Criteria

Display:

Results

Viewing 31 to 60 of 19606
Technical Paper
2014-09-16
Karl-Erik Neumann, Robert Reno
Practical and Portable Automated Machining 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.
Technical Paper
2014-09-16
Joseph R. Malcomb
Automated countersink measurement methods which require contact with the workpiece are susceptible to a loss of accuracy due to cutting debris and lube build-up. This paper demonstrates a non-contact method for countersink diameter measurement on CFRP which eliminates the need for periodic cleaning. Holes are scanned using a laser profilometer. Coordinates for points along the countersink edge are processed with a unique filtering algorithm providing a highly repeatable estimate for major and minor diameter.
Technical Paper
2014-09-16
Roger Holden, Paul Lightowler, Simon Andreou, William Thomas, Jon Moran
This is a work package within STeM (Structural Technology Maturity), a UK Government research project aimed at stimulating R&D and innovation activities. STeM is an Industry lead TSB (Technology Strategy Board) & BIS (Business Innovation & Skills) funded initiative that supports new concepts in wing structure and manufacturing, to enable expansion of the boundaries of aerodynamic performance. The project goal was to deliver "one-shot" robotic drilling and fastening of an innovative composite aircraft assembly for GKN Aerospace. The first major technology advance was to prove that a robot can take one tool (drill and countersink) and make the hole (up to ¼" diameter), then pick-up another separate tool (fastener) and go to exactly the same place/vector to apply the fastener. This meant a multi-function end effector wasn't needed - which in-turn meant only a small payload robot is needed, on a small width rail. This dramatically reduces the capital investment in the robot solution, and requires much less energy, so it's a greener solution as well.
Technical Paper
2014-09-16
Greg Adams
Electroimpact has developed a second generation of mobile robots with several improvements over the first generation. The frame has been revised to a welded 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 shipped complete on a lowboy trailer for deliveries that can be completed by truck. It can also be broken down for container shipping, and reassembly at the customers’ site is a straightforward process.
Technical Paper
2014-09-16
Zachary A. Collier, Steve Walters, Dan DiMase, Jeffrey M. Keisler, Igor Linkov
Counterfeit electronic components entering into critical infrastructure and applications through the global supply chain threaten the economy and national security. In response to the growing threat from counterfeits, the Society of Automotive Engineers G-19 Committee is developing AS6171. This aerospace standard is focused on testing facilities with a goal of standardizing the process of counterfeit detection. An integral part of the standard is a semi-quantitative risk assessment method. This method assigns risk scores to electronic components based on a number of relevant criteria, and places the components into one of five risk tier levels corresponding to an appropriate level of laboratory testing to ensure the authenticity of the component. In this way, the methodology aims at standardizing the risk assessment process and bases the identified risk as guidance for commensurate testing protocols. This paper outlines the risk assessment method contained within AS6171 and briefly explores other complementary efforts and research gaps within the G-19 and electronics community.
Technical Paper
2014-09-16
Richard Kingston
This project presented in this paper is the result of a package of work undertaken as part Manufacturing Technology Centre's Core Research Project programme and backed by MTC members Airbus, GKN, Spirit, Rolls-Royce and Hexagon Metrology. The Metrology Assisted Robotic Automation (MARA) project is MTC's attempt to tackle the issue of industrial robot positional & path accuracy and builds on some of the principals exhibited on commercially available metrology guidance systems. To date, commercially available metrology guidance systems are only capable of performing static correction of a single robot point position. The MARA solution described in this paper details a software development that uses data captured from a metrology device, namely a Leica T-Mac system, and performs a dynamic correction of, not only, a single robot point position but also a dynamic correction of the robot path to accuracies better than +/-0.2 mm.
Technical Paper
2014-09-16
Pietro Ladisa, Gabriele Santonico
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 assembly, integration, test and transport of the satellites (AIT). The satellites marman interfaces are usually designed for launch loads with related flight design safety factors and margins, but this is not always compatible with the handling and transport needings and 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 environment. The study deals with a finite element analysis approach in the calculation and verification of marman clamp bands used for spacecraft AIT operations, where in some chases the loads can be higher or more critical than during launch phases. The paper describes the details of modelling of the clamp band parts, the involved spacecraft launch vehicle interface ring and the MGSE interface.
Technical Paper
2014-09-16
Ruiqiang Lu, Zhixia Hou
With the development of many new technologies in aircraft manufacturing area and the increasing competition of the global market, aircraft manufacturing enterprises have to reduce the total production time and increase the cost-efficiency, with the consideration of high speed response to the changes inside enterprises or in the environment. Production planning and scheduling is a significant process in manufacturing, especially for complicated part or component processing. This paper proposes an agent based multi-objective optimization approach for production planning and scheduling based on genetic algorithms. It aims to minimize the total production cost and simultaneously reducing the emission released during production, and the delivery time and equipment constraints are satisfied as well. The new approach is employed into a workshop for aircraft engine blade manufacturing. Exprimental results show that a group of Pareto optimal solutions are gained, which can be provided to the enterprise decision maker to select according to different actual conditions.
Technical Paper
2014-09-16
Ryan Haldimann, Daniel Orf
Description: Utilization of a vision system to automate mobile assembly machines facilitating movement, placement and accuracy. Problem: To create a flat floor factory where machine tools used for assembly automation need to position rapidly and accurately while moving to multiple positions on the factory floor. Solution: The solution falls to two distinct modes, movement and placement, both of which use the same two-camera vision system. To automate movement, the vision system and a PLC are used to guide the mobile platform to each location with barcodes and optical guidelines placed on the factory floor. Accurate placement is accomplished using a floor resynchronization methodology which utilizes the vision system and miniature embedded targets to rapidly determine position. The combination allows for an early reconfigurable accurate system for a Lean manufacturing environment.
Technical Paper
2014-09-16
Ralf Schomaker, Richard Pedwell, Björn Knickrehm
As a result of the increasing use of fibre reinforced plastic (FRP) components, exceeding more than 50% of the overall structural weight of a modern commercial aircraft, manufacturers are facing new challenges – especially with regards to the achievement 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, significant gaps between the components to be assembled could be encountered. However, from a structure mechanical point of view, gaps can only be accepted to a certain extent in order to maintain the integrity of the joint. Any exceeding of the permissible gap height requires corrective measures, therefore. Today’s state of the art technologies to close gaps between FRP structures comprise shimming methods using liquid, solid or peelable shims.
Technical Paper
2014-09-16
Yvan Blanchard
Today, the design of complex composites structures is managed by taking into account both engineering and basic manufacturing constraints, as ply shape and continuity. But in order to optimize the laminate, it is strongly advised to also take into account material and process constraints, as the machine limitations in the case of automated manufacturing use. A new innovative software technology has been developed to include engineering, material and process specifications, to help designers and NC programmers to optimize the final layup program in terms of structural properties and productivity. A typical aerospace case studies will be presented to highlights these software capabilities.
Technical Paper
2014-09-16
Kim Schwake, Robert Weidner, Jens Wulfsberg, Frank Neuhaus
The manuscript describes the development of a flexible, cost-effective production system based on standard industrial robots for major component assembly. This novel approach enables the aircraft manufactures to keep their production future-oriented and stay competitive. Currently the aircraft industry is confronted with new challenges due to changes of the aircraft market. Changed customer demands have a major impact especially on production planning. The conventional way within aircraft production which is characterized by isolated production lines with special machinery cannot encounter the resulting requirements of flexibility and reactivity. New aircraft production systems have to be lean and flexible to conquer future challenges. The approach of the present manuscript analyses the actual situation of the major component assembly using the example of fuselage assembly. It states identified requirements for a new assembly system and provides an overview of the procedure of conception.
Technical Paper
2014-09-16
Rainer Mueller, Matthias Vette, Andreas Ginschel, Ortwin Mailahn
Innovative production technologies for large part components Prof. Dr. -Ing. Rainer Müller, Dipl.-Wirtsch.-Ing.(FH) Matthias Vette M.Eng., Andreas Ginschel M.Sc. , Dipl.-Ing. Ortwin Mailahn Zentrum für Mechatronik und Automatisierungstechnik gGmbH Gewerbepark Eschbergerweg Gebäude 9 66121 Saarbrücken Germany Phone: +49 (0) 681 85787-544 E-Mail: a.ginschel@mechatronikzentrum.de Abstract Large part components are mostly assembled manually at fixed position assembly. There is a high demand of automated reconfigurable assembly systems. One reason is to reduce this people intensive work. Another reason is to cope with the rising variety of aircraft or wind turbine generator systems. The project “IProGro” is government funded by the European Union .The objective of the project is to develop innovative production technologies for large part components, which offer high flexibility. On one hand this flexibility is reached by a reconfigurable automated fixture for the components on the other hand by assistance systems, which guide the staff and provide information during the assembly process.
Technical Paper
2014-09-16
Helen Lockett, Sarah Fletcher, Nicolas Luquet
The installation of essential systems into aircraft wings involves numerous labour-intensive processes. Many human operators are required to perform complex manual tasks over long periods of time in very challenging physical positions due to the limited access and confined space. This level of human activity in poor ergonomic conditions directly impacts on speed and quality of production but also, in the longer term, can cause costly human resource problems from operators’ cumulative development of musculoskeletal injuries. These problems are exacerbated in areas of the wing which house multiple systems components because the volume of manual work and number of operators is higher but the available space is reduced. To improve the efficiency of manual work processes which cannot yet be automated we therefore need to consider how we might redesign systems installations in these congested areas to better enable operator access and reduce production time. This paper describes a recent study that applied design for assembly and maintainability principles and CATIA v5 computer aided design software to identify small design changes in a congested wing area.
Technical Paper
2014-09-16
Samira Keivanpour, Christian Mascle, Daoud Ait Kadi
The End of Life phase of Aircraft is a relatively complex phase in life cycle of this product. The retired Aircrafts need to be parked in a certain conditions. The valuable parts are disassembled and the rest of them are dismantled. Materials are separated and upgraded, waste is burned or deserted and toxic materials restrained or incinerated. All of these activities should be performed in an ecologically right manner; however, collectively produced added values for all stakeholders need to be considered. This paper aims to provide a conceptual framework for value chain analysis of Aircraft recycling process in the context of sustainable development. The value chain related to recycling aircraft at the end of life was chosen to generate an in-depth analysis of a value chain, considering environmental and socio-economic concerns. The value chain framework for recycling of fleets is identified. The key processes with environmental and social impacts are determined. The decision making process along the value chain and the policy framework including codes, regulations and standards are addressed.
Technical Paper
2014-09-16
Rostislav Sirotkin, Galina Susova
Sirotkin R. Susova G. NIAT, Scherbakov G. AR IAC Abstract The problem of ensuring aviation safety was and remains actual. To realize requirements to the safety, established by standards of the international level, for example, AS9100C, AS9017 and MSG-3, is (expediently rational) to make use of national experience of the solution of this problem. Ensuring non-failure operation of parts of a design and systems of the planes / helicopters influencing safety of flights, in the Russian aviation industry is traditionally regulated by requirements of the national aviation standards establishing an order, the contents and methods of performance of the corresponding works at all stages of life cycle of a product Purpose of work (Objectives) To guarantee a normalized risk level of possible violation of safety of flights of the plane because of refusals by a way (on a basis) purposeful impact on critical parameters of critical elements (parts) of a design of a glider and the equipment during all life cycle (design, production, maintenance at operation).
WIP Standard
2014-07-24
At the Spring, 2014 meeting, a General Agreement Ballot was authorized to change the requirement for adhesion testing from being a lot test to being a periodic test.
Standard
2014-07-23
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
Standard
2014-07-23
This specification covers the heat treatment of titanium and titanium alloy mill products (raw material), including wrought and cast products, by material producers. This specification also covers furnace equipment requirements, test procedures, and general information for heat treating procedures, heat treating temperatures, and material test procedures for the heat treatment of titanium and titanium alloys. It also describes procedures that, when followed, have produced the desired properties within the limitations of the respective alloys.
Standard
2014-07-22
This specification covers an aluminum alloy in the form of plate. This plate has been used typically for parts requiring a high level of mechanical properties and resistance to exfoliation corrosion and moderate resistance to stress-corrosion cracking, but usage is not limited to such applications.
WIP Standard
2014-07-21
General Agreement Ballot will simplify the decarburization requirements of flat rolled products to that of the bar products and will eliminate the step procedure.
WIP Standard
2014-07-18
This specification covers quality assurance sampling and testing procedures used to determine conformance to applicable specification requirements of carbon and low-alloy steel forgings.
Standard
2014-07-17
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
Standard
2014-07-17
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
Standard
2014-07-17
This specification covers an aircraft-quality, low-alloy steel in the form of seamless tubing. This tubing has been used typically for thin wall-thickness sections where minimum tensile strength up to 160 ksi (1103 MPa) is required and where parts may be welded during fabrication, but usage is not limited to such applications.
Article
2014-07-15
Company says Fuselage Automated Upright Build is expected to yield safety, quality benefits; had been in development since 2012.
Article
2014-07-15
Northrop Grumman Corp. broke ground on a new $20 million Maryland Space Assembly and Test (M-SAT) facility on its Baltimore campus adjacent to Baltimore Washington International Thurgood Marshall Airport.
Article
2014-07-15
Volkswagen announced July 14 that a new midsize SUV will be built at its Chattanooga plant in Tennessee, in accordance with the company's Strategy 2018 plan calling for an expanded industrial footprint in the U.S.
Article
2014-07-15
Electric propulsion has been limited so far to small movements of the satellites once it is in its geostationary orbit. The Boeing 702SP innovation is its use of electric propulsion to raise the satellite from its launch-vehicle drop-off point to geostationary orbit.
WIP Standard
2014-07-15
Form: This specification covers an aluminum alloy in the form of plate products from 1.000 to 6.000 inches (152.40 mm) in thickness. Application: 7065-T7451 may be used in aerospace applications requiring high strength and fracture toughness, high resistance to stress-corrosion cracking and good resistance to exfoliation corrosion, but usage is not limited to such applications.
Viewing 31 to 60 of 19606

Filter

  • Article
    1234
  • Book
    54
  • Collection
    12
  • Magazine
    798
  • Technical Paper
    8351
  • Standard
    9157
  • Article
    9157