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This SAE Aerospace Recommended Practice describes the aluminum weldbonding process for fabrication of secondary aircraft structural assemblies possessing excellent strength, fatigue life, and environmental durability.
AMS P17 Polymer Matrix Composites Committee
This recommended practice establishes the procedures and requirements for cleaning titanium alloy parts prior to adhesive bonding operations.
AMS P17 Polymer Matrix Composites Committee
This document defines a set of standard application layer interfaces called JAUS Manipulator Services. JAUS Services provide the means for software entities in an unmanned system or system of unmanned systems to communicate and coordinate their activities. The Manipulator Services represent platform-independent capabilities commonly found across domains and types of unmanned systems. At present, twenty-five (25) services are defined in this document. These services are categorized as: Low Level Manipulator Control Services – The one service in this category allows for low-level command of the manipulator joint actuation efforts. This is an open-loop command that could be used in a simple tele-operation scenario. The service in this category is listed as follows: Primitive Manipulator Service Manipulator Sensor Services – These services, when queried, return instantaneous sensor data. Three services are defined that return respectively joint positions, joint velocities, and joint
AS-4JAUS Joint Architecture for Unmanned Systems Committee
Turbine engines installed in rotorcraft have an exhaust system that is designed and produced by the aircraft manufacturer. The primary function of the exhaust system is to direct hot exhaust gases away from the airframe. The exhaust system may consist of a tailpipe, which is attached to the engine, and an exhaust fairing, which is part of the rotorcraft. The engine manufacturer specifies a baseline "referee" tailpipe design, and guaranteed engine performance is based upon the use of the referee tailpipe and tailpipe exit diameter. The configuration used on the rotocraft may differ from the referee tailpipe, but it is intended to minimize additional losses attributed to the installation. This Aerospace Recommended Practice (ARP) describes the physical, functional, and performance interfaces to be considered in the design of the aircraft exhaust system.
S-12 Powered Lift Propulsion Committee
This document recommends criteria for the layout and for the design, installation, and operation of flight deck facilities for transport aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
This document describes a standard method to collect and report dielectric data for the purpose of monitoring or studying the cure of composites.
AMS P17 Polymer Matrix Composites Committee
This procedure is intended to apply to all engine or airframe mounted fuel pumps and controls when required by the applicable specification. The procedure recommends a recirculation system similar to ARP492 to control the fuel properties affecting the fluid and its ability to "release" fuel vapors and dissolved air and have these "re-entrained or dissolved" during the fluid recovery process back to the tank and the original starting conditions.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
This procedure applies to engine or airframe-mounted fuel pumps. The procedure recommends single-pass operation to minimize changes in fuel properties affecting NPSP capability. An optional method using a recirculation system is also included and may be specified at the discretion of the equipment specification. This procedure defines the recommended test setup, test procedure, data acquisition, and data presentation.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
This recommended practice describes the physical and chemical characterization techniques for identification of epoxy adhesive and prepreg resin systems in order to verify the chemical formulation, resin B-staging (See 8.1), cure reaction rates, adhesive moisture content, and resin component mix ratios, as necessary to achieve manufacturing and quality producibility and engineering performance.
AMS P17 Polymer Matrix Composites Committee
This ARP covers an electro-mechanical pneumatic device which is calibrated to provide control contacts that can be made to operate a warning device whenever the indicated airspeed (IAS) reaches a maximum value as defined by the operating limit speed curve for the specific model aircraft.
A-4 Aircraft Instruments Committee
This recommended practice covers requirements for turbine engine-generators designated as follows:
AE-6 Starting Systems and Auxiliary Power Committee
This SAE Aerospace Recommended Practice (ARP) covers the determination of the amount of stock loss caused by use of chemical cleaning agents on aircraft turbine engine materials.
AMS J Aircraft Maintenance Chemicals and Materials Committee
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.
AGE-3 Aircraft Ground Support Equipment Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
The report shows how the methodology of measurement uncertainty can usefully be applied to test programs in order to optimize resources and save money. In doing so, it stresses the importance of integrating the generation of the Defined Measurement Process into more conventional project management techniques to create a Test Plan that allows accurate estimation of resources and trouble-free execution of the actual test. Finally, the report describes the need for post-test review and the importance of recycling lessons learned for the next project.
E-33 In Flight Propulsion Measurement Committee
This Aerospace Standard (AS) defines the requirements for a heavy duty polytetrafluoroethylene (PTFE) lined, metallic reinforced, hose assembly suitable for use in 400 °F 5000 psi, aircraft and missile hydraulic fluid systems.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Recommended Practice (ARP) is intended as a guide to aid in the specification and testing of Direct Drive Servovalves, but does not include the associated electronic controller. The recommendations contained in this ARP are primarily confined to the input and output characteristics of Direct Drive Servovalves (DDV). The only exception to this approach involves the definition and specification of chip shear force, which is not typically measurable by nondestructive external testing. The information presented should be useful in standardizing the terminology, the specification of physical and performance parameters, and the test procedures used in conjunction with these components. Direct drive servovalves are of two basic types: open loop and closed loop. In the case of open loop direct drive servovalves, the significant input is the motor current as is the case with electrohydraulic servovalves covered in ARP490. A closed loop direct drive servovalve includes a means
A-6B1 Hydraulic Servo Actuation Committee
This document defines the requirements for heavy-duty hose assemblies suitable for use in 21 000 kPa, 135 °C aircraft systems where rapid rate pressure pulsing and torsional/longitudinal flexing may occur in addition to normal hydraulic system loading.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document specifies the requirements for the design objectives for handling qualities applicable to transport aircraft operating in the subsonic, transonic, and supersonic speed range. These objectives are not necessarily applicable to rotor or VTOL aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
The scope of this HIR is to specify general oceanographic environments. Specific environmental requirements shall be specified in a detail specification. Specific requirements are in the state of constant flux because the ocean environment is constantly changing and the changes occur not only on a seasonal basis but also monthly, weekly, daily, and in some cases even hourly. This HIR is to be used as a guide only.
Fluid Power Utilization
Conventional attribute sampling plans based upon nonzero acceptance numbers are no longer desirable. In addition, emphasis is now placed on the quality level that is received by the customer. This relates directly to the Lot Tolerance Percent Defective (LTPD) value or the Limiting Quality Protection of MIL-STD-105. Measuring quality levels in percent nonconforming, although not incorrect, has been replaced with quality levels measured in parts per million (PPM). As a result, this standard addresses the need for sampling plans that can augment MIL-STD-105, are based upon a zero acceptance number, and address quality (nonconformance) levels in the parts per million range. This document does not address minor nonconformances, which are defined as nonconformances that are not likely to reduce materially the usability of the unit of product for its intended purpose.
Systems Management Council
This standard establishes the inspection requirements and acceptance standards for optimum surface finish O-ring packings and gaskets. (This is not an O-ring specification per se.)
AMS CE Elastomers Committee
This report contains background information on life cycle cost elements and key ECS cost factors. Elements of life cycle costs are defined from initial design phases through operational use. Information on how ECS designs affect overall aircraft cost and information on primary factors affecting ECS costs are discussed. Key steps or efforts for comparing ECS designs on the basis of LCC are outlined. Brief descriptions of two computer programs for estimating LCC of total aircraft programs and their use to estimate ECS LCC, are included.
AC-9 Aircraft Environmental Systems Committee
Characteristics of vertical hard-bearing balancing machines are described which make such machines suitable for gas turbine rotor balancing.
EG-1A Balancing Committee
This SAE Aerospace Standard (AS) establishes a Generic Open Architecture (GOA) Framework for application independent hardware/software systems. This document defines the interface classes for the GOA Framework. Supplemental documents define the guidelines for applying the GOA Framework to specific applications.
AS-2 Embedded Computing Systems Committee
The scope of this SAE Aerospace Standard (AS) shall cover the methodology of defining and determining the "internal volumes" of both the main deck and lower deck aircraft cargo compartments. The minimum required clearance between the compartment envelope and the unit load devices (ULDs) shall also be stated in order to provide the maximum ULD external contour and the methodology to define the ULD internal volumes.
AGE-2 Air Cargo
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