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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.
2016-11-08
Technical Paper
2016-32-0078
Mark R. Mataczynski, Paul Litke, Benjamin Naguy, Jacob Baranski
Aircraft engine performance is degraded with increasing altitude according to the resultant reduction in air pressure, temperature, and density. One way to mitigate this problem is through turbo-normalization of the air being supplied to the engine. Supercharger and turbocharger components suffer from a well-recognized loss in efficiency as they are scaled down in order to match the reduced mass flow demands of small-scale Internal Combustion Engines. This is due in large part to problems related to machining tolerance limitations, such as the increase in relative operating clearances, and increased relative blade thickness. As Internal Combustion Engines decrease in size, they also suffer from efficiency losses owing primarily to thermal losses. This amplifies the importance of maximizing the efficiency of all sub-systems in order to minimize fuel consumption and enhance overall aircraft performance.
2016-11-08
Technical Paper
2016-32-0045
Joseph K. Ausserer, Marc D. Polanka, Jacob Baranski, Paul Litke
Small remotely piloted aircraft (10 25 kg) powered by internal combustion engines typically operate on motor gasoline, which has an anti-knock index (AKI) of >80. To comply with the single-battlefield-fuel initiative in DoD Directive 4140.25, interest has been increasing in converting the 1 10 kW power plants in the aforementioned size class to run on lower AKI fuels such as diesel and JP-8, which have AKIs of ~20. It has been speculated that the higher losses (short circuiting, incomplete combustion, heat transfer) that cause these engines to have lower efficiencies than their conventional-scale counterparts may also relax the fuel-AKI requirements of the engines. To investigate that idea, the fuel-AKI requirement of a 3W-55i engine was mapped and compared to that of the engine on the manufacturer-recommended 98 (octane number) ON fuel.
2016-10-26 ...
  • 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.
2016-10-03
Magazine
Achieving Performance Advantages in Unmanned Systems Unmanned Vehicle Systems (UVS) are reaching new levels of functionality and performance, and it’s not just for air vehicles either. COTS Embedded Systems and Link Budgets The days of proprietary embedded computing systems in military systems are numbered. Custom Designing Enclosures Using 3-D CAD Modeling Due to the advancement of 3-D computer-aided design software, enclosure manufacturing is not what it used to be. Technology advances industry. Fiber Optic Multi-Sensing Platforms Enabling Innovation Across Aerospace Organizations RECAT Wake Turbulence Recategorization New Concept for Improving the Performance of Electrically Small Antennas Microwave Radiometer for Advanced Nanosatellite Control Systems Secret Sharing Schemes and Advanced Encryption Standard SIPHER: Scalable Implementation of Primitives for Homomorphic Encryption Using Mathematics to Make Computing on Encrypted Data Secure and Practical
2016-09-28
WIP Standard
ARP4102/11D
This document recommends criteria for Airborne Windshear Systems, including operational objectives, characteristics and functional requirements. The recommendations of the document apply to transport aircraft, and describe the operational objectives of windshear alerting systems, situational displays, guidance systems and avoidance/detection systems.
2016-09-28
WIP Standard
ARP4102/13B
This document recommends criteria for a system designed to manage and communicate information via data link to support flight operations.
2016-09-28
WIP Standard
ARP4102/5SECT3A
This document recommends design criteria for the flight deck installation of electrically signaled flight control systems on fixed wing airplanes.
2016-09-28
WIP Standard
ARP4102/5SECT1A
This document recommends design criteria for the flight deck installation of electrically signaled engine control systems.
2016-09-27
Journal Article
2016-01-2112
Hilmar Apmann
Abstract As a new material FML, made by aluminum foils and Glasfiber-Prepreg, is a real alternative to common materials for fuselages of aircrafts like monolithic aluminum or CFRP. Since experiences within A380 this material has some really good advantages and develops to the status as alternative to aluminum and composite structures. To become FML as a real alternative to aluminum and carbon structures there are many things to improve: design, material, costs and process chain. So following one of the main goals for an industrial application for high production rates of aircrafts is the automation of production processes inside the process chain for FML-parts like skins and panels for fuselages. To reach this goal for high production rates first steps of automation inside this new process chain have been developed in the last two years. Main steps is the automated lay-up of metallic foils and Glasfiber-Prepreg.
2016-09-27
Technical Paper
2016-01-2098
Christophe Vandaele, Didier Friot, Simon Marry, Etienne Gueydon
Abstract With more than 10 000 aircrafts in their order backlog Aircraft manufacturers focus on automated assembly is of critical importance for the future of efficient production assembly. Moreover to obtain maximum benefit from automation, it is necessary to achieve not only an automated assembly cell, but also a real breakthrough in fastener 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 multifunction end effector and high performance 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 many aircraft manufacturers.
2016-09-20
Technical Paper
2016-01-1979
William D. Bertelsen
Abstract Technology to create a VTOL for general aviation that is fast, efficient, easy to fly, and affordable, has proven elusive. Bertelsen Design LLC has built a large research model to investigate the potential of the arc wing VTOL to fulfill these attributes. The aircraft that is the subject of this paper weighs approximately 145 kg (320 lbs) and features coaxial, dual-rotating propellers, diameter 1.91 m (75 inches). Power is from an MZ 202 two-cycle, two-cylinder engine. Wingspan is 1.82 m (72 inches). The arc wing differentiates this aircraft from previous deflected-slipstream prototypes, which suffered from pitch-trim issues during transition. This paper will present configuration details of the Bertelsen model, showing how it is possible to generate high lift from a short-span wing system. The Bertelsen model can hover out of ground effect using just two arc-wing elements: a main wing and a “slat”.
2016-09-20
Technical Paper
2016-01-1986
Qian Li, Balakrishnan Devarajan, Xuning Zhang, Rolando Burgos, Dushan Boroyevich, Pradeep Raj
Abstract The more electric aircraft (MEA) concept has gained popularity in recent years. As the main building blocks of advanced aircraft power systems, multi-converter power electronic systems have advantages in reliability, efficiency and weight reduction. The pulsed power load has been increasingly adopted--especially in military applications--and has demonstrated highly nonlinear characteristics. Consequently, more design effort needs to be placed on power conversion units and energy storage systems dealing with this challenging mission profile: when the load is on, a large amount of power is fed from the power supply system, and this is followed by periods of low power consumption, during which time the energy storage devices get charged.
2016-09-20
Technical Paper
2016-01-1985
Fei Gao, Serhiy Bozhko, Patrick Wheeler
Abstract The paper will deal with the problem of establishing a desirable power sharing in multi-feed electric power system for future more-electric aircraft (MEA) platforms. The MEA is one of the major trends in modern aerospace engineering aiming for reduction of the overall aircraft weight, operation cost and environmental impact. Electrical systems are employed to replace existing hydraulic, pneumatic and mechanical loads. Hence the onboard installed electrical power increases significantly and this results in challenges in the design of electrical power systems (EPS). One of the key paradigms for future MEA EPS architectures assumes high-voltage dc distribution with multiple sources, possibly of different physical nature, feeding the same bus(es). In our study we investigate control approaches to guarantee that the total electric load is shared between the sources in a desirable manner. A novel communication channel based secondary control method is proposed in this paper.
2016-09-20
Technical Paper
2016-01-1980
Syama M. Rao, Dineshkumar M
Abstract This paper studies admissible state trajectories for an unmanned aerial vehicle(UAV) by performing dynamic soaring technique in the wind gradient. An optimization problem is formulated by employing direct optimal piece wise control. A 3-DOF point mass model system dynamics of UAV is considered. The bank angle and lift co-efficient are identified as control variables. A UAV of mass 5.44kg is considered for this study. Performance measures considered are maximization of specific energy and maximization of specific energy rate extracted by the vehicle, and minimization of the control effort. The effects of linear and parabolic wind gradient on maximizing the specific energy of an autonomous dynamic soaring UAV is also studied and minimum linear gradient required is found. The loop radius of the loiter pattern is maximized for applications like surveillance and patrolling of a localized area along with energy maximization as objective function.
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