低氧高碳型连续碳化硅纤维的检验和交收，其他规格纤维的检验和交收参照使用。

摘要： 本文件规定了空间材料科学实验样品安瓿的设计与封装要求，描述了设计验证、检验、封装过程记录和状态确认的方法。
本文件适用于在空间实验平台（含舱内与舱外）或者星球表面等空间环境利用多功能高温炉开展的空间材料科学实验样品安瓿的设计与封装。

摘要： 本文件描述了对非金属材料进行空间辐射效应地面模拟的试验方法，包括模拟试验过程中的空间辐射环境特性、航天材料的性能、空间辐射模拟的要求、模拟辐射源以及可选模拟方法。本文件适用于非金属材料空间辐射效应的地面模拟试验。非金属材料包括漆、玻璃、陶瓷、聚合物、聚合物金属复合材料如金属基复合材料和层压材料等。

摘要： 本文件提供了技术背景、采购指南、工程程序和指南，以帮助组织进行航空航天和高性能电子系统的返工/修复，无论是采用传统合金(SnPb或无铅合金)或焊料与表面镀层结合物已装配的或已返工/修复的系统。本文件包含对已知影响和问题的回顾及返工/修复工艺，重点为维修技术人员执行任务提供技术架构。本文件提供了部件拆卸和更换的指南。本文件中术语“返工/修复”按3.1.29和3.1.30中的定义使用。本文件中包含的信息是基于发布时行业的当前知识。由于知识库的快速变化，本文件仅用于指导。

摘要： 本文件规定了在航空航天、国防和高可靠性产品的电子元器件管理计划（ECMP）的背景下，更换球栅阵列（BGA）元器件封装上焊球的要求。

摘要： 本文件规定了航空航天用热塑性聚氨酯弹性体中间膜的通用技术要求，描述了对应的试验方法。本文件适用于航空航天用热塑性聚氨酯弹性体中间膜(以下简称“TPU胶片”)的设计、制造、检验验收、运输与贮存。

摘要： 本文件提供了向无铅电子产品过渡的技术指南，主要包含技术路径、无铅焊料的一般性能、系统级使用环境、高性能电子产品试验、焊点可靠性、部件、印制电路板、印制电路板（PCB)/印制线路板（PWB)组装件、模块装配、导线/电缆装配、返工/修复、通用产品寿命试验、相似性分析等内容。〓本文件适用于航空航天、国防和高性能电子应用等领域，其他高性能和高可靠性行业参考使用。

摘要： 范围:本文件适用于航空航天工业、轨道交通、船舶等用途，温度使用范围为-55℃～180℃的国产间位芳纶纸蜂窝芯材（以下简称芯材）;主要技术内容:本文件规定了间位芳纶纸蜂窝芯材的术语和定义、芯材类别、规格和标记、原材料要求、技术要求、试验方法、检验规则、标识、包装、运输和贮存

摘要： 主要技术内容:本标准规定了一种使用特定夹持方式，通过发射钛合金弹片冲击聚合物基复合材料平板，从而获取其冲击侵彻抗性的测试方法，包括试验设备、试验条件、试件及冲击物、试验步骤、计算和试验报告等技术要求.

摘要： 1.1This test method covers the determination of the temperature below which solid hydrocarbon crystals form in aviation turbine fuels.1.2This test method is designed to cover the temperature range of −80 °C to 20 °C; however, 2003 Joint ASTM/IP Interlaboratory Cooperative Test Program mentioned in12.4has only demonstrated the test method with fuels having freezing points in the range of −42 °C to −60 °C.1.3The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.1.4This 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.For specific warning statements, see7.1,7.3, and7.5.1.5This 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. ====== Significance And Use ======5.1The freezing point of an aviation fuel is the lowest temperature at which the fuel remains free of solid hydrocarbon crystals. These crystals can restrict the flow of fuel through the fuel system of the aircraft. The temperature of the fuel in the aircraft tank normally decreases during flight depending on aircraft speed, altitude, and flight duration. The freezing point of the fuel must always be lower than the minimum operational fuel temperature.5.2Petroleum blending operations require precise measurement of the freezing point.5.3This test method produces results which have been found to be equivalent to Test MethodD2386and expresses results to the nearest 0.1 °C, with improved precision over Test MethodD2386. This test method also eliminates most of the operator time and judgment required by Test MethodD2386.5.4When specification requires Test MethodD2386, do not substitute this test method or any other test method.

摘要： 1.1This 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.1.2In 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.1.3Typical 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.1.4This 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.1.4.1Test 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 (seeFig. 1). This procedure requires access to only one side of the specimen. This procedure can be conducted by automated or manual means. Automated and manual test results may be analyzed in real time or recorded and analyzed later.FIG. 1Test Procedure A, Pulse Echo Apparatus Set-up for a Composite Panel (Left) and Metal Plate (Right) Using One-sided Access1.4.2Test Procedure B, Through Transmission (non-contacting and contacting)is a combination of two transducers. One transmits a longitudinal wave and the other receives the longitudinal wave in the range of 0.5 MHz to 20 MHz (seeFig. 2). This procedure requires access to both sides of the specimen. Typically, the signal transmitting and signal receiving transducers are perpendicularly aligned with each other. This is normally achieved using a yoke transducer holder arrangement, which attaches the two transducers to a single point but deploys them on opposite sides of the structure. Through transmission inspections are also permitted without the use of a yoke transducer holder. This is due to the capacity for improved manual alignment via the matrix array transducers, whereby the live C-scan display enables visual confirmation of accurate alignment, and facilitates re-alignment if needed. This procedure can be conducted by automated or manual means. Automated and manual test results may be imaged or recorded.FIG. 2Test Procedure B, Through Transmission Apparatus Set-up using Two-sided Access1.5Other contact methods such as angle-beam techniques using shear waves to characterize welds, or surface-beam techniques using Lamb waves to detect impact damage in composite panel structures are not covered.1.6This practice does not specify accept-reject criteria.1.7Units—The values stated in SI units are to be regarded as standard. The values given in parentheses after SI units are provided for information only and are not considered standard.1.8This 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.1.9This 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. ====== Significance And Use ======5.1The 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.5.2This practice provides guidelines for the application of longitudinal wave examination to the detection and quantitative evaluation of damage, discontinuities, and thickness variations in materials.5.3This 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.5.4MAUT 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.5.5The MAUT technique has proven utility in the inspection of multi-ply carbon-fiber reinforced laminates used in primary aircraft structures.115.6For ultrasonic testing of laminate composites and sandwich core materials using conventional UT equipment consult PracticeE2580. Consult PracticeE114for ultrasonic testing of materials by the pulse-echo method using straightbeam longitudinal waves introduced by a piezoelectric element (transducer) with diameters of 3.2 mm to 28.6 mm (⅛ in. to 1⅛ in.) in contact with the material being examined and usually presented in an A-scan display.5.7This practice is directed towards the evaluation of discontinuities detectable at normal beam incidence. If discontinuities or material integrity at other orientations are of concern such as through cracks and welds, alternate scanning techniques are required.5.8Test Procedure A, Pulse Echo—Pulsed energy is transmitted into materials, travels in a direction normal to the contact surface, and is reflected back to the search unit by discontinuity or boundary interfaces, which are parallel or near parallel to the contacted surface. These echoes return to the search unit, where they are converted from mechanical to electrical energy and are amplified by a receiver. The amplified echoes (signals) are displayed as A-, B- or C-scans, or three-dimensional renderings. Types of information that may be obtained from the pulsed-echo straight-beam practice are (1) apparent discontinuity size, (2) depth location of discontinuities, (3) material properties such as velocity of sound in the material, and similarly, the thickness of a material, and (4) the extent of bond and unbond (or fusion and lack of fusion) between two ultrasonic conducting materials if geometry and materials permit. In addition to detecting volumetric discontinuities such as delaminations (Fig. 3), ultrasonic thickness measurements can be made with MAUT search units in pulse-echo mode on basic shapes and products of many materials, and on precision machined parts, to determine wall thinning in process equipment caused by corrosion and erosion (Fig. 4).FIG. 3Detection of Delamination in Flat Panel Carbon-fiber Reinforced Composite Using Matrix Array Ultrasonic Testing Showing Typical A-, B- and C-Scans and A Three-dimensional Rendering (Pulse-Echo Method)FIG. 4Detection of Wall Thinning Corrosion in 3.5 mm Thick Aluminum Plate Using Matrix Array Ultrasonic Testing (Pulse-Echo Method)5.9Test Procedure B, Through Transmission—In TTU, a transducer on one side of a part transmits an ultrasonic pulse to an aligned receiving transducer on the other side (Fig. 2). Alignment between the two transducers is often accomplished by automation. Attenuation or absence of the pulse coming to the receiving transducer indicates the presence of a defect. Advantages of TTU over pulse-echo include less attenuation of sound energy, absence of transducer ringing, and less of an effect of defect orientation on transmitted signal. However, two-sided access is necessary, and like pulse-echo, vertical defects such as through cracks are difficult to detect. Applications include inspection of plate and bar stock after manufacturing, and detection of disbonds in materials with high attenuation properties that hinder sound propagation, such as multiple bond layers, honeycomb cores (Fig. 5), and foam cores.FIG. 5Detection of Disbond in A Sandwich Construction Consisting of A Graphite Fiber Reinforced Facesheet and An Aluminum Honeycomb Core Using Matrix Array Ultrasonic Testing (Through-Transmission Mode)5.10This practice does not discuss nonlinear resonant ultrasonic spectroscopy, ultrasonic spectral analysis, use of angle beams, transverse waves, and guided waves that can be used to assist in bond characterization in composites or sandwich constructions.12Air coupled ultrasonic inspection using MAUT search units to detect skin-to-core disbonds in sandwich constructions is also not discussed.

摘要： 1.1This specification covers hot isostatically-pressed, powder metallurgy, alloy steel piping components for use in pressure systems. Included are flanges, fittings, valves, and similar parts made to specified dimensions or to dimensional standards, such as in ASME Specification B16.5.1.2Several grades of alloy steels are included in this specification.1.3Supplementary requirements are provided for use when additional testing or inspection is desired. These shall apply only when specified individually by the purchaser in the order.1.4This specification is expressed in both inch-pound units and in SI units. Unless the order specifies the applicable “M” specification designation (SI units), however, the material shall be furnished to inch-pound units.1.5The values stated in either inch-pound units or SI units are to be regarded separately as the standard. Within the text, the SI units are shown in brackets. The values stated in each system are not exact equivalents; therefore, each system must be used independently of the other. Combining values from the two systems may result in nonconformance with the specification.1.6The following safety hazards caveat pertains only to test methods portions,8.1,8.2, and9.5 –9.7of this specification: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 to determine the applicability of regulatory limitations prior to use.1.7This 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.

摘要： 1.1These definitions cover generic terms, including terms of commercial importance, that appear in one or more standards on composites containing high-modulus (greater than 20 GPa (3 × 106psi)) fibers.1.2The definitions cover, in most cases, special meanings used in the composites industry. No attempt has been made to include common meanings of the same terms as used outside the composites industry.1.3Definitions included have, in general, been approved as standard.1.4This 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.

摘要： 1.1This guide summarizes the standard test methods available for determining physical and mechanical characteristics of interlayer materials used in multi-ply aerospace transparent enclosures.1.2Interlayer materials are used to laminate glass-to-glass, glass-to-plastic, and plastic-to-plastic. Interlayer materials are basically transparent adhesives with high-quality optical properties. They can also serve as an energy absorbing medium, a fail-safe membrane to contain cockpit pressure and to prevent entry of impact debris; a strain insulator to accommodate different thermal expansion rates of members being laminated and as an adherent to prevent spalling of inner surface ply material fragments. The relative importance of an interlayer characteristic will be a function of the prime use it serves in its particular application.1.3This guide, as a summary of various methods in Section2, is intended to facilitate the selection of tests that can be applied to interlayer materials.1.4The test methods listed are for use in determining basic design characteristics and in assuring lot-to-lot uniformity of the materials being tested except as noted in3.3.1.5This 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.1.6This 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. ====== Significance And Use ======3.1This guide is intended for use by material suppliers, aircraft transparent enclosure fabricators, airframe manufacturers, government agencies, and others that may become involved in the testing of transparent interlayer materials. These test methods provide data on both individual interlayer materials and material combinations commonly used in the fabrication of aerospace transparent enclosures and provide a means of evaluating the performance of one interlayer material against another.3.2Primary characteristics and their long-term stability are critical to the performance of an interlayer material. Basic tests define the as-manufactured material characteristics of the interlayer material. Aging procedures provide for representative exposure to environments that induce changes in material characteristics. Tests performed before and after ageing exposure provide a means of estimating the potential useable life-span of an interlayer material or to compare the durability of one interlayer material with another.3.3When employing these test methods for the comparison of interlayer materials after exposure to selected environmental conditions, the user shall be aware that many factors influencing degradation due to weathering vary from one location and exposure period to another location and exposure period. For direct weathering comparisons, the interlayer materials to be compared shall be subjected to the exposure and have the tests performed at the same time. It is emphasized that the test values obtained under these simultaneously applied conditions are for comparative use and their use as design characteristics shall be made with caution.3.4The test methods listed include those considered critical to the performance of aircraft transparent enclosures. The user is advised to use the latest revision of any test method.

摘要： 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.

摘要： 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.

摘要： 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.

摘要： 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.