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Viewing 1 to 30 of 2615
2015-09-15
Event
2015-09-15
Technical Paper
2015-01-2497
George Nicholas Bullen
The introduction of composite materials onto air vehicles has complicated the traditional hole/countersink assessment criteria due its finished-part thickness variability; softer and dissimilar properties than the metallic substructure where it is mounted and attached; and the increased attention to other acceptance criteria such as fiber tear, fiber pull, and moisture propagation in the hole that degrades fastener capability. The addition of composite materials further complicates the assembly process by adding a boundary layer of liquid shim or sealant between the composite piece (usually a skin) and the substructure. Current hole inspection systems are absent the ability to assess the interior condition of the composite hole such as fiber tear, damage to the liquid shim, and debris or burrs between the multiple stacks of dissimilar material.
2015-09-15
Technical Paper
2015-01-2512
Mark W. Sydenham, Tim Brown
In numerous applications where access to the backside of the work piece is restricted, aircraft manufactures opt to install blind fasteners like the OSI-Bolt. However, one issue with using blind fasteners is that they can require visual inspection to verify proper installation. Electroimpact has developed an automated solution for installing OSI-Bolts which increases process reliability and decreases cost by eliminating the need for visual inspection. This solution utilizes Electroimpact’s existing accurate robotic system together with new hardware designed specifically for OSI-Bolts. In addition to automated drilling and fastener installation, this system performs numerous quality checks to insure the installed fastener meets engineering requirements. Before installing the fastener, the system measures actual stack thickness and the length of the fastener to ensure that the proper grip is installed.
2015-09-15
Technical Paper
2015-01-2491
Paul Haworth, Donald Peterson, Curtis Hayes
A new high speed forming process for fatigue rated index head rivets used in wing panel assembly using ball-screw based servo squeeze actuation has been developed. The new process is achieved using a combination of force and position control and is capable of forming to 40,000 lbs at rates of up to 200,000 lbs/second whilst holding the part location to within +/- 10 thousandths of an inch. Multi-axis riveting machines often have positioning axes that are also used for fastener upset. It is often the case that while a CNC is used for positioning control, another secondary controller is used to perform the fastener upset. In the new process, it has been possible to wrap the control of the upset process into the machine CNC and thus eliminating any separate controllers. The fastener upset force profile is controlled throughout the forming of the rivet by using a closed loop force control system that has a load cell mounted directly behind the stringer side forming tool.
2015-07-28
Standard
AS172236D
SCOPE IS UNAVAILABLE.
2015-07-28
Standard
MA3423A
SCOPE IS UNAVAILABLE.
2015-07-20
WIP Standard
AS4108/1A
SCOPE IS UNAVAILABLE.
2015-07-20
WIP Standard
AS4108/3A
SCOPE IS UNAVAILABLE.
2015-07-20
WIP Standard
AS4108/2A
SCOPE IS UNAVAILABLE.
2015-07-20
Standard
MA3393A
SCOPE IS UNAVAILABLE.
2015-07-20
Standard
MA3428A
SCOPE IS UNAVAILABLE.
2015-07-20
Standard
MA3394A
SCOPE IS UNAVAILABLE.
2015-07-11
Standard
AS3261B
SCOPE IS UNAVAILABLE.
2015-07-07
WIP Standard
MA3422A
No scope available.
2015-07-07
WIP Standard
MA3424A
No scope available.
2015-07-07
WIP Standard
MA3426A
No scope available.
Viewing 1 to 30 of 2615

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