V13 航空与航天用非金属材料 标准查询与下载

BS EN 2757:2011 航空航天系列.结构粘合系统.试验方法.底漆的干式和灼烧残渣的测定

This European Standard defines the general requirements for the determination of drying residues (solid content) (Method A) and residues after ignition (corrosion inhibitor content) (Method B) of primers for aerospace applications.

Aerospace series. Structural adhesives system. Test method. Determination of the drying and ignition residues of primers

BS EN 4160:2011 航空航天系列.涂料和清漆.热暴露效应的测定

This European Standard specifies the method of test for determining the resistance of paints and varnishes to the effects of heat or cold within the limits of − 50 °C to 200 °C. The test procedure assesses the resistance of paint coatings, varnishes or related products to changes of gloss, colour, blistering, cracking and/or detachment from the substrate as a result of exposure to elevated or sub-ambient temperature. The procedure is applicable to products intended for use in aerospace applications.

Aerospace series. Paints and varnishes. Determination of the effect of thermal exposure

SAE AMS3193D-2011 中等温度和极低温度的闭孔硅橡胶海绵

This specification covers a silicone rubber sponge in the form of sheet, strip, extrusions, and molded shapes. This sponge has been used typically for general applications requiring closed-cell, medium sponge rubber that will be flexible from -166 to +401 degrees F (-110 to +205 degrees C) , but usage is not limited to such applications. Compression set may be high at the higher temperature.

Silicone Rubber Sponge, Closed Cell, Medium, Extreme Low Temperature

SAE AMS3194D-2011 坚定的极端低温闭孔硅橡胶海绵

This specification covers a silicone rubber sponge in the form of sheet, strip, extrusions, and molded shapes. This sponge has been used typically for general applications requiring closed-cell, firm sponge rubber that will be flexible from -166 to +401 degrees F (-110 to +205 degrees C), but usage is not limited to such applications. Compression set may be high at the higher temperature.

Silicone Rubber Sponge, Closed Cell, Firm, Extreme Low Temperature

SAE AMS3195F-2011 中等硅泡沫橡胶闭孔泡沫

This specification covers a silicone rubber sponge in the form of sheet, strip, extrusions, and molded shapes. This product has been used typically for general applications requiring closed-cell, medium sponge rubber that will be flexible from -103 to +401 degrees F (-75 to +205 degrees C) , but usage is not limited to such applications. Compression set may be high at the higher temperature.

Silicone Rubber Sponge Closed Cell, Medium

SAE AMS3220G-2011 55-65耐湿通用合成橡胶

This specification covers a synthetic rubber in the form of sheet, strip, tubing, extrusions, and molded shapes. Primarily for packing and sealing joints which come in contact with aircraft fuels, hot petroleum-base lubricating oils, and ethylene glycol from -20 to +220 degrees F (-29 to +104 degrees C) . This material has fair resistance to all fluids listed. Where better resistance to a particular fluid is required, use the AMS for material compounded specifically for good resistance to that fluid.

Rubber, Synthetic General Purpose, Fluid Resistant, 55-65

SAE AS5272E-2011 抗腐蚀加热固化固体薄膜润滑剂采购规格

This SAE Aerospace Standard (AS) establishes the requirements for heat cured solid film lubricants. For other general or high temperature applications, see AS1701.

Lubricant, Solid Film, Heat Cured, Corrosion Inhibiting, Procurement Specification

DIN EN 2826:2011 航空航天系列.辐射热和火焰影响下的非金属材料燃烧行为.烟雾中气体成分的测定.德文和英文版本EN 2826-2011

Aerospace series - Burning behaviour of non metallic materials under the influence of radiating heat and flames - Determination of gas components in the smoke; German and English version EN 2826:2011

SAE AMS3175A-2011 非铬酸盐表面预处理涂装前

This specification establishes the performance requirements for non-chromated materials used for surface preparation of metallic aircraft surfaces prior to applying organic coatings. Pretreatment materials qualified to this specification may be used on metallic surfaces that are subsequently painted. These include, but are not limited to, external and internal aircraft surfaces,off-aircraft part surfaces, and aircraft surfaces undergoing touch-up/repairs.

Non-Chromated Surface Pretreatment Prior to Painting

SAE AMS-S-83318B-2011 整体油箱和燃料电池腔快速修复式低温固化聚硫型密封胶

This specification covers two-component polysulfide sealing compounds, temperature resistant, for use from -65 to 250 °F (-54 to 121 °C), low temperature curing from 20 °F (-13 °C) minimum, for quick repair of integral fuel tanks and fuel cell cavities. During application, sealing compound shall exhibit suitable, fluid consistency.

Sealing Compound, Polysulfide Type, Low Temperature Curing, Quick Repair, Integral Fuel Tanks and Fuel Cell Cavities

NF L06-451*NF EN 3238:2011 航空航天系列.非金属材料.试验方法.电线和铆钉的抗剪试验

Aerospace series - Metallic materials - Test method - Shear test for wires and rivets.

SAE AMS3970A-2011 120℃(250℉)真空固化碳纤维织物修补预浸材料.第0部分:引言

This document (echnical Specification) gives information about qualification rules and the relation between the different specification parts involved, such as the Technical Specification (TS), Material Specification (MS), and Purchasing Specification (PS). The link to the material qualification and qualified products is presented. This document is only applicable to epoxy or modified epoxy resin prepreg systems used for repair of carbon fiber composite structures and companion non-structural glass fiber prepreg. Generally, an epoxy or modified epoxy resin film adhesive will be part of the prepreg system for co-cure bonding applications.

Carbon Fiber Fabric Repair Prepreg, 120°C (250°F) Vacuum Curing Part 0 - Introduction

SAE AMS3970/6-2011 120℃(205\MDF)真空固化碳纤维织物修补预浸材料.第6部分:材料规范:修补平纹棉布190 g/m2用碳纤维织物增强环氧树脂预浸材料,修补和非结构玻璃纤维增强环氧树脂预浸材料105 g/m2用胶膜

This Material Specification defines the requirements of carbon fiber reinforced epoxy prepreg for repair, 120 °C (250 °F) Vacuum curing, Plain Weave Fabric, 193 g/m2 and a companion non-structural glass fiber fabric reinforced epoxy prepreg, 105 g/m2, qualified according to AMS3970/1 and AMS3970/2 for aerospace application. The prepreg system may include an epoxy film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests. If included, the requirements to be met by the adhesive are also defined in this document.

Carbon Faber Fabric Repair Prepreg, 120 °C (205 \MDF)Vacuum Curing - Part 6: Material Specification: Carbon Fiber Fabric Reinforced Epoxy Prepreg for Repair, Plain Weave Fabric, 190 g/m<(hoch)2>, Adhesive Film for Repair and Non-Structural Glass Fiber Fab

SAE AMS3970/1A-2011 120℃(250℉)真空固化碳纤维织物修补预浸材料.第1部分:一般要求

AMS 3970/1 gives information about the technical requirements and qualification procedure for carbon fiber fabric epoxy prepreg and a companion non-structural glass prepreg used for repair of carbon fiber reinforced epoxy structures. The prepreg system may include a film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests.

Carbon Fiber Fabric Repair Prepreg, 120°C (250°F) Vacuum Curing Part 1 - General Requirements

SAE AMS3970/3A-2011 120℃(250℉)真空固化碳纤维织物修补预浸材料.第3部分:碳预浸材料用采购规范

The PS, AMS3970/3 specifies the batch release and delivery requirements for carbon fiber fabric epoxy prepreg used for repair. This specification relates to qualified carbon fiber fabric epoxy prepreg listed in the associated PRI QPL AMS3970.

Carbon Fiber Fabric Repair Prepreg, 120°C (250°F) Vacuum Curing Part 3 - Purchasing Specification for Carbon Prepreg

SAE AMS3970/5-2011 120℃(250℉)真空固化碳纤维织物修补预浸材料.第5部分:配套非结构玻璃纤维织物预浸材料的采购规范

The PS, AMS3970/5, specifies the batch release and delivery requirements for the companion non-structural glass fiber fabric prepreg. This specification relates to qualified companion non-structural glass fiber fabric prepreg listed in the associated PRI QPL AMS3970.

Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing - Part 5: Purchasing Specification for Companion Non-Structural Glass Fiber Fabric Prepreg

SAE AMS3970/2A-2011 碳纤维织物预浸料维修,120℃(250 ℉)真空固化第2部分.资格认证程序,碳纤维,织物预浸料,胶膜和非结构性玻璃预浸

AMS 3970/2 gives specific information about the qualification program for carbon fiber reinforced epoxy structural repair prepreg systems, applicable for 120 °C (250 °F) vacuum curing. The prepreg system may include an epoxy film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests.

Carbon Fiber Fabric Repair Prepreg, 120°C (250°F) Vacuum Curing Part 2 - Qualification Program for Fiber, Fabric, Carbon Prepreg, Film Adhesive and Non-Structural Glass Prepreg

BS EN 2826:2011 航空航天系列.受火焰和辐射热影响的非金属材料的燃烧行为.烟雾中毒气含量测定

This European Standard defines a test method to determine the concentration of certain gas components due to pyrolitic decomposition of solid materials and composite materials under the influence of radiant heat only or with simultaneous flame application. NOTE 1 The gas components in the smoke are determined according to the specific environmental and test conditions defined in EN 2824 and this standard. No studies have been made up to now to determine whether the results can be transferred to different conditions, particularly to actual fire conditions. The inhalatory toxical risk and irritancy affect cannot be assessed by merely measuring the concentration of individual gas components in the smoke. NOTE 2 The burning behaviour and consequently the gas components in the smoke of aerospace materials are not only influenced by the type of material but also to a large extent by the configuration, the specific surface and mass, the combination with other materials, the means of joining as well as the processing technique. NOTE 3 These influences shall be taken into account in the preparation of tests, the selection of test specimens and the interpretation of test results.

Aerospace series. Burning behaviour of non metallic materials under the influence of radiating heat and flames. Determination of gas components in the smoke

SAE AMS-S-8802C-2011 高粘合性整体油箱和燃料电池腔耐热密封剂

This specification covers temperature resistant, two-component synthetic rubber compounds of the polysulfide type for sealing and repairing integral fuel tanks and fuel cell cavities, for continuous service use from -65 to +250 °F (-54 to 121 °C).

Sealing Compound, Temperature Resistant, Integral Fuel Tanks and Fuel Cell Cavities, High Adhesion

ASTM D3800M-11 高模量纤维密度的标准试验方法

Fiber density is useful in the evaluation of new materials at the research and development level and is one of the material properties normally given in fiber specifications. Fiber density is used to determine fiber strength and modulus both of a fiber bundle and an individual filament. These properties are based on load or modulus slope over an effective area. Fiber density may be used with lineal mass of the fiber to give an approximation of effective tow area. Tow area divided by the average number of filaments in a tow gives an approximation of the effective area of an individual filament. Fiber density is used as a constituent property when determining reinforcement volume and void volume based on reinforcement mass and laminate density.1.1 This test method covers the determination of the density of high-modulus fibers and is applicable to both continuous and discontinuous fibers. 1.2 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard. 1.3 This standard may involve hazardous materials, operations, and equipment. 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. See Section 9 for additional information.

Standard Test Method for Density of High-Modulus Fibers