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This specification covers a corrosion and heat-resistant nickel alloy in the form of pre-alloyed powder.
AMS AM Additive Manufacturing Metals
This document outlines a standard practice for conducting system safety. In some cases, these principles may be captured in other standards that apply to specific commodities such as commercial aircraft and automobiles. For example, those manufacturers that produce commercial aircraft should use SAE ARP4754 or SAE ARP4761 (see Section 2 below) to meet FAA or other regulatory agency system safety-related requirements. The system safety practice as defined herein provides a consistent means of evaluating identified risks. Mishap risk should be identified, evaluated, and mitigated to a level as low as reasonably practicable. The mishap risk should be accepted by the appropriate authority and comply with federal (and state, where applicable) laws and regulations, executive orders, treaties, and agreements. Program trade studies associated with mitigating mishap risk should consider total life cycle cost in any decision. This document is intended for use as one of the elements of project
G-48 System Safety
Propulsion measurements and thrust methods presented in the current published versions of AIR1703 and AIR5450 place a primary focus on the engine reactionary force (thrust) acting to propel an aircraft in the forward direction. In contrast, this document addresses the use of the engine reactionary force in the opposite direction (reverse thrust) to supplement aircraft deceleration. This document’s application spans commercial and military transport turbofan engine applications for various engine and reverse thrust configurations. The discussion and examples primarily focus on separate flow exhaust turbofan engines. Piston and turboprop variable-pitch propeller blade applications are not covered. Although reverse thrust has been utilized for in-flight deceleration, primarily for short takeoff and landing aircraft and military fighter applications, this application of reverse thrust is only covered in a cursory manner.
E-33 In Flight Propulsion Measurement Committee
The objective of this document is to provide a recommended practice for the development of aerospace EPS dynamic models so that models developed by different companies/industries/governments/etc. will have a basic level of compatibility and interconnectivity. This will be crucial as the aerospace industry looks to solve the challenges of the 21st century through integrated vehicle optimization. This document focuses on model interfaces and their interconnection. Other than these boundary characteristics, this document does not attempt to describe or regulate the inner workings of individual component models. AIR6326 defines the four-level paradigm for aircraft EPS MSAT studies. Of the four levels, Device Physical, Behavioral, Functional, and Architectural, only the first three are dynamic models. Further, the Device Physical level is too detailed and not intended to be interconnected to other EPS models. Thus, only the middle two levels – Behavioral and Functional – will be covered by
AE-7M Aerospace Model Based Engineering
This SAE Information Report has been prepared at the request of the SAE Road Vehicle Aerodynamics Forum Committee (RVAC), incorporating material from earlier revisions of the document first prepared by the Standards Committee on Cooling Flow Measurement (CFM). Although a great deal is already known about engine cooling, recent concern with fuel conservation has resulted in generally smaller air intakes whose shape and location are dictated primarily by low vehicle drag/high forward speed requirements. The new vehicle intake configurations make it more difficult to achieve adequate cooling under all conditions. They cause cooling flow velocity profiles to become distorted and underhood temperatures to be excessively high. Such problems make it necessary to achieve much better accuracy in measuring cooling flows. As the following descriptions show, each company or institution concerned with this problem has invested a lot of time and as a result gained considerable experience in
Road Vehicle Aerodynamics Forum Committee
This SAE Standard serves as the guidance document for the J2945/x family of standards as illustrated in Figure 7. It contains cross-cutting material which applies to the other J2945/x standards, including recommended practice for the use of Systems Engineering (SE) and generic DSRC interface requirements content. The scope for the DSRC system environment is to provide for the information exchange between a host vehicle and another DSRC enabled device, a device worn by or otherwise attached to a traveler, a roadside device, or a management center, to address safety, mobility, and environmental system needs. The audience for this document includes the technical teams of developers of the J2945/x documents and the implementers of the applications which are based on the J2945/x documents.
V2X Core Technical Committee
This test plan is broken into three major sections for the testing of bus controllers Electrical, Protocol and Noise tests.
AS-1A Avionic Networks Committee
This document provides a review of published methods that have been used to provide estimates of the levels of distortion and/or the concomitant loss of stability pressure ratio that can occur when the recommended full complement of aerodynamic interface plane high-response instrumentation is not used when obtaining inlet data. The methods have been categorized based on the underlying mathematical representation of the aerophysics. Further, the use of maximum value statistics, which has been used to further improve the results where short-duration time records have been employed, is discussed.
S-16 Turbine Engine Inlet Flow Distortion Committee
This SAE Aerospace Standard (AS) standardizes inspection and test procedures, workmanship criteria, and minimum training and certification requirements to detect Suspect/Counterfeit (SC) Electrical, Electronic, and Electromechanical (EEE) parts. The requirements of this document apply once a decision is made to use parts with unknown chain of custody that do not have pedigree back to the original component manufacturer or have been acquired from a broker or independent distributor, or when there are other known risk elements that result in the User/Requester to have concerns about potential SC EEE parts. The tests specified by this standard may also detect occurrences of malicious tampering, although the current version of this standard is not designed specifically for this purpose. This standard ensures consistency across the supply chain for test techniques and requirements based on assessed risk associated with the application, component, supplier, and other relevant risk factors
G-19A Test Laboratory Standards Development Committee
This SAE Standard provides a method for determining the Effective Projected Luminous Lens Area (EPLLA) of a lamp function using design analysis. This standard was created to clarify and address how to determine EPLLA with traditional and new technologies.
Test Methods and Equipment Stds Committee
This document provides recommendations for several aspects of air-breathing gas turbine engine performance modeling using object-oriented programming systems. Nomenclature, application program interface, and user interface are addressed with the emphasis on nomenclature. The Numerical Propulsion System Simulation (NPSS) modeling environment is frequently used in this document as an archetype. Many of the recommendations for standards are derived from NPSS standards. NPSS was chosen because it is an available product. The practices recommended herein may be applied to other object-oriented systems. While this document applies broadly to any gas turbine engine, the great majority of engine performance computer programs have historically been written for aircraft propulsion systems. Aircraft and propulsion terminology and examples appear throughout.
S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
This report covers engine tests performed in Altitude Test Facilities (ATFs) with the primary purpose of determining steady state thrust at simulated altitude flight conditions as part of the in-flight thrust determination process. As such it is complementary to AIR1703 and AIR5450, published by the SAE E-33 Technical Committee. The gross thrust determined using such tests may be used to generate other thrust-related parameters that are frequently applied in the assessment of propulsion system performance. For example: net thrust, specific thrust, and exhaust nozzle coefficients. The report provides a general description of ATFs including all the major features. These are: Test cell air supply system. This controls the inlet pressure and includes flow straightening, humidity and temperature conditioning. Air inlet duct and slip joint. Note that the report only covers the case where the inlet duct is connected to the engine, not free jet testing. Thrust stand force measurement system
E-33 In Flight Propulsion Measurement Committee
This SAE Aerospace Information Report (AIR) describes a method for assessing size dependent particle losses in a sampling and measurement system of specified geometry utilizing the non-volatile PM (nvPM) mass and number concentrations measured at the end of the sampling system.1 The penetration functions of the sampling and measurement system may be determined either by measurement or by analytic computational methods. Loss mechanisms including thermophoretic (which has a very weak size dependence) and size dependent losses are considered in this method2 along with the uncertainties due to both measurement error and the assumptions of the method. The results of this system loss assessment allow development of estimated correction factors for nvPM mass and number concentrations to account for the system losses facilitating estimation of the nvPM mass and number at the engine exhaust nozzle exit plane. As the particle losses are size dependent, the magnitude of correction factors can
E-31P Particulate Matter Committee
This report revises ARD50015 document to the AIR format. This report, as was the original, is intended to complement ARP1420C and AIR1419C documents issued by the SAE S-16 Committee on spatial total-pressure distortion. These previous documents addressed only total-pressure distortion and excluded total temperature distortion. The subject of inlet total temperature distortion is addressed in this report with some background and identification of the problem area. The status of past efforts is reviewed, and an attempt is made to define where we are today. Deficiencies, voids, and limitations in knowledge and test techniques for total temperature distortion are identified.
S-16 Turbine Engine Inlet Flow Distortion Committee
The Physics-of-Failure (PoF) is a science-based approach to reliability that uses modeling and simulation to design-in reliability. This approach models the root causes of failures such as fatigue, fracture, wear, and corrosion. Computer-Aided Design (CAD) tools have been developed to address various loads, stresses, failure mechanisms and sites. PoF uses knowledge of basic failure processes to prevent failures through robust design and manufacturing practices, and aims to: Design-in reliability up front; Eliminate failures prior to testing; Increase fielded reliability; Promote rapid, cost effective deployment of Health and Usage Monitoring Systems (HUMS); Improve diagnostic and prognostic techniques and processes; and, Decrease operational and support costs. This guide provides a high level overview of the methodology, process and advantages to performing a PoF assessment.
G-41 Reliability
This SAE Standard provides measurement methods to determine HUD optical performance in typical automotive ambient lighting conditions. It covers indoor measurements with simulated outdoor lighting for the measurement of HUD virtual images. HUD types addressed by this standard includes w-HUD (windshield HUD) and c-HUD (combiner HUD) with references to Augmented Reality (AR) HUD as needed. It is not the scope of this document to set threshold values for automotive compliance; however, some recommended values are presented for reference.
Vehicular Flat Panel Display Standards Committee
This document contains recommended practices for the effective control of non-deliverable software. It addresses practices for control during the development, production, release maintenance, and retirement of non-deliverable software, as well as for software procured from outside manufacturers and incorporated in the production, evaluation, test, acceptance or calibration of processes. For the purposes of this document, the terms software and non-deliverable software are considered synonymous.
G-14 Americas Aerospace Quality Standards Committee (AAQSC)
The CDIF Family of Standards is primarily designed to be used as a description of a mechanism for transferring information between CASE tools. It facilitates a successful transfer when the authors of the importing and exporting tools have nothing in common except an agreement to conform to CDIF. The language that is defined for the Transfer Format also has applicability as a general language for Import/Export from repositories. The CDIF Integrated Meta-model defined for CASE also has applicability as the basis of standard definitions for use in repositories. The standards which form the complete family of CDIF Standards are documented in EIA/IS-106 CDIF - CASE Data Interchange Format - Overview. These standards cover the overall framework, the transfer format and the CDIF Integrated Meta-model. The diagram in Figure 1 depicts the various standards that comprise the CDIF Family of Standards. The shaded box depicts this Standard and its position in the CDIF Family of Standards. This
Systems Management Council
The CDIF Family of Standards is primarily designed to be used as a description of a mechanism for transferring information between CASE tools. It facilitates a successful transfer when the authors of the importing and exporting tools have nothing in common except an agreement to conform to CDIF. The language that is defined for the Transfer Format also has applicability as a general language for Import/Export from repositories. The CDIF Integrated Meta-model defined for CASE also has applicability as the basis of standard definitions for use in repositories. The standards which form the complete family of CDIF Standards are documented in EIA/IS-106 CDIF - CASE Data Interchange Format - Overview. These standards cover the overall framework, the transfer format and the CDIF Integrated Meta-model. The diagram in Figure 1 depicts the various standards that comprise the CDIF Family of Standards. The shaded box depicts this Standard and the role that it plays in the CDIF Family of Standards
Systems Management Council
The scope of this bulletin is to provide guidance on the use of current and future technologies for the electronic interchange of CM data.
G-33 Configuration Management
This SAE Aerospace Information Report (AIR) provides a methodology for performing a statistical assessment of gas-turbine-engine stability-margin usage. Consideration is given to vehicle usage, fleet size, and environment to provide insight into the probability of encountering an in-service engine stall event. Current industry practices, such as ARP1420, supplemented by AIR1419, and engine thermodynamic models, are used to determine and quantify the contribution of individual stability threats. The statistical technique adopted by the S-16 committee for performing a statistical stability assessment is the Monte Carlo method (see Applicable References 1 and 2). While other techniques may be suitable, their application is beyond the scope of this document. The intent of the document is to present a methodology and process to construct a statistical-stability-assessment model for use on a specific system and its mission or application.
S-16 Turbine Engine Inlet Flow Distortion Committee
This document surveys the systems used for thermal management of batteries in vehicles. Battery thermal management is important for battery performance and cycle life. The document also includes a summary of design considerations for battery thermal management and a glossary of terms.
Battery Thermal Management Committee
The turbine-engine inlet flow distortion methodology addressed in this document applies only to the effects of inlet total-pressure distortion. Practices employed to quantify these effects continue to develop and, therefore, periodic updates are anticipated. The effects of other forms of distortion on flow stability and performance, and of any distortion on aeroelastic stability are not addressed. The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which guidelines for descriptor use, assessment techniques, and testing outlined in this document are applied to a specific program should be consistent with the expected severity of the compatibility problem.
S-16 Turbine Engine Inlet Flow Distortion Committee
This SAE Aerospace Information Report (AIR) provides data and general analysis methods for calculation of internal and external, pressurized and unpressurized airplane compartment pressures during rapid discharge of cabin pressure. References to the applicable current FAA and EASA rules and advisory material are provided. While rules and interpretations can be expected to evolve, numerous airplanes have been approved under current and past rules that will have a continuing need for analysis of production and field modifications, alterations and repairs. The data and basic principles provided by this report are adaptable to any compartment decompression analysis requirement.
AC-9 Aircraft Environmental Systems Committee
The purpose of this document is to establish the requirements for Real-Time Communication Protocols (RTCP). Systems for real-time applications are characterized by the presence of hard deadlines where failure to meet a deadline must be considered a system fault. These requirements have been driven predominantly, but not exclusively, by aerospace type military platforms and commercial aircraft, but are generally applicable to any distributed, real-time, control systems. These requirements are primarily targeted for the Transport and Network Layers of peer to peer protocols, as referenced in the Open System Interconnect Reference Model (2.2.1 and 2.2.2), developed by the International Standards Organization (ISO). These requirements are intended to complement SAE AS4074 (2.1.1) and AS4075 (2.1.2), and future SAE communications standards. Although information transfer objectives herein concentrate primarily on digital data flow attributes, efforts have been made such as not to preclude
AS-1A Avionic Networks Committee
The scope of this document is to provide review of recent history of loss-of-control accidents during airline revenue operations.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
This Aerospace Information Report (AIR) has been prepared by the Systems Applications and Requirements Subcommittee of SAE Committee AS-2. It is intended to provide guidance primarily, but not exclusively, for specifiers and designers of data communication systems for real time military avionics applications within a platform. The subject of high speed data transmission is addressed from two standpoints: (1) the influence of developments in technology on avionics architectures as a whole and (2) the way in which specific problems, such as video, voice, closed loop control, and security may be handled. While the material has been prepared against a background of experience within SAE AS-2 relating to the development of a family of high speed interconnect standards, reference to specific standards and interconnect systems is minimized. It should be noted, however, that many of the concepts described require interconnect systems with advanced operational and performance characteristics
AS-1A Avionic Networks Committee
This SAE Aerospace Information Report (AIR) has been prepared by a panel of the SAE A-5A Committee and is presented to document the design approaches and service experience from various applications of antiskid systems. This experience includes commercial and military applications.
A-5A Wheels, Brakes and Skid Controls Committee
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, η 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.
E-33 In Flight Propulsion Measurement Committee
This Handbook has been prepared by the Ring Implementation Task Group of the SAE AS-2 Committee, and is intended to support AS4075 by providing explanation of the standard itself and guidance on its use. The principal objective in the preparation of a standard is to provide a statement of operational and performance requirements, and an unambiguous definition of the functions to be realized in any implementation, primarily from the view point of interoperability. While efforts have been made within the AS4075 standard to provide a readable general description of the HSRB, detailed explanations, rationale and guidance to the use are incompatible with the purpose and, indeed, the format of a standard. Accordingly, this Handbook contains a paragraph-by-paragraph explanation of the main sections of the standard, and a discussion of application and implementation issues.
AS-1A Avionic Networks Committee
This document provides an overview of currently available and need to be developed modeling and simulation capabilities required for implementing robust and reliable Aerospace WDM LAN applications.
AS-3 Fiber Optics and Applied Photonics Committee
This SAE Aerospace Information Report (AIR) discusses the nature of landing gear stability, describes many common landing gear stability problems, and suggests approaches and methods for solving or avoiding them.
A-5B Gears, Struts and Couplings Committee
This SAE Aerospace Information Report (AIR) covers, and is restricted to, hands-on servicing/ maintenance of industrial lead acid batteries used solely for motive power and exclusively for ground support equipment (GSE). It does not address or pertain to automotive-type SLI (starting-lighting-ignition) batteries or any other types of batteries (such as nickel-cadmium, zinc, or lithium batteries) which may be on-board airport GSE for either motive power or auxiliary uses. Similarly, the battery servicing and charging facilities described herein are those intended exclusively for industrial lead acid batteries.
AGE-3 Aircraft Ground Support Equipment Committee
This SAE Recommended Practice applies to both Original Equipment Manufacturer (OEM) and aftermarket ITS message-generating systems for passenger vehicles and heavy trucks. The recommended practice describes the method for prioritizing ITS in-vehicle messages and/or displayed information based on a defined set of criteria. Each criterion has a fixed number of levels that are used to rate/rank a given message or information item to determine its prioritization value. The prioritization value is used to determine the priority in which simultaneous, or overlapping, in-vehicle messages are presented to the driver.
Driver Vehicle Interface (DVI) Committee
The recommendations of this SAE Aerospace Recommended Practice (ARP) for aircraft compartment automatic temperature control systems are primarily intended to be applicable to occupied or unoccupied compartments of civil and military aircraft.
AC-9 Aircraft Environmental Systems Committee
This document discusses a recommended new approach to integrate probabilistic methodologies with design practices, procedures, and software codes currently being used. In addition to complementing design methods currently in use, this new procedure will permit the designer to quantify the amount of conservatism that exists for a particular design due to the large amount of additional information which is provided to the designer. This additional information will allow the designer to make better decisions when faced with tradeoffs between cost, reliability, performance, and weight. Although the methodologies described herein can be used heavily in the design process, their applicability is much more encompassing. They can be used from product concept to customer delivery.
G-11 Probabilistic Methods and Uncertainty Quantification
This SAE Aerospace Recommended Practice (ARP) contains methods used to measure the optical performance of airborne electronic flat panel display (FPD) systems. The methods described are specific to the direct view, liquid crystal matrix (x-y addressable) display technology used on aircraft flight decks. The focus of this document is on active matrix, liquid crystal displays (LCD). The majority of the procedures can be applied to other display technologies, however, it is cautioned that some techniques need to be tailored to different display technologies. The document covers monochrome and color LCD operation in the transmissive mode within the visual spectrum (the wavelength range of 380 to 780 nm). These procedures are adaptable to reflective and transflective displays paying special attention to the source illumination geometry. Photometric and colorimetric measurement procedures for airborne direct view CRT (cathode ray tube) displays are found in ARP1782. Optical measurement
A-20A Crew Station Lighting
This section establishes modeling conventions and guidelines to be followed during the development of the GEIA-STD-927 top level schema. The following is within the scope of this document: Modeling rules, conventions and guidelines for the GEIA-STD-927 top level schema. The following are outside the scope of this document: An introduction to information modeling; An introduction to the EXPRESS modeling language.
G-47 Systems Engineering
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