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Viewing 1 to 30 of 19837
2016-09-27
Technical Paper
2016-01-2080
Carter L. Boad, Kevin Brandenstein
The newest generation of automated fastening machines require a feed system that is smaller, more flexible, and faster than any currently available. The feed system must be compact enough to fit on a robot base, yet have a capacity large enough to support unmanned production for hours. A large variety of fasteners must be supported and the entire system must be reloaded or reconfigured in minutes to match the next work piece being assembled by the machine. When requested by the part program, the correct fastener must be released directly and immediately into the feed tube to minimize cycle time. This paper describes a new “plate cartridge” feed system developed to meet these needs.
2016-09-27
Technical Paper
2016-01-2079
Alexander Janssen
The industry wide requirement of new highly flexible automated fastening systems in aircraft production has created the need for developing new fastening systems. This paper will focus on the development of the Frame Riveting Assembly Cell (FRAC) by BROETJE-Automation to meet this need. The new FRAC machine configuration is built for automated drilling and fastening of different aircraft type panels. It is highly flexible with a high speed positioning system mounted outer end effector. System travel is limited only by installed track length. The FRAC integrates well with conventional and reconfigurable automated fastening work holding tools.
2016-09-27
Technical Paper
2016-01-2086
Yinglin Ke, Weidong Zhu
Fastener selection and feeding for Automated Riveting Machines was always a challenge from the very beginning of this assembly technology. It was found appropriate to feed fasteners in air tubes from remote selection systems to process endeffectors. But fasteners are sometimes small, light weight aluminium parts, sometimes heavy titanium „bullets“. How to deal with large varieties of fastener dimension and mass? This paper will investigate the physics behind the air tube feeding process. By understanding the physical model it will become easy to predict the velocity and energy of a fastener at the end of its journey to the process endeffector. Feeding too fast will result in potential damage of aluminium fasteners at the endeffector pickup while heavy titanium fastener tend to damage the pickup system itself. State of the art seems to be trial and error to determine the optimum settings between speed and damage prevention and adjustment to fastener type.
2016-09-27
Technical Paper
2016-01-2085
Kyle Pritz, Brent Etzel, Zheng Wei
The automation takt time of wing assembly can be shortened with the use of single-sided temporary fasteners by providing temporary part clamping and doweling during panel drilling. Feeding these fasteners poses problems due to their complexity in design and overall heavy weight. In the past, Electroimpact has remotely fed these fasteners by blowing them through pneumatic tubing. This technique has resulted in occasional damage to fasteners during delivery and a complex feed system that requires frequent maintenance. Due to these issues, Electroimpact has developed a new fully automated single-sided temporary fastening system for installation of the LISI Clampberry fasteners in wing panels for the C919 wing factory in Yanliang, China. The feed system stores fasteners in gravity-fed cartridges on the end effector near the point of installation.
2016-09-27
Technical Paper
2016-01-2088
Eric Barton
The following case study details a new wing riveting solution designed with automation technology for high performance electric slug riveting capability. The “Rosie” wing riveting machine was engineered for GEMCOR’s patented squeeze-squeeze process to automatically install slug fasteners within Airbus wing panels.
2016-09-27
Technical Paper
2016-01-2087
Hunter O'Folan, Peter B. Zieve
There is an ever present risk of the lower ram of a riveting machine crashing into and damaging stringers and clips. The risk becomes greater as the parts get deeper and fasteners move closer to the web. In designing a riveting machine for the Lockheed C-130 we were concerned about the long lower anvil working in a challenging environment. We wanted the lower ram to drop down without causing damage even if the upset ram is offset and wrapped around a part. But we also wanted the lower tool to crash from the side without causing damage. Once this is achieved we have crash protection from five of six sides. A competing requirement is the need to strip collars. At Electroimpact we prefer to use the up-down action in the lower ram to do the stripping. We checked for the most difficult collar to strip and found that a 3/8 GP collar can take up to 3000 pounds of force to strip. Therefore we had a target that the magnetic pull-down on the lower anvil should exceed 3000 pounds.
2016-09-27
Technical Paper
2016-01-2081
Rodrigo Pinheiro, Robert Gurrola
The installation of common threaded aerospace fasteners by the application of a tightening torque to a nut or deformable locking collar is made possible by an internal wrenching element or recess feature adapted to the threaded end of a pin which accepts a mating anti-rotation key designed to partially balance or counter the applied torque. In highly-demanding applications such as the mechanical joining of composite structures accomplished by wet clearance fit installations of permanent fasteners, high nut or collar seating torques not adequately opposed by frictional resistance at the contact surfaces of the fastener and joint members effectively shift a greater proportion of the torque reaction requirement onto the recess and mating anti-rotation key which in turn can experience high torsional stresses exceeding their design capability and result in frequent service failures.
2016-09-27
Technical Paper
2016-01-2084
Curtis Hayes, Donald Peterson
Successfully riveting aerospace fatigue-rated structure (for instance, wing panels) requires achieving rivet interference between a minimum and a maximum value in a number of locations along the shank of the rivet. In unbalanced structure, where the skin is much thicker than the stringer, this can be particularly challenging, as achieving minimum interference at D2 (the exit of the skin) can often be a problem without exceeding the maximum interference at D4 (exit of the stringer). Softer base materials and harder, higher-strength rivets can compound the problem. This paper presents a solution that has been successfully implemented on a production commercial aircraft. The application of a special coating on the tail side die dramatically reduces D4 interference, which in some instances resulted in a reduction of more than 30%. This allowed an increase in forming force to increase D2 interference and made for a much more robust process.
2016-09-27
Technical Paper
2016-01-2083
Steven P. Smith
This paper traces the development of a single sided blind fastener at Airbus’ Broughton’s plant, commencing with the initial identification of the need for the A380XWB programme, through various prototypes testing early production trials. These requirements were further refined for A350XWB, resulting in a new contending fastener design, further evaluation and testing before pre-production trials and selection for A350XWB programme. Experience gained has led to further design development by the supplier leading to its current applications which are explained and the next steps of our Journey.
2016-09-27
Technical Paper
2016-01-2089
Jose Guerra cEng, Miguel Angel Castillo
During the year 2003 Aernnova decided to invest in automated machines procuring and installing a Broetje automatic machine (known in Aernnova as CIMPA) in Aernnova Berantevilla facility in order to perform operations such as drilling, countersinking or riveting in aircraft structures during its assembly. Due to the high load of work at that time in Aernnova mainly due to work packages from Embraer and Sikorsky, a solution was needed in order to assemble all the products required by our customer and deliver them on properly in terms of time and good quality. Several ideas came to our engineering team always having in mind the idea of reducing time being more competitive specially in repetitive operations and at the same time keeping good quality. Finally after a depth search, the option selected was an automated machine from Broetje that after some adjustments and customizations regarding our purposes could provide us the best solution.
2016-09-27
Technical Paper
2016-01-2103
Eric Barton
With commercial aircraft rates continuing to climb and factory floor space running out, GEMCOR was challenged to deliver a CNC automatic fastening solution that would accurately and reliably perform under high-speed conditions without a foundation. The primary design goal was to define an optimized CNC positioner configuration that could be installed on a typical 8.0” concrete factory floor without a foundation being required.
2016-09-27
Technical Paper
2016-01-2116
Peter Mueller-Hummel
ABSTRACT: Drilling holes into metal is a normal procedure, because the drill (metal drill) and the mal-leable capability of the metal compensate the insufficient cutting capability of a worn out drill. Drilling Composite by using the same drill (metal drill) is different procedure, because composite fibers are not mal-leable like metal at all. This fact is the reason why drills for metal are getting very hot by drilling Composite fibers. Even the diameter of the drilled holes in the carbon fiber parts are getting smaller than the drill them-selves afterwards. The hole in the metal part of the stack remains constant. This article explains the physical reason and characterizes the special features of a drill to realize a safe drilling Composite or CFRP/Aluminum stacks in H8 quality. Simplified theoretic models will show how CFRP/Aluminum stacks should be machined “Safe”, inside the cpk tolerance, without scratches even when the drill is worn.
2016-09-27
Technical Paper
2016-01-2128
Henry Guo
V-band joint is widely used in turbocharger industry. It is used to connect housings in turbocharger for both passenger vehicle and commercial vehicle applications, which can provide simple and robust solutions to replace bolt flanges. However, current issue for V-band joint in turbine side is the higher cost. The major cost for V-band joint comes from T-bolt which works in very hostile environment with high temperature and high vibration level. T-bolt is made from special stainless steel which takes around a half cost of total joint. This paper introduces a new V-band joint which replaces T-bolt from special bolt to standard bolt through changing bolt stress status from tension to compression, which provides possibility to reduce cost greatly. The prototype is made and performed static tests including anti-rotating torque test and salt spray test.
2016-09-27
Technical Paper
2016-01-2145
Ryan Haldimann
Inspection of fasteners prior to installation is critical to the quality of aerospace parts. Fasteners must be inspected for length/grip and diameter at a minimum. Inspecting the fasteners mechanically just prior to insertion can cause additional cycle time loss if inspection cannot be performed at the same time as other operations. To decrease fastener inspection times and to ensure fastener cartridges contain the expected fastener a system was devised to measure the fastener as it travels down the fastener feed tube. The optics system is designed such that two views 90° apart are captured of the fastener. The fastener is backlit using telecentric illuminators and imaged using a telecentric lens. The processing of the image occurs on the camera. The information as to what fastener the operator has loaded into the bowl is sent to the camera including the expected diameter and overall length.
2016-09-27
Technical Paper
2016-01-2098
Christophe Vandaele, Vincent Defrance, Etienne Gueydon
With more than 10 000 aircrafts in their order backlog, automated assembly is of critical importance to the progress for aircraft manufacturers. Moreover to obtain maximum benefit from automation, it is necessary to achieve not only an integrated fastener cell, but also a real breakthrough in fasteners technology. The optimum solution, known as "One Side Assembly", performs the whole assembly sequence from one side of the structure using an accurate robot arm equipped with a Multi function End effector and high performances fasteners. This configuration provides an efficient and flexible automated installation process, superior to current solutions which are typically, large scale, capital intensive, systems, which still require operators to complete or control the fastener installation. The search for a technological breakthrough in this domain has been targeted for more than 15 years by the majors aircrafts manufacturers.
2016-09-13
Event
2016-07-25 ...
  • July 25-26, 2016 (8:30 a.m. - 4:30 p.m.) - Tysons, Virginia
  • December 1-2, 2016 (8:30 a.m. - 4:30 p.m.) - Troy, Michigan
Training / Education Classroom Seminars
SAE International is pleased to announce that this course will also be offered in London UK at IMechE, One Birdcage Walk, SW1H9JJ during the week of June 6th through June 10th. The SAE Europe Aerospace Training Week is a series of courses designed especially for the aerospace engineer. For additional information about this course, others and to register, please visit http://sae-europe.org/aerospace-training-week-june-2016-london/#programme. The requirements for producing an FAA approved replacement part can be daunting.
2016-06-30
Standard
J2270_201606
This SAE Standard covers both quality assurance and installation requirements for fasteners. This document establishes engineering criteria and guidance for quality assurance requirements (including Test and Inspection) for procurement of threaded fasteners where such criteria and guidance is not otherwise provided by existing fastener standards or specifications. The document also provides requirements and test procedures for self-locking fasteners including those manufactured by the installing activity. This document also provides requirements for the selection and use of fastener lubricants, additional corrosion protection treatments, fastener tightening procedures, and the use of thread-locking compounds.
2016-06-30
Standard
AMS6276L
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
2016-06-30
Standard
AMS6494B
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
Viewing 1 to 30 of 19837

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