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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 ".
2014-09-24
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
AMSQQA591B
This specification has been declared “NONCURRENT” by the Aerospace Materials Division, SAE, as of August 2009. It is recommended, therefore, that this specification not be specified for new designs. “NONCURRENT” refers to those specifications which have previously been widely used and which may be required for production or processing of existing designs in the future. The Aerospace Materials Division, however, does not recommend these specifications for future use in new designs. “NONCURRENT” specifications are available from SAE upon request.
2014-09-24
WIP Standard
AMS5707M
This specification covers a corrosion and heat resistant nickel alloy in the form of bars, forgings, flash welded rings, and stock for forging or flash welded rings.

These products have been used typically for parts, such as cases, requiring high strength up to 1500 degrees F (816 degrees C) and oxidation resistance up 1750 degrees F (954 degrees C), but usage is not limited to such applications.

2014-09-24
WIP Standard
AMS5704K
This specification covers a corrosion and heat resistant nickel alloy in the form of forgings and forging stock.

These forgings have been used typically for rotating parts, such as compressor blades, discs, hubs, shafts, and spacers requiring high strength up to 1500 degrees F (816 degrees C) and oxidation resistance up to 1750 degrees F (954 degrees C), but usage is not limited to such applications.

2014-09-23
WIP Standard
GAD14AA
1) Retain section heading "Response to Heat Treatment" when solution treatment is performed. 2) Change section heading to "Response to Temper Conversion" when precipitation aging is the only thermal processing performed. In this instance, also include a clear description of the Starting Temper and Ending Temper - examples: "Response to Heat Treatment The product, after solution and precipitation heat treatment to the T62 temper (See AS1990) in accordance with AMS 2772, shall have the properties listed in Table X." "Response to Temper Conversion Product in the T4 temper, precipitation heat treated to the T62 temper (See AS1990) in accordance with AMS2772, shall have the properties shown in Table Y."
2014-09-23
WIP Standard
AMS2475H
This specification establishes the requirements for chromate conversion coatings on magnesium alloys. This process has been used typically to improve corrosion resistance and adherence of organic finishes but usage is not limited to such applications. The dichromate treatment may not be suitable for alloys with high manganese content. The chrome pickle treatment has been used as touch-up for previously dichromate-treated surfaces and for improving corrosion protection temporarily, but usages are not limited to such applications.
2014-09-23
WIP Standard
AMS2481K
This specification covers the requirements for a manganese phosphate coating on ferrous alloys.
2014-09-23
WIP Standard
AMS2482E
This specification establishes the requirements for a hard aluminum oxide coating, impregnated or codeposited with polytetrafluoroethylene (PTFE) on aluminum alloys.
2014-09-23
Standard
AS3535B
Scope is unavailable.
2014-09-20
WIP Standard
AMS2467A
No Scope Available
2014-09-19
Standard
AMS4162E
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles, and tubing under 3.00 inches (76.2 mm) in diameter, least thickness, or wall thickness and 25 in 2 (161 cm 2 ) or less in cross-sectional area.
2014-09-16
Standard
ARP169B
This SAE Aerospace Recommended Practice (ARP) defines a method of numbering aricraft engine cylinders.
2014-09-16
Technical Paper
2014-01-2127
Karl Strauss
Abstract “Today's electronic components rely on principles of physics and science with no manufacturing precedence and little data on long term stability and reliability.” [1] Yet many are counting on their reliable performance years if not decades into the future, sometimes after being literally abandoned in barns or stored neatly in tightly sealed bags. What makes sense? To toss everything away, or use it as is and hope for the best? Surely there must be a middle ground! With an unprecedented number of missions in its future and an ever-tightening budget, NASA faces the daunting task of doing more with less. One proven way for a project to save money is to use already screened and qualified devices from the spares of its predecessors. But what is the risk in doing so? How can a project reliably count on the value of spare devices if the risk of using them is not, in itself, defined? With hundreds of thousands of devices left over from previous missions, the parts bins of NASA hold a wealth of electronic components, (possibly) ready for use many years after their production.
2014-09-16
Technical Paper
2014-01-2138
Ron Wang, Michelle Bash, Steven D. Pekarek
Abstract In this research, excitation strategies for a salient-pole wound rotor synchronous machine are explored using a magnetic equivalent circuit model that includes core loss. It is shown that the excitation obtained is considerably different than would be obtained using traditional qd-based models. However, through evaluation of the resulting ‘optimal’ excitation, a relatively straightforward field-oriented type control is developed that is consistent with a desire for efficiency yet control simplicity. Validation is achieved through hardware experiment. The usefulness/applicability of the simplified control to variable speed applications is then considered.
2014-09-16
Technical Paper
2014-01-2275
Karl-Erik Neumann, Robert Reno
Abstract The utilization of new materials and tightening of desired tolerances has driven the advancement of Practical and Portable Automated Machining. Increased demand in volume within the aerospace industry not only requires minimizing the amount of manual operations, but also applying automation inside existing manual fixtures. In the past, manual labor, with drastic limitations on achievable accuracies, has been utilized in areas that machine tools cannot either access or the limited amount of work does not justify the expense of additional machines. Assemblies requiring critical hole alignment or drilling through stack materials often are difficult to achieve using manual operations. The solution is a practical and very portable machining unit that is small enough to fit into otherwise difficult areas and is lightweight enough to be either moved into position by small machines or quickly disassembled/assembled with each subassembly capable of being positioned manually. The criteria for the developed machine were that it be; Lightweight - Under 250 lbs allowing for manual positioning or easy mechanical positioning Accurate - Maintain accuracy achieved with current PKM technology Rigid - Capable of drill/mill/orbital of titanium Flexible - Can be mounted in any orientation and is adaptable to rail, vacuum, fixed leg, gantry, etc.
2014-09-16
Technical Paper
2014-01-2238
Richard Kingston
Abstract Industrial robots are extremely good at repetitive tasks. They exhibit excellent repeatability, making them ideal candidates for many tasks. However, increasing use of CAD based offline programming highlights the fact that industrial robots are generally not accurate devices. Several approaches have been used to compensate for this deficiency. Robot calibration is well established and factory calibrated robots are available from most industrial robot manufacturers. This can improve the spatial accuracy of robots to figures better than 1mm which is adequate for most robot processes in use today. Improvements in accuracy beyond this point can be achieved if the working range of the robot is constrained in some way. For example, limiting a robot to working in a single plane or restricting the robot to a reduced work volume can contribute to significant improvements in accuracy. However, for applications requiring high accuracy without these constraints some additional control is needed.
2014-09-16
Technical Paper
2014-01-2237
Rainer Mueller, Matthias Vette, Andreas Ginschel, Ortwin Mailahn
Abstract The global competition challenges aircraft manufacturers in high wage countries. The assembly of large components happens manually in fixed position assembly. Especially the completion of the inner fuselage structure is done 100% manually. The shells have to be joined with rivets and several hundred clips have to be assembled to connect the shell to the frames. The poise of the worker is not ergonomic so a lot of physical stress is added to the worker and minimizes the working ability. Aircraft manufacturers need a lot of different production resources and qualified persons for the production, which provokes higher costs. Due to these high costs there is a demand for automated reconfigurable assembly systems, which offer a high flexibility and lower manufacturing costs. The research project “IProGro” deals with this challenge and develops innovative production systems for large parts. On one hand the flexibility is reached by a reconfigurable fixture for the components on the other hand it is achieved by assistance systems, which guide staff during assembly processes.
2014-09-16
Technical Paper
2014-01-2246
Yanbin Yao
Abstract Drilling plays a significant process in the aircraft manufacturing. This paper develops a robot automatic drilling system for processing the titanium alloy, aluminum alloy and laminated composites component of aircraft. The accurate robot drilling system is comprised of ABB IRB6640-235 robot, drilling end-effector, end-effctor control system and vision system. Experimental results show that the system absolute location precision is within 0.3mm, and the drilling efficiency can be up to four holes per minute. The drilling efficiency and quality of the aircraft component can be increased immensely by the developed robot automatic drilling system.
2014-09-16
Technical Paper
2014-01-2264
Peter B. Zieve, Osman Emre Celek, John Fenty
Abstract The E7000 riveting machine installs NAS1097KE5-5.5 rivets into A320 Section 18 fuselage side panels. For the thinnest stacks where the panel skin is under 2mm (2024) and the stringer is under 2mm (7075), the normal process of riveting will cause deformation of the panel or dimpling. The authors found a solution to this problem by forming the rivet with the upper pressure foot extended, and it has been tested and approved for production.
2014-09-16
Technical Paper
2014-01-2256
Roger Holden, Paul Lightowler, Simon Andreou
Abstract The 30 month COMET project aims to overcome the challenges facing European manufacturing industries by developing innovative machining systems that are flexible, reliable and predictable with an average of 30% cost efficiency savings in comparison to machine tools. From a conceptual point of view, industrial robot technology could provide an excellent base for machining being both flexible and cost efficient. However, industrial robots lack absolute positioning accuracy, are unable to reject disturbances in terms of process forces and lack reliable programming and simulation tools to ensure right first time machining, once production commences. These three critical limitations currently prevent the use of robots in typical machining applications. The COMET project is co-funded by the European Commission as part of the European Economic Recovery Plan (EERP) adopted in 2008. The EERP proposes the launch of Public-Private Partnerships (PPP) in three sectors, one of them being Factories of the Future (FoF).
2014-09-16
Technical Paper
2014-01-2257
Roger Holden, Paul Lightowler, Simon Andreou
Abstract The 30 month COMET project aims to overcome the challenges facing European manufacturing industries by developing innovative machining systems that are flexible, reliable and predictable with an average of 30% cost efficiency savings in comparison to machine tools. From a conceptual point of view, industrial robot technology could provide an excellent base for machining being both flexible and cost efficient. However, industrial robots lack absolute positioning accuracy, are unable to reject disturbances in terms of process forces and lack reliable programming and simulation tools to ensure right first time machining, once production commences. These three critical limitations currently prevent the use of robots in typical machining applications. The COMET project is co-funded by the European Commission as part of the European Economic Recovery Plan (EERP) adopted in 2008. The EERP proposes the launch of Public-Private Partnerships (PPP) in three sectors, one of them being Factories of the Future (FoF).
2014-09-16
Technical Paper
2014-01-2259
Greg Adams
Abstract Electroimpact has developed a second generation of mobile robots with several improvements over the first generation. The frame has been revised from a welded steel tube to a welded steel plate structure, making the dynamic response of the structure stiffer and reducing load deflections while maintaining the same weight. The deflections of the frame have been optimized to simplify position compensation. The caster mechanism is very compact, offers greater mounting flexibility, and improved maneuverability. The mechanism uses a pneumatic airbag for both lifting and suspension. The robot sled has been improved to offer greater rigidity for the same weight, and dual secondary feedback scales on the vertical axis further improve the rigidity of the overall system. Maintenance access has been improved by rerouting the cable and hose trays, and lowering the electrical cabinet. The mobile robot is sized so it can be shipped complete on a lowboy trailer for deliveries that can be completed by truck.
2014-09-16
Technical Paper
2014-01-2267
George Nicholas Bullen
Abstract Rapid advances in cloud-based computing, robotics and smart sensors, multi-modal modeling and simulation, and advanced production are transforming modern manufacturing. The shift toward smaller runs on custom-designed products favors agile and adaptable workplaces that can compete in the global economy. This paper and presentation will describe the advances in Digital Manufacturing that provides the backbone to tighten integration and interoperability of design methods interlinked with advanced manufacturing technologies and agile business practices. The digital tapestry that seamlessly connects computer design tools, modeling and simulation, intelligent machines and sensors, additive manufacturing, manufacturing methods, and post-delivery services to shorten the time and cost between idea generation and first successful product-in-hand will be illustrated.
2014-09-16
Technical Paper
2014-01-2250
Nicholas Lum, Qun Luo
Abstract Electroimpact has designed and manufactured a flexible tooling system for the E7000-ARJ horizontal panel riveter. This tooling design accommodates panel sizes from 3.5m to 10m long, with a variety of straight and tapered curvatures. The tooling is re-configured manually and utilizes removable index plates that can be adapted to accommodate new panel types. This type of tooling is ideal for value-conscious applications where a single machine must process a large range of panel styles. Electroimpact is currently using this system to tool 17 different styles of pre-tacked panels on a single E7000-ARJ machine. This flexible system does not require large removable form boards or custom frames that index one type of panel. Instead it uses 4 form boards that are permanently mounted to the picture frame by linear rails, allowing them to index anywhere along the 10m working envelope. Each form board holds several rail mounted surface indexes that are adjusted to accommodate different panel curvatures.
2014-09-16
Technical Paper
2014-01-2249
Thomas G. Jefferson, Svetan Ratchev, Richard Crossley
Abstract Aerospace assembly systems comprise a vast array of interrelated elements interacting in a myriad of ways. Consequently, aerospace assembly system design is a deeply complex process that requires a multi-disciplined team of engineers. Recent trends to improve manufacturing agility suggest reconfigurability as a solution to the increasing demand for improved flexibility, time-to-market and overall reduction in non-recurring costs. Yet, adding reconfigurability to assembly systems further increases operational complexity and design complexity. Despite the increase in complexity for reconfigurable assembly, few formal methodologies or frameworks exist specifically to support the design of Reconfigurable Assembly Systems (RAS). This paper presents a novel reconfigurable assembly system design framework (RASDF) that can be applied to wing structure assembly as well as many other RAS design problems. The framework is a holistic, hierarchical approach to system design incorporating reconfigurability principles, Axiomatic Design and Design Structure Matrices.
2014-09-16
Technical Paper
2014-01-2248
Santiago Droll
In contemporary industries the demand for very accurate robots is continuously growing. Yet, robot vendors are limited in the achievable accuracy of their robots, as they have no means to provide a direct end-effector feedback. Therefore, most approaches aim to identify an accurate model of the robotic system, thus providing compensation factors to correct the deflections. Models, however, are unable to represent the real physical system in a sufficient manner for path correction. The non-linearities in robotic systems are difficult to model and the dynamics cannot be neglected. A better approach is, therefore, to use direct end-effector position and orientation feedback from an external sensor as, e.g. a Leica laser tracker. The measured data can directly be compared to the nominal data from the path interpolator. Hence, the data are independent of the kinematic robot model. The residual errors can be used to calculate correction values in Cartesian space, which are mapped to each individual robot joint, thus providing a fast path correction algorithm.
2014-09-16
Technical Paper
2014-01-2234
Nelson W. Sorbo, Jason J. Dionne
Abstract The use of composite materials and composite stackups (CO-Ti or CO-Al) in aerospace and automotive applications has been and will continue to grow at a very high rate due to the high strength and low weight of the materials. One key problem manufacturers have using this material is the ability to efficiently drill holes through the layers to install fasteners and other components. This is especially true in stackups of CFRP and titanium due to the desire of drilling dry for the CFRP layer and the need for cooling when drilling the high strength Ti layer. By using CO2 through tool cooling, it is possible to protect both layers. Through work supported by the National Science Foundation (NSF) and Department of Energy (DOE) it is shown that CO2 through tool cooling productivity can be significantly increased while maintaining required hole tolerances in both the composite and Ti layers. Improvements in tool life have been demonstrated when compared to either emulsion or dry drilling.
2014-09-16
Technical Paper
2014-01-2253
Ralf Schomaker, Richard Pedwell, Björn Knickrehm
Abstract As a result of the increasing use of fibre reinforced plastic (FRP) components in a modern commercial aircraft, manufacturers are facing new challenges - especially with regards to the realisation of significant build rates. One challenge is the larger variation of the thickness of FRP components compared with metal parts that can normally be manufactured within a very narrow thickness tolerance bandwidth. The larger thickness variation of composite structures has an impact on the shape of the component and especially on the surfaces intended to be joined together with other components. As a result, gaps between the components to be assembled could be encountered. However, from a structural point of view, gaps can only be accepted to a certain extent in order to maintain the structural integrity of the joint. Today's state of the art technologies to close gaps between FRP structures comprise shimming methods using liquid and solid shims. Another option is the use of peelable shims that offer significant economic benefits compared with liquid and solid shims.
Viewing 91 to 120 of 19740

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