Results
This SAE Aerospace Information Report (AIR) contains information on the thermal design requirements of airborne avionic systems used in military airborne applications. Methods are explored which are commonly used to provide thermal control of avionic systems. Both air and liquid cooled systems are discussed.
The test procedure applies to the refueling manifold system connecting the receiver aircraft fuel tanks to the refueling source fuel pump(s) for both ground and aerial refueling. The test procedure is intended to verify that the limit value for surge pressure specified for the receiver fuel system is not exceeded when refueling from a refueling source which meets the requirements of AS1284 (reference 2). This recommended practice is not directly applicable to surge pressure developed during operation of an aircraft fuel system, such as initiating or stopping engine fuel feed or fuel transfer within an aircraft, or the pressure surge produced when the fuel pumps are first started to fill an empty fuel manifold.
The purpose of this document is to relate areas where carbon brake technology may differ from traditional steel brake technology in design and performance. Carbon brakes have been used on military aircraft for many years and are now frequently used on newly commercial developed aircraft. This document presents some of the lessons learned.
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.
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.
This document provides a description of a process for development of fly-by-wire actuation systems. Included are (1) the development of requirements for the servo-actuator hardware and the electronics hardware and software, (2) actuator and servo-electronics interface definitions and, (3) the required communications and interactions between the servo-actuator and the servo-electronics designers.
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.
The tests are static in nature to minimize complexity and cost of required testing facilities. As far as practical, applied static loads should take into account the combined static and dynamic loads anticipated in service. It is intended that tests shall be non-destructive in nature and not result in damage unless ultimate load conditions are employed. Test equipment and methods of testing described are not meant to be restrictive. Alternate equivalent methods to accomplish the desired results may be employed. In selected cases, tests may be repeated under ultimate load conditions when required for substantiation of analytical data. If this becomes necessary, the parts deformed may be removed and replaced prior to the retest.
This Aerospace Information Report (AIR) is presented in two parts. The first part is simply a summarization of design factors that must be considered in establishing vehicle specifications and design characteristics. The second part refers particularly to the performance characteristics of an aircraft tow tractor. Some definitions, formulas, data, and an example are provided mainly for assisting the specifying engineers of potential buyers and users of aircraft tow tractors in the evaluation and comparison of their requirements with the performance capabilities of the various tow tractors offered by the tow tractor manufacturers. Although the design engineers could also use the formulas and data in their calculations of the performance specifications of aircraft tow tractors, this AIR is not intended to provide the methods and all data necessary for detailed calculations and design of an aircraft tow tractor.
This SAE Aerospace Recommended Practice (ARP) describes a two-pole electric connector for use in battery powered ground support equipment, i.e., traction batteries. Alternatively, the connector can have two or more auxiliary contacts for auxiliary circuits. A handle may be added as an option to assist in connecting and disconnecting.
The aircraft landing gear is a complex multi-degree of freedom dynamic system, and may encounter vibration or dynamic response problems induced by braking action. The vibratory modes can be induced by brake and tire-ground frictional characteristics, antiskid operation, brake design features, landing gear design features, and tire characteristics. The impact of this vibration can range from catastrophic failure of critical system components or entire landing gears, to fatigue of small components, to passenger annoyance. It is therefore important that the vibration is assessed during the design concept phase, and verified during the development and testing phases of the system hardware. This SAE Aerospace Information Report (AIR) has been prepared by a panel of the A-5A Subcommittee to present an overview of the landing gear problems associated with aircraft braking system dynamics, and the approaches to the identification, diagnosis, and solution of these problems. All pertinent system
This SAE Recommended Practice defines an architecture, including operating modes, in which an advanced driver interface system and related software exist. It also provides reference to a set of Federal Highway Administration approved guidelines for human factors characteristics of such systems and related software.
This document establishes the requirements for technical content and format of hydraulic system diagrams. This document does not establish configuration requirements, material, or performance requirements for any system or component identified herein.
This specification covers disinfectants or chemicals for use in disinfecting aircraft after carrying livestock.
This specification covers an aluminum alloy in the form of die forgings 4 inches (102 mm) and under in nominal thickness and forging stock of any size (see 8.6).
This specification covers a corrosion- and heat-resistant nickel-iron alloy in the form of bars, forgings, and flash-welded rings 5.0 inches (127 mm) and under in nominal diameter, or maximum cross-sectional distance between parallel sides (thickness), and stock of any size for forging or flash-welded rings.
This specification covers a runway deicing and anti-icing product in the form of a solid. Unless otherwise stated, all specifications referenced herein are latest (current) revision.
This specification covers runway deicing and anti-icing products in the form of a liquid. Unless otherwise stated, all specifications referenced herein are latest (current) revision.
Items per page:
50
1 – 50 of 211951