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Viewing 1 to 30 of 429
CURRENT
2013-11-11
Standard
AIR4994A
Gas compressors (air and other compressible fluids) have been used sporadically since the 1940's for various utility functions in aerospace applications. They have been used to provide power to gun purge and drive systems, engine or APU starters (recharge accumulators), reservoir pressurization, cockpit pressurization, braking systems, canopy seals, engine control devices, landing gear activation, and boosted flight controls (see Table 1). In current state-of-the-art aircraft, most pneumatic system power is extracted from a stage of compression in the turbo-jet engine. As more and more demands are put on new generation engines for fuel economy and performance there is an increasing need for a new source of pneumatic power. This document is intended to describe current state-of-the-art technology in compressors, define the limitations, discuss enhancements needed and attempt to predict the needs of the future.
CURRENT
2013-06-17
Standard
AIR1343B
This information report presents a preliminary discussion of liquid propellant gas generation (LPGG) systems. A LPGG system, as used herein, is defined as a system which stores a liquid propellant and, on command, discharges and converts the liquid propellant to a gas. The LPGG system can interface with a gas-to-mechanical energy conversion device to make up an auxiliary power system. Figure 1 shows a block diagram of LPGG system components which include a propellant tank, propellant expulsion system, propellant control and a decomposition (or combustion) chamber. The purpose of this report is to provide general information on the variety of components and system arrangements which can be considered in LPGG design, summarize advantages and disadvantages of various approaches and provide basic sizing methods suitable for initial tradeoff purposes.
2015-05-04
WIP Standard
ARP5384
This Recommended Practice provides a guide for specifying general design, performance, and test requirements for Power Drive Units (PDUs) for aerospace flight controls or other aerospace applications.
CURRENT
2002-04-05
Standard
ARP5311
This SAE Aerospace Recommended Practice (ARP) defines all the relevant issues that affect the generation of an Interface Control Document for Mechanical Actuation Sub-Systems. It is intended to provide to all parties involved with the generation of Mechanical Actuation Sub-Systems, a definition of documentation, drawings, reports and design parameters required to assure a successful development of mechanical actuation sub-systems for Aerospace-Military and Commercial applications.
CURRENT
2014-04-24
Standard
ARP4904A
This SAE Aerospace Recommended Practice (ARP) establishes software capability guidelines for computer controlled test equipment, hereinafter referred to as automatic test equipment (ATE), for testing hydraulic components. A typical ATE system is shown in Figure 1. The items herein have been selected as potential features which may or may not be applicable to a particular application. This document does not address software development requirements, qualification procedures, or hardware design requirements, but encourages users to refer to existing documents, defined in 2.1.1, for guidance on such issues.
CURRENT
2014-07-01
Standard
ARP4940
This SAE Aerospace Recommended Practice (ARP) is an application guide for fixed and variable displacement hydraulic motors. It provides details of the characteristics of fixed and variable displacement hydraulic motors, architectures, circuit designs, controls, and typical applications. The applications include airborne and defense vehicles with emphasis on high performance applications.
HISTORICAL
2009-06-01
Standard
ARP4378A
This Aerospace Recommended Practice (ARP) provides design and test requirements for factory precharged, welded bellows hydraulic accumulators.
HISTORICAL
2009-08-06
Standard
ARP4378B
This Aerospace Recommended Practice (ARP) provides design and test requirements for factory precharged, welded bellows hydraulic accumulators.
2016-08-17
WIP Standard
ARP4553B
This SAE Aerospace Recommended Practice (ARP) is intended to provide design and qualification requirements for self-displacing hydraulic accumulators.

These requirements are intended to be included in the Producrement Specification for the accumulator. Those requirements identified by the use of "shall" are considered to be essential requirements; those requirements identified by the use of "should" are considered to be optional requirements for inclusion in the Specificaiton at the discretion of the Purchaser.

In addition, test methods for production acceptance and qualification purposes are provided.

The accumulator is intended for use in military aerospace hydraulic systems with rated pressures of up to 8000 psi (55,158 kPa) and of the following types as specified in SAE AS 5440: Type I: -65 to +160 °F (-54 to +71 °C) fluid temperature; Type II: -65 to +275 °F (-54 to +135 °C) fluid temperature.

CURRENT
2008-12-19
Standard
ARP4553A
This SAE Aerospace Recommended Practice (ARP) is intended to provide design and qualification requirements for self-displacing hydraulic accumulators. These requirements are intended be included in the Procurement Specification for the accumulator. Those requirements identified by the use of “shall” are considered to be essential requirements; those requirements identified by the use of “should” are considered to be optional requirements for inclusion in the Specification at the discretion of the Purchaser. In addition, test methods for production acceptance and qualification purposes are provided. The accumulator is intended for use in military aerospace hydraulic systems with rated pressures of up to 8000 psi (55 158 kPa) and of the following types as specified in AS5440: Type I −65 to +160 °F (−54 to +71 °C) fluid temperature Type II −65 to +275 °F (−54 to +135 °C) fluid temperature The accumulator is also intended for use in commercial aerospace and helicopter hydraulic systems.
CURRENT
2010-05-04
Standard
ARP5777
This document is to be used as a guide in preparing specifications for maintenance and inspection of acme screw assemblies used in driven linear actuators. It is intended to cover Acme screw assemblies driven by electric, hydraulic, pneumatic, manual means, with or without gear case or speed reduction systems, and micro actuators. Though the Acme screw is the most common thread form for sliding contact jackscrews this guideline is equally applicable to other sliding contact thread forms such as buttress, square, stub acme, and others including custom thread forms. The term Acme shall be used generally to address all sliding contact thread forms.
CURRENT
2009-12-30
Standard
ARP1280B
This SAE Aerospace Recommended Practice (ARP) is an application guide for hydraulic power transfer units and describes: The various types Typical design approaches Their operational characteristics and limitations Circuit recommendations Typical applications The scope of this ARP is limited to devices that transfer power between hydraulic systems and do so by means of rotary subassemblies such as hydraulic motors and pumps.
HISTORICAL
1976-03-01
Standard
ARP1280
This document will be limited in scope to power transfer units made up of two fixed displacement pumps/motors.
CURRENT
2013-06-18
Standard
ARP4727B
This SAE Aerospace Recommended Practice (ARP) presents two BASIC language computer programs to promote and standardize the computation of installed O-ring cross-section deflection hereafter referred to as "squeeze" and the computation of gland volume. The two programs were written with line numbers and without use of any system specific BASIC commands to allow usage with as many systems as possible with a minimum of editing. The programs support entry of customary U.S. or metric dimensions.
2016-10-11
WIP Standard
AIR5713A
An industry survey has been completed to determine the incidence of jam and excessive backlash in rotary and linear mechanical actuators subject to "primary flight control like" duty cycles. The data is valuable for understanding how existing mechanical actuators behave in service, identifying areas for potential improvement and possibly being used as a reference to support future primary flight control system trade-off studies.
CURRENT
2008-07-15
Standard
AIR5713
An industry survey has been completed to determine the incidence of jam and excessive backlash in rotary and linear mechanical actuators subject to “primary flight control like” duty cycles. The data is valuable for understanding how existing mechanical actuators behave in service, identifying areas for potential improvement and possibly being used as a reference to support future primary flight control system trade-off studies.
HISTORICAL
2011-10-11
Standard
AIR5872
This Aerospace Information Report presents an overview of the application and control of fixed and variable displacement pumps with the emphasis on the controls most commonly used on variable displacement pumps. It describes various options to control the operation of hydraulic pumps in terms of controlling the pump output pressure and/or flow and assisting in the selection of the pump.
CURRENT
2011-09-21
Standard
AIR6052
The purpose of this AIR is to provide a comprehensive description document that displays various examples of transport and business aircraft systems driving Trimmable Horizontal Stabilizers. The main focus is on mechanical systems which may be actuated hydraulically or electrically. The document is intended as an overview for those specifying or designing Horizontal Stabilizer Trim Actuators in order to compare existing solutions as reference for implementation in new aircraft programs.
CURRENT
2010-06-16
Standard
AIR744C
This SAE Aerospace Information Report (AIR) is a review of the general characteristics of power sources that may be used to provide secondary, auxiliary, or emergency power for use in aircraft, space vehicles, missiles, remotely piloted vehicles, air cushion vehicles, surface effect ships, or other vehicles in which aerospace technology is used. The information contained herein is intended for use in the selection of the power source most appropriate to the needs of a particular vehicle or system. The information may also be used in the preparation of a power source specification. Considerations for use in making a trade study and an evaluation of the several power sources are included. More detailed information relating to specific power sources is available in other SAE Aerospace Information Reports or in Aerospace Recommended Practices.
HISTORICAL
1995-07-01
Standard
AIR744B
This SAE Aerospace Information Report (AIR) is a review of the general characteristics of power sources that may be used to provide secondary, auxiliary, or emergency power for use in aircraft, space vehicles, missiles, remotely piloted vehicles, air cushion vehicles, surface effect ships, or other vehicles in which aerospace technology is used. The information contained herein is intended for use in the selection of the power source most appropriate to the needs of a particular vehicle or system. The information may also be used in the preparation of a power source specification. Considerations for use in making a trade study and an evaluation of the several power sources are included. More detailed information relating to specific power sources is available in other SAE Aerospace Information Reports or in Aerospace Recommended Practices.
HISTORICAL
1992-07-01
Standard
AIR744A
HISTORICAL
1965-01-10
Standard
AIR786
This document contains data relative to the chemical nature of aerospace fluids and relates each to its effect upon elastomeric components. Since the compatibilities of elastomers are determined by the compounding as well as the nature of the base polymer, the elastomers considered are limited to finished compounds for which material or performance specifications could be referenced.
CURRENT
2013-10-04
Standard
ARP5724
This document provides an overview of the tests, and issues related to testing, that are unique to Electromechanical Actuators (EMAs). The tests, and issues documented, are not necessarily all-inclusive. This document discusses both the tests applicable to EMAs and the test methodologies to accomplish the test objectives. EMAs may be used in a wide variety of applications such as utility, secondary flight controls and primary flight controls, in a wide variety of markets including manned and unmanned civil and military aircraft, small missile fin and thrust vector control applications up to high powered utility and flight controls. EMAs may also have either a rotary or a linear output, be servo controlled or use simple open loop point-to-point or other control topologies. As such this document covers a wide range of potential applications, the application of any given test requirement is determined by the application and the user.
HISTORICAL
1983-10-01
Standard
J1134_198310
This SAE Recommended Practice establishes a single bolt pattern for the No. 1 clutch housing (see Figure 1) and the No. 2 clutch housing (see Figure 2). These four bolt patterns are designated to give commonality of mounting brackets in existing frame rails. The 420 mm (16.5 in) span, pad face to pad face, allows the ease of installation in existing frame rail widths. This is also the minimum spacing which will accommodate commonly used clutches.
HISTORICAL
1976-01-01
Standard
J1134_197601
This SAE Recommended Practice establishes a single bolt pattern for the No. 1 clutch housing (see Figure 1) and the No. 2 clutch housing (see Figure 2). These four bolt patterns are designated to give commonality of mounting brackets in existing frame rails. The 420 mm (16.5 in) span, pad face to pad face, allows the ease of installation in existing frame rail widths. This is also the minimum spacing which will accommodate commonly used clutches.
HISTORICAL
2000-04-26
Standard
J1134_200004
This SAE Recommended Practice establishes a single bolt pattern for the No. 1 clutch housing (see Figure 1) and the No. 2 clutch housing (see Figure 2). These four bolt patterns are designated to give commonality of mounting brackets in existing frame rails. The 420 mm (16.5 in) span, pad face to pad face, allows the ease of installation in existing frame rail widths. This is also the minimum spacing which will accommodate commonly used clutches.
2017-12-07
WIP Standard
J1711
This Society of Automotive Engineers (SAE) Recommended Practice establishes uniform chassis dynamometer test procedures for hybrid-electric vehicles (HEVs) that are designed to be driven on public roads. The procedure provides instructions for measuring and calculating the exhaust emissions and fuel economy of HEVs driven on the Urban Dynamometer Driving Schedule (UDDS) and the Highway Fuel Economy Driving Schedule (HFEDS), as well as the exhaust emissions of HEVs driven on the US06 Driving Schedule (US06) and the SC03 Driving Schedule (SC03). However, the procedures are structured so that other driving schedules may be substituted, provided that the corresponding preparatory procedures, test lengths, and weighting factors are modified accordingly. Furthermore, this document does not specify which emissions constituents to measure (e.g., HC, CO, NOx, CO2); instead, that decision will depend on the objectives of the tester.
CURRENT
2010-06-08
Standard
J1711_201006
This Society of Automotive Engineers (SAE) Recommended Practice establishes uniform chassis dynamometer test procedures for hybrid-electric vehicles (HEVs) that are designed to be driven on public roads. The procedure provides instructions for measuring and calculating the exhaust emissions and fuel economy of HEVs driven on the Urban Dynamometer Driving Schedule (UDDS) and the Highway Fuel Economy Driving Schedule (HFEDS), as well as the exhaust emissions of HEVs driven on the US06 Driving Schedule (US06) and the SC03 Driving Schedule (SC03). However, the procedures are structured so that other driving schedules may be substituted, provided that the corresponding preparatory procedures, test lengths, and weighting factors are modified accordingly. Furthermore, this document does not specify which emissions constituents to measure (e.g., HC, CO, NOx, CO2); instead, that decision will depend on the objectives of the tester.
Viewing 1 to 30 of 429

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