Display:

Results

Viewing 151 to 180 of 15451
2014-09-25
WIP Standard
ARP5483/3B
This test method outlines the standard procedure for measuring the radial and axial internal clearance of rolling element bearings used in airframe controls.
2014-09-25
Standard
AMS4257
This specification covers an aluminum alloy in the form of extruded bars, rods, and profiles.
2014-09-25
WIP Standard
AS6039E
This specification covers sealed, self-aligning, anti-friction, rod end ball bearings with application in temperature ranges (1) -65°F to 250°F and (2) -65°F to 300°F with 20% reduction of dynamic load carrying capacity when subjected to operation above 250° F.
2014-09-24
WIP Standard
AMS4824E
This specification has been declared "CANCELLED " by the Aerospace Materials Division, SAE, as of January 2009. By this action, this document will remain listed in the Numerical Section of the Index of Aerospace Material Specifications indicating that it has been "CANCELLED ".
2014-09-24
WIP Standard
AMS4822G
This specification has been declared "CANCELLED " by the Aerospace Materials Division, SAE, as of January 2009. By this action, this document will remain listed in the Numerical Section of the Index of Aerospace Material Specifications indicating that it has been "CANCELLED ".
2014-09-23
Standard
AS85049/148
Scope is unavailable.
2014-09-23
Standard
AS3484C
Scope is unavailable.
2014-09-23
Standard
AS3535B
Scope is unavailable.
2014-09-22
WIP Standard
AS5830A
This aerospace specification defines the requirements for a threadless, flexible, conductive, self-bonding coupling assembly which, when installed on fixed cavity ferrules, provides a flexible, current carrying connection for joining tubing and components in aircraft fuel, vent and other systems. The assembled coupling is designed to provide interchangeability of parts and components between qualified manufacturers for the service life of the aircraft system. The assembled coupling is for use from -65 to +200 °F at nominal operating pressures (125 psig for -08 through -64 and 30 psig for -72 through -88). This aerospace specification is a departure from prior qualification practices for assembled couplings. Prior practice sought to validate this type of assembled coupling design by conducting a sequence of tests on sets of coupling assemblies. There were multiple test sequences and each was conducted on a different set of coupling assemblies.
2014-09-22
WIP Standard
J1065
This SAE Information Report is intended to provide design guidance in the selection of steel tubing and related tube fittings for general hydraulic system applications. The information presented herein is based on tubing products which conform to SAE standards listed in the reference section. Purpose The purpose of this document is to provide nominal reference working pressures for selecting tube material, OD size and wall thickness for given hydraulic system working pressures based on desired 4 to 1 design factor of the applicable burst pressure rating.
2014-09-17
WIP Standard
AS90328A
No scope available.
2014-09-16
Journal Article
2014-01-2144
Marco Amrhein, Jason Wells, Eric Walters, Seana McNeal, Brett Jordan, Peter Lamm
Abstract Transient operating conditions in electrical systems not only have significant impact on the operating behavior of individual components but indirectly affect system and component reliability and life. Specifically, transient loads can cause additional loss in the electrical conduction path consisting of windings, power electronic devices, distribution wires, etc., particularly when loads introduce high peak vs. average power ratios. The additional loss increases the operating temperatures and thermal cycling in the components, which is known to reduce their life and reliability. Further, mechanical stress caused by dynamic loading, which includes load torque cycling and high peak torque loading, increases material fatigue and thus reduces expected service life, particularly on rotating components (shaft, bearings).
2014-09-16
Journal Article
2014-01-2242
Samuel Baha II
Hybrid (bolted/bonded) joining is becoming one of the innovative joining processes for light weight structures in the transport industry, especially in the aerospace industry where weight reduction and high joining requirements are permanent challenges. Combining the adhesive bonding with the mechanical joining -riveting for instance- can lead to an enhancement of the properties of the joint compared to the wide established riveting, as a result of a synergistic load bearing interaction between the fastener and the adhesive bondline. The influence of the rivet installation process on a hybrid joint regarding the joint stress state, the change of the bondline thickness as well as its effects on the joint performance and load transfer are some of the factors that drive the users to a better understanding of the hybrid joining process.
2014-09-16
Journal Article
2014-01-2241
Jamie Skovron, Laine Mears, Durul Ulutan, Duane Detwiler, Daniel Paolini, Boris Baeumler, Laurence Claus
Abstract A state of the art proprietary method for aluminum-to-aluminum joining in the automotive industry is Resistance Spot Welding. However, with spot welding (1) structural performance of the joint may be degraded through heat-affected zones created by the high temperature thermal joining process, (2) achieving the double-sided access necessary for the spot welding electrodes may limit design flexibility, and (3) variability with welds leads to production inconsistencies. Self-piercing rivets have been used before; however they require different rivet/die combinations depending on the material being joined, which adds to process complexity. In recent years the introductions of screw products that combine the technologies of friction drilling and thread forming have entered the market. These types of screw products do not have these access limitations as through-part connections are formed by one-sided access using a thermo-mechanical flow screwdriving process with minimal heat.
2014-09-16
Technical Paper
2014-01-2263
Eric Barton, Dan Hasley, Joey Jackson
Abstract The following is a unique case study expounding on automatic fastening technology designed and engineered to ramp up a Tier 2 supplier that had no experience with automatic fastening, to efficiently produce a large volume of fuselage panel assemblies with demanding process requirements in a very short amount of time. The automation technology integrated for the skin to stringer & skin to window frame fastening were two GEMCOR G12 five-axis CNC All-Electric fastening systems coupled with a Cenit offline part programming system. This joint solution served as a launch vehicle for Center Industries to efficiently supply the full rate of fuselage panel assemblies for a large volume commercial aircraft program without having any automatic riveting experience.
2014-09-16
Journal Article
2014-01-2268
Pietro Ladisa, Gabriele Santonico
Abstract The marman interface is widely used in space applications to fit the spacecrafts to the launch vehicle and it is the same interface that allows the integration, test and transport of the satellites (AIT). It is usually designed for launch loads with related flight design safety factors and margins, but this is not always compatible with the handling and transport environment. In particular some criticalities are evidenced during the transport of satellites, where they are mounted in the container in horizontal position therefore subjected to bending loads due to gravity and transport dynamic loads. The study deals with a finite element analysis approach in the calculation and verification of marman clamp bands used for spacecraft AIT operations. The paper describes the details of modeling of the clamp band parts, the involved spacecraft launch vehicle interface ring and the MGSE interface.
Viewing 151 to 180 of 15451

Filter

Subtopics