Results
This SAE Aerospace Recommended Practice (ARP) recommends a methodology to be used for the design, analysis and test evaluation of modern helicopter gas turbine propulsion system stability and transient response characteristics. This methodology utilizes the computational power of modern digital computers to more thoroughly analyze, simulate and bench-test the helicopter engine/rotor system speed control loop over the flight envelope. This up-front work results in significantly less effort expended during flight test and delivers a more effective system into service. The methodology presented herein is recommended for modern digital electronic propulsion control systems and also for traditional analog and hydromechanical systems.
This SAE Aerospace Information Report (AIR) has been written for individuals associated with the ground-level testing of large turbofan and turbojet engines, particularly those who are interested in infrasound phenomena.
This SAE Aerospace Information Report (AIR) outlines a recommended procedure for evaluation of the vibration environment to which the gas turbine engine powerplant is subjected in the helicopter installation. This analysis of engine vibration is normally demonstrated on a one-time basis upon initial certification, or after a major modification, of an engine/helicopter configuration. This AIR deals with linear vibration as measured on the basic case structure of the engine and not, for example, torsional vibration in drive shafting or vibration of a component within the engine such as a compressor or turbine airfoil. In summary, this AIR discusses the engine manufacturer’s "Installation Test Code" aspects of engine vibration and proposes an appropriate measurement method.
This SAE Recommended Practice is part of the SAE J2534-2/X_0500 set of documents that extends the SAE J2534-1_0500 API (version 05.00) specification. It defines the common data structures and constants that will be used to implement the extension to the SAE J2534 API. This document will only include the items that are used by the V05.00 API and that are NOT included in SAE J2534-1_0500. It will not include items from older API versions unless they are used by the V05.00 API.
The purpose of this SAE Aerospace Information Report (AIR) is two-fold: to inform the reader of the extent of effort that went into the development of the Joint Architecture for Unmanned Systems (JAUS); and to capture for posterity the domain analysis that provides the underpinnings for the work by the AS-4 Committee (Unmanned Systems).
This SAE Recommended Practice defines the performance requirements, size and mating interfaces for M12 style 4 and 5 pole Heavy Duty High Speed Datalink connection systems, and applies to both cable-to-cable and cable-to-device connectors.
This specification covers the grain flow pattern requirements in headed bolts, screws, and studs. The heading practice in the manufacture of the bolt, screw, or stud sets the grain flow pattern, but it is also greatly influenced by the fastener and tooling design as well as cold-forging setup. The use of tooling design simulation software is recommended and a commonly used practice that provides reliable forging predictions for superior grain flow quality.
Recent field experience has indicated significant problems with some types of wire and cables as routed on aircraft landing gear. This SAE Aerospace Information Report (AIR) is intended to identify environmental concerns the designer should consider, materials that appear to be most suitable for use in these areas, routing, clamping, and other protection techniques that are appropriate in these applications. In recent years aircraft certification regulatory agencies introduced new regulations regarding Electrical Wiring Interconnection Systems (EWIS) to further enhance safety of the associated systems and aircraft overall.
The requirements presented in this document address the key considerations for thermal safety in aircraft fuel pump design. Document sections focus on understanding safety relative to an electrically motor driven fuel pump assembly acting as an ignition source for explosive fuel vapors within the airplane tank.
This procurement specification covers aircraft quality self-locking nuts for wrenching (hex, spline) and anchor (plate, gang channel, shank) types of nuts made from a corrosion and heat-resistant nickel-base alloy of the type identified under the Unified Numbering System as UNS N07001. Tension height nuts having overall length of threaded portion not less than 1.2 times the nominal thread diameter have 1210 MPa minimum tensile strength at room temperature. Shear height nuts having shorter threaded portion have 1100 MPa minimum tensile strength at room temperature. Maximum test temperature of parts is 730 °C.
This SAE Aerospace Standard (AS) establishes the requirements for fluid fittings that combine both flareless and pipe threaded connections for use in all types of fluid systems.
This test method provides a procedure for measuring no-load rotational breakaway torque of self-lubricating spherical bearings.
This TIR establishes high-flow fueling protocols, including their process limits for fueling of compressed gaseous hydrogen vehicles at peak flow rates from 60 to 300 g/s with compressed hydrogen storage system (CHSS) volume capacities between 248.6 and 7500 L which have been qualified to UN GTR #13. This document is initially being published as a TIR due to limited field testing of the fueling protocols. Once the fueling protocols have been field tested, the SAE Fuel Cell Standards Committee Interface Task Force intends to publish a revision to this document as an SAE Standard.
The purpose of this section is to provide methods and a set of convenient working charts to estimate penalty values in terms of take-off fuel weight for any given airplane mission. The curves are for a range of specific fuel consumption (SFC) and lift/drag ratio (L/D) compatible with the jet engines and supersonic aircraft currently being developed. A typical example showing use of the charts for an air conditioning system is given. Evaluation of the penalty imposed on aircraft performance characteristics by the installation of an air conditioning system is important for two reasons: 1 It provides a common denominator for comparing systems in the preliminary design stage, thus aiding in the choice of system to be used. 2 It aids in pinpointing portions of existing systems where design improvements can be most readily achieved. All factors that influence the flight performance of an aircraft can be expressed in terms of weight, external and momentum drags, and changes in powerplant
This SAE Aerospace Standard (AS) establishes the requirements for a grooved clamp coupling and flanges suitable for joining intermediate pressure and temperature ducting in aircraft pneumatic systems. The rigid coupling joint assembly, hereafter referred to as “the joint”, shall operate within the temperature range of -65 °F external ambient to +800 °F internal fluid.
This Aerospace Recommended Practice (ARP) provides design philosophies, guidelines, requirements, and a set of recommended symbols, lines, and linear patterns for aeronautical information presented on electronic flight deck display devices. Specifically, this document addresses symbols, lines, and linear patterns historically seen on aeronautical charts. It provides recommended symbols for navigation aids, airspace boundaries, missed approach holding patterns, etc. The document does not address all aeronautical symbols, lines, or linear patterns, nor does it provide specific recommendations about color, text and fonts, line weight, or symbol size. Additionally, it does not provide recommendations for non-aeronautical symbols such as traffic or weather. The general guidelines, recommendations and requirements are intended to apply regardless of whether the display application is intended for IFR or VFR operations and regardless of the type of aircraft (14 CFR Part 23, 25, 27, or 29
A recommended pilot-system integration (i.e., crew interface and system integration) approach for concept development is described in Figure 1. The approach emphasizes the fundamental need for a top-down design methodology with particular focus on clear operational performance requirements and functional integration. While this document is primarily aimed at aircraft systems design and integration, the methodology is applicable to a wide range of design and integration situations. It is derived from well established human factors engineering design principles.
This specification establishes the requirements for flake or granular cetyl alcohol, solvents for dissolving the cetyl alcohol, preparation and application requirements for use of cetyl alcohol as an installation lubricant on mechanical fasteners, such as pins, bolts, nuts, washers, threaded or nonthreaded fastening devices, and inspection criteria for coated parts.
This SAE Aerospace Standard (AS) specifies solid polytetrafluoroethylene (PTFE) retainers (backup rings) for use in static glands in accordance with AS5857. They are usually for use in hydraulic and pneumatic systems as anti-extrusion devices in conjunction with O-rings and other seals.
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