航空航天发动机和推进系统

摘要： 本文件描述了航空发动机碳烟颗粒排放的测量方法，规定了航空发动机碳烟颗粒排放测量的测量对象、测量系统布局、测量条件、试剂与材料、仪器设备、测量程序、测量数据处理、质量保证和控制，以及测量报告内容。
本文件适用于航空发动机（以下简称“发动机”）碳烟颗粒排放的测量。

摘要： 本文件规定了采用纯电方式驱动的平流层飞艇推进系统的组成、功能、性能、接口、环境适应性、安全性、可靠性、维修性、测试性、保障性等技术要求以及相应的验证试验要求。
本文件适用于采用纯电方式驱动的平流层飞艇推进系统的设计与制造，其他采用纯电方式的飞艇、高空气球和太阳能飞机的推进系统参照使用。

摘要： 1.1This 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.1.2This 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.1.3This 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 specification provides designers and manufacturers of electric propulsion for light sport aircraft design references and criteria to use in designing and manufacturing EPUs.3.2Declaration of compliance is based on testing and documentation during the design, ground testing and flight testing of the EPU by the manufacturer or under the manufacturers’ guidance.3.3Manufacturers of the EPUs are encouraged to review and incorporate appropriate standards and lessons learned from ground based systems as documented in SAE J2344 and EASA CRI F-58 (seeAppendix X2).3.4Electric aircraft may contain potentially hazardous level of electrical voltage or current. It is important to protect persons from exposure to this hazard. Under normal operating conditions, adequate electrical isolation is achieved through physical separation means such as the use of insulated wire, enclosures, or other barriers to direct contact. There are conditions or events that can occur outside normal operation that can cause this protection to be degraded. Some means should be provided to detect degraded isolation or ground fault. In addition, processes or hardware, or both, should be provided to allow for controlled access to the high voltage system for maintenance or repair. A number of alternative means may be used to achieve these electrical safety goals including automatic hazardous voltage disconnects, manual disconnects, interlock systems, special tools and grounding. The intention of all these means is either to prevent inadvertent contact with hazardous voltages or to prevent damage or injury from the uncontrolled release of electric energy. Lightning strikes are not addressed in this Standard Practice because LSA aircraft are limited to VMC flight only.

摘要： 1.1This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.1.2The 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.1.3Units—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.1.4This 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.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.

摘要： 1.1The purpose of this guide is to address the basic fundamental subject knowledge, task performance, and task knowledge activities and functions for power plants professionals.1.2This 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.1.3This 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 ======4.1The guide is intended to be used to assess competencies of qualified individuals who wish to become certified as a Powerplant Technician through any certified program.4.2The guide is intended to be used in concert with a certification provider’s structure and materials for management, exam delivery, and candidate preparation.4.3Each section is categorized into theory, inspection, maintenance/service, troubleshooting, repair, and overhaul with each of these categories having a relevant competency level assigned (referenceTable 1).

摘要： 主要技术内容: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

摘要： 1.1This specification covers the establishment of the minimum requirements for the design, testing, and quality assurance of fixed-pitch or ground adjustable propellers for light sport aircraft. These propellers are used on light aircraft, and could be used with engines conforming to PracticeF2339.1.1.1When applying the additions provided inAppendix X1, this specification also covers the establishment of the minimum requirements for the design, testing and quality assurance of in-flight adjustable propellers for light-sport aircraft.1.2This specification is intended for use by manufacturers of propellers for light sport aircraft.1.3This specification does not address the airframe installation requirements for propellers.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 to determine the applicability of regulatory limitations prior to use.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.

摘要： 1.1This standard defines the requirements for batteries used in small Unmanned Aircraft Systems (sUAS).1.2This standard does not define requirements for the systems in which sUAS battery packs may be utilized.1.3This standard is subordinate to SpecificationF2910.1.4If allowed by a nation’s GAA, certain sUAS may be exempt from this standard and may use commercial off-the-shelf (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.1.5This 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.

摘要： 1.1This 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)21.2Metallic 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.1.3This practice is suitable for use with the following lubricants: polyol esters, phosphate esters, petroleum industrial gear oils and petroleum crankcase oils.1.4This practice is for metallic wear debris detection, not cleanliness.1.5The values stated in SI units are to be regarded as standard. The values given in parentheses are provided for information only.1.6This 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.1.7This 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. ====== Significance And Use ======4.1This practice is intended for the application of in-line, full-flow inductive wear debris sensors. According to(1), passing the entire lubrication oil flow for aircraft and aero-derivative gas turbines through a debris-monitoring device is a preferred approach to ensure sufficient detection efficiency.4.2Periodic sampling and analysis of lubricants have long been used as a means to determine overall machinery health(2). The implementation of smaller oil filter pore sizes for machinery operating at higher rotational speeds and energies has reduced the effectiveness of sampled oil analysis for determining abnormal wear prior to severe damage. In addition, sampled oil analysis for equipment that is remote or otherwise difficult to monitor or access is not practical. For these machinery systems, in-line wear debris sensors can be very useful to provide real-time and near-real-time condition monitoring data.4.3In-line full-flow inductive debris sensors have demonstrated the capability to detect and quantify both ferromagnetic and non-ferromagnetic metallic wear debris. These sensors record metallic wear debris according to size, count, and type (ferromagnetic or non-ferromagnetic). Sensors are available for a variety of oil pipe sizes. The sensors are designed specifically for the protection of rolling element bearings and gears in critical machine applications. Bearings are key elements in machines since their failure often leads to significant secondary damage that can adversely affect safety, operational availability, or operational/maintenance costs, or a combination thereof.4.4The main advantage of the sensor is the ability to detect early bearing damage and to quantify the severity of damage and rate of progression of failure towards some predefined bearing surface fatigue damage limiting wear scar. Sensor capabilities are summarized as follows:4.4.1In-line full flow non-intrusive inductive metal detector with no moving parts.4.4.2Detects both ferromagnetic and non-ferromagnetic metallic wear debris.4.4.3Detects 95 % or more of metallic wear debris above some minimum particle size threshold.4.4.4Counts and sizes wear debris detected.4.5Fig. 1presents a widely used diagram(2)to describe the progress of metallic wear debris release from normal to catastrophic failure. It must be pointed out that this figure summarizes metallic wear debris observations from all the different wear modes that can range from polishing, rubbing, abrasion, adhesion, grinding, scoring, pitting, spalling, etc. As mentioned in numerous references(1-11), the predominant failure mode of rolling element bearings is spalling or macro pitting. When a bearing spalls, the contact stresses increase and cause more fatigue cracks to form within the bearing subsurface material. The propagation of existing subsurface cracks and creation of new subsurface cracks causes ongoing deterioration of the material that causes it to become a roughened contact surface as illustrated inFig. 2. This deterioration process produces large numbers of metallic wear debris with a typical size range from 100 to 1000 microns or greater. Thus, rotating machines, such as gas turbines and transmissions, which contain rolling element bearings and gears made from hard steel tend to produce this kind of large metallic wear debris that eventually leads to failure of the machines.FIG. 1Wear Debris CharacterizationFIG. 2Typical Bearing Spall4.6In-line wear debris monitoring provides a more reliable and timely indication of bearing distress for a number of reasons:4.6.1Firstly, bearing failures on rotating machines tend to occur as events often without sufficient warning and could be missed by means of only periodic inspections or data sampling observations.4.6.2Secondly, since it is the larger wear metallic debris that are being detected, there is a lower probability of false indication from the normal rubbing wear that will be associated with smaller particles.4.6.3Thirdly, build or residual debris from manufacturing or maintenance actions can be differentiated from actual damage debris because the cumulative debris counts recorded due to the former tend to decrease while those due to the latter tend to increase.4.6.4Fourthly, bearing failure tests have shown that wear debris size distribution is independent of bearing size.(2-5)and(11).

摘要： 1.1This 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.1.2The 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.1.3All 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.1.4This 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.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 ======4.1The requirements for radiographic examination in this practice are applicable to all types of metallic and nonmetallic material used in designated applications such as gas turbines and flight structures.4.2This practice establishes the basic parameters for the application and control of the radiographic process. This practice may be specified on an engineering drawing, specification, or contract; however, it is not a detailed radiographic technique and must be supplemented. Section7and PracticesE1030/E1030MandE1032contain information to help develop detailed radiographic techniques.

摘要： 1.1This 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.1.2An 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 A1maps 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.1.3This 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.1.4This 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 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.1.2An 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 A1maps 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.1.3This 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.1.4This 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： 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。

摘要： 范围:本文件规定了航空发动机零件整体盘尺寸标注的标注内容、标注形式、标注位置以及关键信息表达要求。本文件适用于航空发动机整体盘厂际合作过程中零件尺寸标注、制造与检测识图等协调;主要技术内容: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

摘要： 范围:本标准规定了航空发动机零件整体盘航空发动机零件整体盘工艺加工的基本流程、标注信息的提取要求、关键控制尺寸范围以及对应的工艺控制方法等。本标准适用于航空发动机整体盘厂际合作过程中零件工艺设计、制造与检测控制等协调;主要技术内容: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

摘要： 范围:本文件确立了民用大涵道比涡扇发动机压气机气动性能试验方法，并规定了试验原理、试验设 备、试验项目、试验策划与实施、试验结果分析与评定及试验报告编制等内容。 本文件适用于民用大涵道比涡扇发动机压气机气动性能试验，其他领域相类似的压气机部件气 动性能试验参照使用;主要技术内容: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

摘要： 范围:本文件提供了民用大涵道比涡扇发动机高压压气机静子叶片静强度、振动及寿命分析的分析依 据、分析要求、分析报告要求等方面的指导。 本文件适用于民用大涵道比涡扇发动机高压压气机静子叶片静强度、振动及寿命分析工作；高 压压气机进口导向叶片的结构形式、载荷环境、分析方法参照使用;主要技术内容: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.