49.050 航空航天发动机和推进系统 标准查询与下载

GB/T 40536-2021 航天器剩余推进剂排放设计要求

本文件规定了航天器剩余推进剂排放的设计依据,设计准则,设计内容和程序等一般设计要求,详细设计要求等内容，本文件适用于航天器的推进剂及高压气体的主动排放设计和被动排放设计。航天器上其他工质的排放设计可参照执行。

Design requirements for residual propellant venting of Spacecraft

GB/T 31767.1-2015 飞机导管和管路 V型卡箍连接凸缘的轮廓尺寸

Aircraft ducting and piping—Profile dimension for flanges of V-band couplings

GB/T 31767-2015 飞机管道和管路 V型卡箍连接凸缘的轮廓尺寸

本标准规定了用于飞机英制管道和管路V型卡箍连接凸缘的轮廓尺寸，包括： --轻型实心凸缘轮廓； --中型实心凸缘轮廓； --重型实心凸缘轮廓； --窄钣金凸缘轮廓； --宽钣金凸缘轮廓； --宽实心凸缘轮廓； --宽钣金配实心凸缘轮廓。

Aircraft ducting and pipling.Profile dimensions for flanges of V-band couplings

ASTM F3066/F3066M-23 飞机动力装置安装危险缓解标准规范

1.1  This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes. 1.2  The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. 1.3  Units— The values stated are SI units followed by imperial units in brackets. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard. 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.

Standard Specification for Aircraft Powerplant Installation Hazard Mitigation

ASTM F2840-14(2023) 轻型运动飞机用电力推进装置的设计和制造标准实施规程

1.1 This practice covers minimum requirements for the design and manufacture of Electric Propulsion Units (EPU) for light sport aircraft, VFR use. The EPU shall as a minimum consist of the electric motor, associated controllers, disconnects and wiring, an Energy Storage Device (ESD) such as a battery or capacitor, or both, and EPU monitoring gauges and meters. Optional onboard charging devices, in-flight charging devices or other technology may be included. 1.2 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. 1.3 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.

Standard Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft

ASTM F3005-22 小型无人机系统（sUAS）用电池的标准规范

1.1 This standard defines the requirements for batteries used in small Unmanned Aircraft Systems (sUAS). 1.2 This standard does not define requirements for the systems in which sUAS battery packs may be utilized. 1.3 This standard is subordinate to Specification F2910. 1.4 If allowed by a nation’s GAA, certain sUAS may be exempt from this standard and may use commercial off-theshelf (COTS) batteries in non-safety-critical payloads (lithium chemistries may not be exempted). Air transport regulations still shall be adhered to when air transport is used for COTS cells or batteries in bulk. 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 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.

Standard Specification for Batteries for Use in Small Unmanned Aircraft Systems (sUAS)

ASTM F3239-22a 飞机电力推进系统标准规范

1.1 This specification addresses airworthiness requirements for the design and installation of electric propulsion systems for aeroplanes. Hybrid-electric propulsion systems are addressed implicitly unless explicitly stated otherwise. This specification was written with the focus on electric propulsion systems with conventional system layout, propulsion characteristics, and operation. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. 1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/ COMMITTEE/F44.htm). Annex A1 maps the Means of Compliance described in this specification to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later. 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.

Standard Specification for Aircraft Electric Propulsion Systems

ASTM E2104-22 先进航空和涡轮材料和部件的射线照相检验的标准实施规程

1.1 This practice establishes the minimum requirements for radiographic examination of metallic and nonmetallic materials and components used in designated applications such as gas turbine engines and flight structures. 1.2 The requirements in this practice are intended to control the radiographic process to ensure the quality of radiographic images produced for use in designated applications such as gas turbine engines and flight structures; this practice is not intended to establish acceptance criteria for material or components. When examination is performed in accordance with this practice, engineering drawings, specifications, or other applicable documents shall indicate the acceptance criteria. 1.3 All areas of this practice may be open to agreement between the cognizant engineering organization and the supplier, or specific direction from the cognizant engineering organization. 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.

Standard Practice for Radiographic Examination of Advanced Aero and Turbine Materials and Components

ASTM D7685-11(2022) 航空衍生和航空燃气涡轮发动机轴承铁磁和非铁磁磨损碎屑测定和诊断用直列全流感应传感器的标准实施规程

1.1 This practice covers the minimum requirements for an in-line, non-intrusive, through-flow oil debris monitoring system that monitors ferromagnetic and non-ferromagnetic metallic wear debris from both industrial aero-derivative and aircraft gas turbine engine bearings. Gas turbine engines are rotating machines fitted with high-speed ball and roller bearings that can be the cause of failure modes with high secondary damage potential. (1)2 1.2 Metallic wear debris considered in this practice range in size from 120 µm (micron) and greater. Metallic wear debris over 1000 µm are sized as over 1000 µm. 1.3 This practice is suitable for use with the following lubricants: polyol esters, phosphate esters, petroleum industrial gear oils and petroleum crankcase oils. 1.4 This practice is for metallic wear debris detection, not cleanliness. 1.5 The values stated in SI units are to be regarded as standard. The values given in parentheses are provided for information only. 1.6 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. 1.7 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.

Standard Practice for In-Line, Full Flow, Inductive Sensor for Ferromagnetic and Non-ferromagnetic Wear Debris Determination and Diagnostics for Aero-Derivative and Aircraft Gas Turbine Engine Bearing

ASTM F3239-22 飞机电力推进系统标准规范

Standard Specification for Aircraft Electric Propulsion Systems

T/CSAA 16-2022 涡轮叶片内部冷却通道旋转状态 铜块法换热测试方法

4 一般要求　 4.1 试验目的　 4.2 试验任务书　 4.3 试验大纲　 4.4 试验原理与方法　 4.5 试验件　 4.6 试验设备　 4.7 测量参数精度　 4.8 测量参数及测点布置　 4.9 测试中断及故障处理要求　 5 试验项目及试验程序　 5.1 试验项目　 5.2 试验程序　 6 试验数据录取与处理　 6.1 试验数据记录要求　 6.2 试验数据处理与分析　 7 误差分析　 7.1 直接误差分析　 7.2 间接误差分析　 8 试验结果评定　 8.1 试验结果的评定内容　 8.2 试验参数整理　 8.3 试验结果分析内容　 9 试验报告编写　

Test method of copper plate method heat transfer in rotating state of internal cooling channel of turbine blade

T/YH 1023-2022 微小卫星推进模块通用要求

本文件规定了微小卫星推进模块的通用技术要求，涉及技术要求、质量保证规定和交货准备等方面。该标准内容主要包括模块结构、机械接口、电接口、安全性要求、试验要求、环境要求等。 本文件适用于微小卫星的推进模块的订购、设计、生产、试验、检验和验收。

General requirements for microsatellite propulsion modules

T/CSAA 15-2021 航空发动机整体盘制造工艺控制要求

4 一般要求　 5 工艺流程　 5.1 工艺设计　 5.2 加工步骤　 5.3 典型工序控制要求　 6 标注信息提取　 6.1 关键尺寸信息　 6.2 特种工艺信息　 6.3 检测信息　 6.4 三维模型　 7 关键尺寸及控制要求　 7.1 叶型　 7.2 定位面　 7.3 制造技术要求　 7.4 工艺参数选择　 7.5 检测要求　

Requirements for manufacturing process control of aeroengine integral disk

T/CSAA 14-2021 航空发动机整体盘尺寸标注要求

4 基本原则　 5 标注内容　 5.1 基准　 5.2 尺寸　 5.3 形位　 5.4 表面质量　 5.5 制造控制信息　 5.6 技术条件　 6 标注形式　 6.1 二维图样　 6.2 三维模型　 6.3 图样布局　 7 标注位置　 7.1 主视图　 7.2 局部视图　 7.3 其他关键信息　 附　录　A  （资料性附录） 发动机整体盘零件标注示例　

Dimension requirements of aeroengine integral disk

ASTM F3063/F3063M-21 飞机燃料贮存和输送的标准规范

1.1?This specification covers minimum requirements for the design and integration of Fuel Storage and Delivery system installations for aeroplanes. 1.2?This specification is applicable to aeroplanes as defined in the F44 terminology standard. 1.3?The applicant for a design app

Standard Specification for Aircraft Fuel Storage and Delivery

ASTM F3338-21 通用航空飞机用电动发动机设计的标准规范

1.1?This specification covers minimum requirements for the design of electric engines. 1.2?Distributed propulsion is not excluded; however, additional requirements will be needed to address the additional issues that distributed propulsion can create. Some of those issues may i

Standard Specification for Design of Electric Engines for General Aviation Aircraft

ASTM F3065/F3065M-21a 飞机螺旋桨系统安装的标准规范

1.1 This specification addresses the airworthiness requirements for the installation and integration of propeller systems. 1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard. 1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. Annex A1 maps the Means of Compliance described in this specification to EASA CS-23, amendment 5, or later, and FAA 14 CFR Part 23, amendment 64, or later. 1.4 Units—The values stated are SI units followed by Imperial units in square brackets. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined. 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 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.

Standard Specification for Aircraft Propeller System Installation

T/CSAA 10-2021 民用大涵道比涡扇发动机压气机气动性能 试验规范

4 试验原理及方法 5 试验设备及要求. 6 试验目的、项目. 6.1试验目的. 6.2试验项目. 7 试验策划与实施. 7.1试验流程图. 7.2试验输入 7.3试验可行性评估 7.4试验文件准备 7.5试验设备准备 7.6试验件领用及检查 7.7试验件安装 7.8试验准备总结及评审 7.9试验实施过程 7.10试验异常及处理 8 试验结果分析与评定. 9 试验报告编写 附录 A（资料性）试验流程图  附录 B (资料性) 试验数据处理方法

Specification for aerodynamic test of high pressure compressors for commercial high bypass ratio turbofan Aero-engines

T/CSAA 12-2021 民用大涵道比涡扇发动机高压压气机静子 叶片静强度、振动及寿命分析指南

4 分析依据、准则 4.1 分析依据. 4.2 分析准则 5 分析过程. 5.1 坐标系定义. 5.2 有限元模型建立 5.3 有限元计算. 5.4 静强度分析 5.5 振动分析 5.6 寿命分析 6 分析报告 6.1 分析报告内容 6.2 分析报告要素起草.

Guide for static strength, vibration, and life analysis of stator vane of high pressure compressor for commercial high bypass ratio turbofan Aero-engines

T/CSAA 11-2021 民用大涵道比涡扇发动机高压压气机气动 性能试验测点选取布置规范

4 测点选 4.1 一般要求 4.2 气动性能参数测点选取. 4.3 安全监测参数测点选取. 5 测点布置 5.1 气动性能参数测点布置. 5.2 安全监测参数测点布置. 5.3 其他参数测点布置.. 6 测点维护

Specification of instrumentation selection and arrangement of aerodynamic test for high pressure compressors of commercial high bypass ratio turbofan Aero-engines