49.050 航空航天发动机和推进系统 标准查询与下载

SAE AS3084A-2012 预成型包装.AMS 7280.密封

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist.

Packing, Preformed - AMS 7280 - Seal

SAE ARP1401B-2012 飞机燃料系统和组件结冰试验

This Aerospace Recommended Practice (ARP) covers a brief discussion of the icing problem in aircraft fuel systems and different means that have been used for icing. Fuel preparation procedures and icing tests for aircraft fuel system and components are proposed herein as a recommended practice to be used in the aircraft industry for fixed wing aircraft and their operational environment only. In the context of this ARP, the engine (and APU) is not considered to be a component of the aircraft fuel system, for the engine fuel system is subjected to icing tests by the engine/APU manufacturer for commercial and specific military applications. This ARP is written mostly to address fuel system level testing. It also provides a means to address the requirements of 14 CFT 23.951(c) and 25.951(c). Some of the methods described in this document can be applied to engine and APU level testing or components of those application domains. This revision does not completely address new developments in ice accretion resulting from internal flow in tubing. This will be addressed ina future revision when more experimental data is available. Some background information on the topic is planned to be available in AIR 790.

Aircraft Fuel System and Component Icing Test

SAE AIR4065A-2012 推进器/八叶螺旋桨飞行推力测定

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. AIR 4065, "Propeller/Propfan In-Flight Thrust Determination" addresses steady state propeller thrust as applied to aircraft which are usually powered by gas turbine engines. It includes theory, examples, and methods which have been used. Specifically two methods are discussed, the "J" or traditional J,Cp,Ct,ν method including the SBAC variation and a new method we call the "Theta" method which is dependent on knowing blade angle, power/torque and flight Mach number. Implementation guidelines are offered as well as overall approaches to flight testing. Appendices include expansions on theory and testing as well as examples.

Propeller/Propfan In-Flight Thrust Determination

SAE AIR4979A-2012 基于北大西洋公约组织(NATO)航天研发顾问团(AGARD)一致性引擎检测规程的引擎检测中不确定性测量的评估

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. The primary objective of this document is to describe the systematic and random measurement uncertainties which may be expected when testing gas turbine engines in a range of different test facilities. The documentation covers a "traditional" method for estimating pretest uncertainties and a "new" method for computing and comparing posttest uncertainties. To determine these posttest uncertainties, data generated during the AGARD Uniform Engine Test Program (UETP) were analyzed and compared to the pretest estimates. The proposed procedure provides a mechanism for determining the expected accuracy of test results obtained from facilities which were not previously cross calibrated. Furthermore, the method can be used to assist in making cost-effective management decisions on the level of validation/cross calibration necessary when bringing a test facility on line. This document is also intended to act as a guide for improving uncertainty analyses in a broad spectrum of related industries. Measurement uncertainty and measurement system approaches and practices for the UETP are presented in a systematic format. Readers can use these uncertainty approaches and practices for comparison to their own measurement systems. The approach chose was to analyze three of the UETP test conditions at eight test facilities along with the individual measurement system approaches and practices. The test program provided a wide range of performance measurements and corresponding pretest uncertainty estimates encompassing a variety of test and measurement approaches and practices. Included in the analysis are the basic gas turbine performance measurements of temperature, pressure, airflow, fuel flow, area, speed, thrust, and typical performance parameter functions and associated uncertainty estimates.

Estimation of Measurement Uncertainty in Engine Tests Based on Nato Agard Uniform Engine Test Program

SAE ARP6196-2012 燃气轮机发动机试验设备审核流程

This SAE Aerospace Recommended Practice provides recommendation for: the audit process in general; a list of specific areas of attention to be audited; maintaining the test facility in such a manner that it meets audit requirements.

Gas Turbine Engine Test Facility Audit Process

SAE AIR4068B-2012 燃气轮机发射探测器因素

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of technical requirements. Newer technology may exist. This report describes the concept and data analysis of the probe factor (pf) scheme. Conclusions are drawn and recommendations made for action to further the requirements for improved methods and procedures in emissions sampling technology.

Gas Turbine Emission Probe Factors

SAE AIR4246D-2012 航空器涡轮发动机燃料系统组件试验的污染物

This Aerospace Information Report (AIR) is intended as a guide toward standardization in fluid contamination descriptions and specifications. This document discusses descriptions of fluid contamination products. These contaminants are used for design evaluation and formal component qualification/certification testing. Such tests are routinely performed on candidate aircraft engine fuel and pneumatic system components. Typical of these components are fuel pumps, fuel filters, fuel controls, pressurizing valves, flow dividers, selector valves and combustor nozzles. The purpose of this document is to recommend standard descriptions to be used by specification writers.

Contaminants for Aircraft Turbine Engine Fuel System Component Testing

SAE AIR5892B-2012 排放的不挥发性颗粒的测量技术

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This SAE Aerospace Information Report (AIR) addresses procedures applicable to quantifying the emission of nonvolatile particulate matter at the exit plane of aircraft gas turbine engines. While both volatile and nonvolatile particulate matter (PM) are present in aircraft gas turbine exhaust, the methods used to measure nonvolatile particles are farther advanced and are addressed here. Existing PM measurement regulations employ the SAE Smoke Number measurement (Reference 2.1.1), a stained filter technique used in evaluating visible emissions. The environmental and human health issues associated with submicronic PM emissions require more detailed measurement of the mass, size, and quantity of these particle emissions. Responding to regulatory agency requests, this AIR describes measurement techniques that are well developed and could be applied to the measurement of aircraft engine particulate matter. The techniques discussed here are considered relevant for measuring particle parameters identified with environmental and health concerns. The discussion that follows is based on research made while developing measurement techniques and in scientific and engineering experiments regarding PM emissions. The techniques are not yet used in routine aircraft engine certification. Future use in regulatory testing is likely to involve further refinements in methodology and application. It is planned that these refinements will be included in the subsequent publication of an Aerospace Recommended Practice. The distinction between nonvolatile and volatile particle types is a critical task in the measurement of particles in aircraft engine exhaust. Appendix A, SAE E-31 Position Paper on Particle Matter Measurements, provides additional technical bases for the scope of this AIR. The measurement methods for volatile condensed particles in turbine exhaust will be covered in a subsequent report. Observations to date show that volatile particles occur mainly at diameters less than 10 nanometers (

Nonvolatile Exhaust Particle Measurement Techniques

ANSI/AMCA 500-L-2012 测试热流率用热控百叶窗的实验室方法

The purpose of this standard is to establish uniform laboratory test methods for louvers. Characteristics to be determined include air leakage, pressure drop, water penetration, wind driven rain, and operational torque. This standard may be used as a basis for testing louvers with air used as the test gas. Tests conducted in accordance with the requirements of this standard are intended to demonstrate the performance of a louver and are not intended to determine acceptability level of performance.

Laboratory Methods of Testing Louvers for Rating

GOST R 54978-2012 飞机和直升机的燃油系统.术语和定义

Fuel systems for airplanes and helicopters. Terms and definitions

ANSI/NFPA 1122-2012 模拟火箭规程

1.1 Scope. 1.1.1 This code shall apply to the design, construction, limitation of rocket propellant mass and power, and reliability of model rocket motors and model rocket motor reloading kits and their components, produced commercially for sale to or for use by the public for purposes of education, recreation, and sporting competition. 1.1.2 This code also shall apply to the design and construction of model rockets propelled by model rocket motors specified in 1.1.1. 1.1.3 This code also shall apply to the conduct of launch operations of model rockets specified in 1.1.2. 1.1.4 This code shall not apply to the design, construction, production, manufacture, fabrication, maintenance, launch, flight, test, operation, use, or other activity that is connected with a rocket or rocket motor where carried out or engaged in by any of the following: (1) National, state, or local government (2) Individual, firm, partnership, joint venture, corporation, or other business entity engaged as a licensed business in the research, development, production, testing, maintenance, or supply of rockets, rocket motors, rocket propellant chemicals, or rocket components or parts (3) Colleges or universities 1.1.5 This code shall not apply to the design, construction, fabrication, maintenance, production, manufacture, launch, flight, test, operation, or use of rocket-propelled model aircraft that sustain their mass against the force of gravity by aerodynamic lifting surfaces that support the aircraft during the entire duration of its flight in the air, but shall apply to the model rocket motors and their components that provide the propulsion for such model aircraft. 1.1.6 This code shall not apply to model or toy rockets propelled by pressurized-liquid rocket motors containing less than 250 mL (8.45 fl oz) of water. 1.1.7 This code shall not apply to fireworks rockets or pyrotechnic rockets as defined in NFPA 1123, Code for Fireworks Display. 1.1.8 This code shall not apply to NFPA 1124, Code for the Manufacture, Transportation, Storage, and Retail Sales of Fireworks and Pyrotechnic Articles. 1.1.9 This code shall not apply to NFPA 1126, Standard for the Use of Pyrotechnics Before a Proximate Audience. 1.1.10 This code shall not apply to high power rocketry as defined in NFPA 1127, Code for High Power Rocketry.

Code for Model Rocketry

SAE AS3332B-2011 管道连接平头铜垫圈

Gasket - Copper, Tube Connection, Plain

SAE AIR6197-2011 重新装载新燃气涡轮发动机试验设施的现场选择考虑因素

This document discusses, in broad and general terms, the effects of various natural and man-made influences on the design, construction, equipping, operation and long term supportability of gas turbine engine test facilities. It will assist existing or future operators of gas turbine engine test facilities in making informed decisions regarding the siting, design, construction or long term support of their facilities. This document is intended to aid operators in understanding the basic terms and concerns regarding gas turbine engine test facility site selection. It is not intended that this document be an exhaustive design guide such that any operator or contractor could accomplish the task of gas turbine test facility site selection independently and without further specialist advice or assistance. To this end it is suggested that this document be read in in conjunction with other SAE International specialist ARP and AIR documents and in association with other industry experts from the OEM's, test facility specialist design houses, architects with specialized knowledge or independent consultants (SME's) within the field.

Site Selection Considerations for New Re-Loaded Gas Turbine Engine Test Facilities

SAE AMS3022D-2011 耐碳氢燃料材料的基准液,10%芳烃含量

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This specification covers a hydrocarbon fluid mixture for use as a reference fuel test fluid to evaluate the ability of polymeric compounds to conform to designated requirements after immersion in the fluid at a specific temperature for a specified time, as required by an applicable specification.

Reference Fluid For Testing Hydrocarbon Fuel Resistant Materials, 10% Aromatic Content

SAE AIR5687-2011 进气道/发动机兼容性.从模型到全尺寸开发

This document reviews the state of the art for data scaling issues associated with air induction system development for turbine-engine-powered aircraft. In particular, the document addresses issues with obtaining high quality aerodynamic data when testing inlets. These data are used in performance and inlet-engine compatibility analyses. Examples of such data are: inlet recovery, inlet turbulence, and steady-state and dynamic total-pressure inlet distortion indices. Achieving full-scale inlet/engine compatibility requires a deep understanding of three areas: 1) geometric scaling fidelity (referred to here as just "scaling"), 2) impact of Reynolds number, and 3) ground and flight-test techniques (including relevant environment simulation, data acquisition, and data reduction practices). The Model-to-Full Scale Subcommittee of the S- 16 Turbine Engine Inlet Flow Distortion Committee has examined archives and has obtained recollections of experts regarding air induction system development experience to produce this document. The primary objective of this document is to provide a consolidated record of what is known regarding the effectiveness of wind-tunnel scale-model testing in the prediction of full-scale flight characteristics such as inlet recovery, inlet turbulence, and steady-state and dynamic total-pressure inlet distortion. Discussion is offered regarding these findings in light of our current knowledge and understanding. Based on this discussion material, the SAE S-16 Committee has been able to achieve consensus on lessons learned and to provide recommendations.

Inlet / Engine Compatibility - From Model to Full Scale Development

SAE J1899-2011 飞机活塞发动机润滑油(无灰分散剂)

This SAE Standard establishes the requirements for lubricating oils containing ashless dispersant additives to be used in four-stroke cycle, reciprocating piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-22851. Users should consult their airframe or engine manufacturers manuals for the latest listing of acceptable lubricants.

Lubricating Oil, Aircraft Piston Engine (Ashless Dispersant)

SAE J1787-2011 通过计算法测量航空活塞发动机油的灰分总含量

This SAE Recommended Practice describes an empirical method for determining the theoretical ash content of aviation piston engine lubricating oils by calculating the equivalent weight of metallic oxides formed at 775 °C based on the metallic elemental concentration. The calculation method of ash determination may be used as an alternate to ASTM D 482 for application to the standards for aviation piston engine lubricating oils.

Measurement of the Total Ash Content of Aviation Piston Engine Oils by a Calculation Method

SAE J1966-2011 活塞式飞机发动机润滑油(非分散剂的矿物油)

This SAE Standard establishes the requirements for nondispersant, mineral lubricating oils to be used in four-stroke cycle piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-6082. Users should consult their engine manufacturers manuals for the latest listing of acceptable lubricants.

Lubricating Oils, Aircraft Piston Engine (Nondispersant Mineral Oil)

SAE ARP8615-2011 燃料系统部件:通用规范

This document describes the requirements for air vehicle fuel, vent, and propulsion fuel system functional components.

Fuel System Components: General Specification

SAE AIR5026A-2011 试验室仪器

This document discusses, in broad general terms, typical present instrumentation practice for post-overhaul gas turbine engine testing. Production engine testing and engine development work are outside the scope of this document; they will use many more channels of instrumentation, and in most cases will have requirements for measurements that are never made in post-overhaul testing, such as fan airflow measurements, or strain measurements on compressor blades. The specifications for each parameter to be measured, in terms of measurement range and measurement accuracy, are established by the engine manufacturers. Each test cell instrument system should meet or exceed those requirements. Furthermore, each instrument system should be recalibrated regularly, to ensure that it is still performing correctly.

Test Cell Instrumentation