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Viewing 1 to 30 of 4042
2017-04-21
Event
2017-03-10
Event
2016-11-14 ...
  • November 14-16, 2016 (8:00 a.m. - 5:00 p.m.) - Tysons, Virginia
Training / Education Classroom Seminars
Internal audits are a requirement of the AS9100 Rev C standard and one of the fundamental requirements of the internal audit program is to verify the compliance of the organization's quality management system to the AS9100 standard. Internal auditors must be knowledgeable of these requirements and the expectations as identified in the standard. In addition, the requirements of AS9101 Standard have significantly changed the way audits are expected to be performed in the Aviation, Space and Defense industries.
2016-09-28 ...
  • September 28-29, 2016 (8:30 a.m. - 4:30 p.m.) - Cerritos, California
  • October 26-27, 2016 (8:30 a.m. - 4:30 p.m.) - Warrendale, Pennsylvania
  • November 24-25, 2016 (8:30 a.m. - 4:30 p.m.) - Shanghai, China
Training / Education Classroom Seminars
The certification of transport category cabin interiors requires a thorough understanding of Part 25 Transport Category aircraft cabin interior safety and crashworthiness regulations and compliance requirements. Regardless of whether it is a simple modification, a specialized completion (VIP or VVIP) or airline passenger configuration, engineers, designers, and airworthiness personnel must understand and adhere to these requirements. This two day seminar will begin with a discussion of Commercial off the Shelf (COTS) test requirements.
2016-09-27
Technical Paper
2016-01-2098
Christophe Vandaele, Didier Friot, Simon Marry, 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.
2016-09-27
Journal Article
2016-01-2112
Hilmar Apmann
As a new material FML made by aluminum foils and Glasfibre-Prepreg is a real alternative to common materials for fuselages of aircrafts. Since experiences within A380 this material has some really good advantages and becomes status as alternative to Aluminum and composite structures. Main goal for an industrial application for a higher production rates of aircrafts (like for single aisle) is the automation of production processes inside the process chain for FML-parts like skins and panels for fuselages. To reach these goals for high production rates first steps of automation inside this process chain have been developed in the last two years. Main steps is the automated lay-up of metallic foils and Glasfibre-Prepreg and also for integration of the bond film. Over this there are some more steps within positioning of i.e. stringers and doublers by automatic integration and shorter process chain to reduce process cost significantly.
2016-09-26 ...
  • September 26-27, 2016 (8:30 a.m. - 4:30 p.m.) - Hartford, Connecticut
Training / Education Classroom Seminars
ARP4754A substantially revises the industry guidance for the development of aircraft and aircraft systems while taking into account the overall aircraft operating environment and functions. This development process includes validation of requirements and verification of the design implementation for certification and product assurance. ARP4754A provides the practices for showing compliance with regulations and serves to assist companies in developing and meeting its own internal standards though application of the described guidelines.
2016-09-20
Technical Paper
2016-01-2052
Virgilio Valdivia-Guerrero, Ray Foley, Stefano Riverso, Parithi Govindaraju, Atiyah Elsheikh, Leonardo Mangeruca, Gilberto Burgio, Alberto Ferrari, Marcel Gottschall, Torsten Blochwitz, Serge Bloch, Danielle Taylor, Declan Hayes-McCoy, Andreas Himmler
This paper presents an overview of a project called “Modelling and Simulation Tools for Systems Integration on Aircraft (MISSION)”. This is a collaborative project being developed under the European Union Clean Sky 2 Program, a public-private partnership bringing together aeronautics industrial leaders and public research organizations based in Europe. The provision of integrated modelling, simulation, and optimization tools to effectively support all stages of aircraft design remains a critical challenge in the aerospace industry. In particular the high level of system integration that is characteristic of new aircraft designs is dramatically increasing the complexity of both design and verification. Simultaneously, the multiphysics interactions between structural, electrical, thermal, and hydraulic components have become more significant as the systems become increasingly interconnected.
2016-09-20
Technical Paper
2016-01-1989
Qiong Wang, Rolando Burgos, Xuning Zhang, Dushan Boroyevich, Adam White, Mustansir Kheraluwala
Abstract In modern aircraft power systems, active power converters are promising replacements for transformer rectifier units concerning efficiency and weight. To assess the benefits of active power converters, converter design and optimization should be carefully done under the operation requirements of aircraft applications: electromagnetic interference (EMI) standards, power quality standards, etc. Moreover, certain applications may have strict limits on other converter specifications: weight, size, converter loss, etc. This paper presents the methodology for performance optimization of different active power converters (active front-ends, isolated DC/DC converters and three-phase isolated converters) for aircraft applications. Key methods for power converter component (e.g. inductors, semiconductor devices, etc.) performance optimization and loss calculation are introduced along with the converter optimization procedure.
2016-09-20
Technical Paper
2016-01-2004
M. Parvez Alam, Dinesh Manoharan
In this paper we discuss about the design and development of an “Autonomous Amphibious Unmanned Aerial Vehicle (AAUAV)” that can fly autonomously to the polluted water areas where human accessibility is formidable to test the water quality. The AAUAV system is an integrated multi-copter with tilt rotor capability to facilitate easy landing, navigation and maneuver on water. A 3D CAD model has been designed and analyzed. A specific propulsion system has been devised and lab tested. A proof of concept model has been made and tested in the field with its instruments to ascertain its technical/ operational feasibility. This system can also be tailored to collect and store the water samples from the polluted sites for further comprehensive research at the laboratory. AAUAV system is the novel solution to the polluted environment through a complete integrated system. This will be an effective alternative for the conventional water sampling techniques.
2016-09-20
Technical Paper
2016-01-2008
Alexander Grima, Colin Theodore, Oliver Garrow, Ben Lawrence, Linnea Persson
Abstract The Elytron 2S is a prototype aircraft concept to allow VTOL capabilities together with fixed wing aircraft performance. It has a box wing design with a centrally mounted tilt-wing supporting two rotors. This paper explores the aerodynamic characteristics of the aircraft using computational fluid dynamics in hover and low speed forward flight, as well as analyzing the unique control system in place for hover. The results are then used to build an input set for NASA Design and Analysis if Rotorcraft software allowing trim and flight stability and control estimations to be made with SIMPLI-FLYD.
2016-09-20
Technical Paper
2016-01-2009
Natasha Barbely, Narayanan Komerath, Nandeesh Hiremath
Abstract Coaxial rotors are finding use in advanced rotorcraft concepts. Combined with lift offset rotor technology, they offer a solution to the problems of dynamic stall and reverse flow that often limit single rotor forward flight speeds. In addition, coaxial rotorcraft systems do not need a tail rotor, a major boon during operation in confined areas. However, the operation of two counter-rotating rotors in close proximity generates many possible aerodynamic interactions between rotor blades, blades and vortices, and between vortices. With two rotors, the parameter design space is very large, and requires efficient computations as well as basic experiments to explore aerodynamics of a coaxial rotor and the effects on performance, loads, and acoustics.
2016-09-20
Technical Paper
2016-01-2015
Rory Telford, Catherine Jones, Patrick Norman, Graeme Burt
Abstract Mass and efficiency are key performance indicators for the development and design of future electric power systems (EPS) for more-electric aircraft (MEA). However, to enable consideration of high-level EPS architecture design trades, there is a requirement for modelling and simulation based analysis to support this activity. The predominant focus to date has been towards the more detailed aspects of analysis, however there is also a significant requirement to be able to perform rapid high-level trades of candidate architectures and technologies. Such a capability facilitates a better appreciation of the conflicting desires to maximize availability and efficiency in candidate MEA architectures, whilst minimizing the overall system mass. It also provides a highly valuable and quantitative assessment of the systemic impact of new enabling technologies being considered for MEA applications.
2016-09-20
Technical Paper
2016-01-2019
Richard P. Johnston
Abstract An advanced composite Blended Wing Body (BWB) air frame previously used as a study aircraft to transport a 75-ton military cargo halfway around the world and back unrefueled has been modified and evaluated as a 150-ton heavy lifter. The modifications include enlarging the forward trim canard, reducing fuel load by 151,850 lbs, increasing the high-mach NASA-type counter-rotating propellers from 12 feet to 13 feet diameter, extending the propeller support pylons' height by 6 inches and modifying cruise flight and prop control strategies. Due to structural and propulsion system changes, the air frame Operational Empty Weight (OEW) was increased by 1,850 lbs. but the maximum Take Off Gross Weight (TOGW) was held to 800,000 lbs. Brief descriptions of the major propulsion system components are provided. In addition, a comparison of three different counter-rotating propeller systems is presented. The first is a Standard configuration.
2016-09-20
Technical Paper
2016-01-2012
Frank Feng, Debabrata Pal
Abstract There are many identical large solid-state switching Multi-Purpose Motor Controllers on board of one of the More Electric Aircrafts (MEA). The controllers drive over twice as many different machines with wide torque and speed ranges. The common motor controllers are installed in a central location. The machines are located at diverse and distant positions. Power is delivered and routed from the controllers to machines via a large network comprising of unshielded feeders and multiplexing units. The controllers are required to produce sine wave voltage output to machines, and draw clean power from the source to meet Power Quality (PQ) and Electromagnetic Interference (EMI) requirements. There are significant aircraft level weight savings with that concept. However, designing such a clean motor controller was a major power density challenge beyond switches, accounting for high torque main propulsion engine start and high speed Cabin Air Compressors.
2016-09-20
Technical Paper
2016-01-2010
Nandeesh Hiremath, Dhwanil Shukla, Narayanan Komerath
Abstract The design of advanced rotorcraft requires knowledge of the flowfield and loads on the rotor blade at extreme advance ratios (ratios of the forward flight speed to rotor tip speed). In this domain, strong vortices form below the rotor, and their evolution has a sharp influence on the aero-dynamics loads experienced by the rotor, particularly the loads experienced at pitch links. To understand the load distribution, the surface pressure distribution must be captured. This has posed a severe problem in wind tunnel experiments. In our experiments, a 2-bladed teetering rotor with collective and cyclic pitch controls is used in a low speed subsonic wind tunnel in reverse flow. Stereoscopic particle image velocimetry is used to measure the three component spatial velocity field. Measurement accuracy is now adequate for velocity data, and can be converted to pressure both at and away from the blade surface.
2016-09-20
Technical Paper
2016-01-2020
Constanza Ahumada Sanhueza, Andrea Bristot, Shubham Kumar, Nicolas Schneider, Seamus Garvey, Herve Morvan
Abstract This paper proposes an integrated system’s approach towards design of aero-engine subsystems - seals, bearing chamber, generator and power system. In a conventional design approach, the design of the overall system is typically broken-down into subsystems. Therefore, the focus is not on the mutual interaction between different components or subsystems, resulting in a lack of characterization of the overall system performance at the design phase. A systems design approach adopts a much broader outlook, focusing on the overall optimization of the system performance. This paper is divided into two parts. The first part presents an integrated approach for modelling the electrical, mechanical and hydraulic subsystems of aero engines, in order to analyze the fluid dynamics interactions and reduce the transversal shaft vibrations. For this, an in-line starter/generator and an air-riding seal are studied.
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