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 Standard establishes a test method and a definition for disclosing the performance of suction/blower fans when applied to self-propelled sweepers that solely use a pneumatic conveyance means for the collection and transfer of “sweepings” into a collection hopper.
This document provides the technical requirements for implementing the SAE J1939 Functional Safety Communication Protocol in a manner determined suitable for meeting industry applicable functional safety standards.
This specification covers a fiberglass reinforced silicone rubber in the form of sheet, strip, and molded parts.
This document presents design and application information which will allow optimized utilization of filter line wire and cable purchased to AS85485. Filter line wire is defined and design information is presented. The electrical and mechanical performance characteristics of the wire, along with recommended harnessing methods and techniques, are also presented.
This document describes guidelines, methods, and tools used to perform the ongoing safety assessment process for transport airplanes in commercial service (hereafter, termed “airplane”). The process described herein is intended to support an overall safety management program. It is associated with showing compliance with the regulations, and also with assuring a company that it meets its own internal standards. The methods identify a systematic means, but not the only means, to assess ongoing safety. While economic decision-making is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. To put it succinctly, this document addresses the “Is it safe?” part of safety management; it does not address the “How much does it cost?” part of the safety management. This document also does not address any specific organizational structures for accomplishing the safety assessment process. While the nature of the organizational
This document provides vehicle-level data collection, data analysis, and data verification procedures that may be used to verify that an instrument under test (IUT) satisfies the vehicle-level requirements specified in SAE J3161/1. For the purposes of this report, “vehicle-level requirements” primarily consist of those requirements which can be verified external to the vehicle. The IUT for these procedures is a configured LTE-V2X vehicle-to-vehicle (V2V) device as defined in SAE J3161/1 and is installed on a vehicle of class 2, 3, 4, or 5. While the IUT is conceptually separated from the vehicle it is installed on, the tests outlined in this document are primarily vehicle level, so the terms “vehicle” and “IUT” can generally be considered interchangeable. Additionally, non-vehicle-level complementary tests, not included in this document, are required to verify that the entire set of requirements specified in SAE J3161/1 is satisfied. This document also includes a Traceability Matrix to
SAE Aerospace Recommended Practice ARP1533 is a procedure for the analysis and evaluation of the measured composition of the exhaust gas from aircraft engines. Measurements of carbon monoxide, carbon dioxide, total hydrocarbon, and the oxides of nitrogen are used to deduce emission indices, fuel-air ratio, combustion efficiency, and exhaust gas thermodynamic properties. The emission indices (EI) are the parameters of critical interest to the engine developers and the atmospheric emissions regulatory agencies because they relate engine performance to environmental impact. While this procedure is intended to guide the analysis and evaluation of the emissions from aircraft gas turbine engines (burning conventional hydrocarbon based liquid fuels), the methodology may be applied to the analysis of the exhaust products of any hydrocarbon/air combustor. Some successful applications include: Aircraft engine combustor development rig tests (aviation jet fueled) Stationary source combustor
This specification covers a silver alloy in the form of wire, rod, sheet, strip, foil, pig, powder, shot, and chips and a viscous mixture (paste) of powder in a suitable binder.
This SAE Recommended Practice establishes a standard method to perform screening test sequences that identify a brake friction material’s effectiveness under various test conditions. The result is an evaluation of brake friction material effectiveness under a set of defined braking conditions considered most relevant to automobile braking system development.
The purpose of this SAE Information Report is to provide basic information on penetrating radiation, as applied in the field of nondestructive testing, and to supply the user with sufficient information so that he may decide whether penetrating radiation methods apply to his particular inspection need. Detailed information references are listed in Section 2.
This section presents methods and examples of computing the steady-state heating and cooling loads of aircraft compartments. In a steady-state process the flows of heat throughout the system are stabilized and thus do not change with time. In an aircraft compartment, several elements compose the steady-state air conditioning load. Transfer of heat occurs between these sources and sinks by the combined processes of convection, radiation, and conduction in the following manner: 1 Convection between the boundary layer and the outer airplane skin. 2 Radiation between the external skin and the external environment. 3 Solar radiation through transparent areas directly on flight personnel and equipment and on the cabin interior surfaces. 4 Conduction through the cabin walls and structural members. 5 Convection between the interior cabin surface and the cabin air. 6 Convection between cabin air and flight personnel or equipment. 7 Convection and radiation from internal sources of heat such as
This document lists definitions that are commonly used in describing aircraft reciprocating engine performance.
This SAE Aerospace Standard (AS) is intended for use by those involved in the design of aircraft, missile, or space systems, and their support equipment to define the various types of fastener torque.
This SAE Aerospace Standard (AS) applies to a portable chemical oxygen generator assembly intended for the following uses: a First aid treatment of aircraft occupants after an emergency descent following a decompression or other emergency condition. b Use by cabin attendants to maintain their mobility after a decompression.
This document is a guide to the application of magnesium alloys to aircraft interior components including but not limited to aircraft seats. It provides background information on magnesium, its alloys and readily available forms such as extrusions and plate. It also contains guidelines for “enabling technologies” for the application of magnesium to engineering solutions including: machining, joining, forming, cutting, surface treatment, flammability issues, and designing from aluminum to magnesium.
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