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Training / Education
2014-10-27
The simultaneous demands for reliability and minimum weight for aircraft and propulsion systems offer some of the most challenging technical problems that structural and safety engineers can encounter. Although much information is available on fracture mechanics and aircraft damage tolerance, this course specifically relates to damage tolerance for gas turbine engines. The need to consider damage tolerance more broadly in new engine designs has just recently been written into FAR 33.70 and new EASA guidelines. With an increasing need for education, both in the U.S. and internationally, this seminar relates directly to the growing interest and priority the AIA, FAA, and engine OEM’s have placed on turbine engine damage tolerance. This two-day seminar offers a broad survey of damage tolerance, one of the many principles behind one of the safest industries in the world. Although the basics of fracture mechanics will be covered, this is not an advanced fracture mechanics course. Attendees will be presented information on how experts in the propulsion community use the principles of prevent, quantify, and improve to keep air travel safe.
Event
2014-10-05
SAE Chassis Brake Standards Committee plays the central role in the development of essential consensus-based standards development to meet the needs of manufacture, supplies, buyer, engineer, consumer and others. Each committee develops a full suite of standards that are related to quality, durability, environmental effect and safety. Your involvement with SAE Standards Committees provides industry, companies and individuals with extensive opportunities to participate, and influence the standard.
Event
2014-09-25
This session shall include papers related to military manned aircraft and air vehicle electrical power management and distribution (relays, circuit breakers, SSPCs), control & protection, arc fault protection, power conversion (AC/DC, DC/DC/ AC/AC) and power conditioning. AC (fixed & variable frequency) and DC (28 VDC and 270 VDC) systems are planned for discussion.
Event
2014-09-25
This session shall include papers related to military manned aircraft and air vehicle electrical power management and distribution (relays, circuit breakers, SSPCs), control & protection, arc fault protection, power conversion (AC/DC, DC/DC/ AC/AC) and power conditioning. AC (fixed & variable frequency) and DC (28 VDC and 270 VDC) systems are planned for discussion.
Event
2014-09-24
This session focuses on the use of the engines as novel flight effectors, including integrated control of flight path and engines, strategies and architectures for improved flight safety and fuel efficiency, engine and flight control interfaces, novel flight and engine control requirements and restrictions due to integration, flight and propulsion control law design, and model based control law design and validation.
Event
2014-09-24
This session focuses on the use of the engines as novel flight effectors, including integrated control of flight path and engines, strategies and architectures for improved flight safety and fuel efficiency, engine and flight control interfaces, novel flight and engine control requirements and restrictions due to integration, flight and propulsion control law design, and model based control law design and validation.
Event
2014-09-24
This session is dedicated to topics dealing with the integration between the Powerplant system & the airframe. This session covers the physical & functional interfaces between the different components, and their aerodynamic, thermal, structural, loads & Dynamic integration. This session covers: the Engine, Nacelle, Pylon & associated local sub systems (Fuel, Bleed, Oil, Fire, Etc).
Event
2014-09-23
Event
2014-09-23
Technical Paper
2014-09-16
Marco Amrhein, Brian Raczkowski, Jason Wells, Eric Walters, Sean Field, Jason Gousy
Analyzing and maintaining power quality in electrical power systems of electrical equipment, weapons systems, and installations is essential to ensure that power generation, distribution, and loads function as expected within their designated operating regime. Standards such as MIL-STD-704, MIL-STD-1399, MIL-E-7894, MIL-STD-1332, etc., and associated documents provide the framework for power quality metrics that need to be satisfied under varying operating conditions. These can include steady-state time-domain metrics, limitations on spectral content (frequency-domain), and transient limitations during normal and abnormal operation. Frequently, test methods for the metrics exists that allow system integrators and subsystem providers to determine power quality performance within a controlled environment as part of acceptance testing. However, analyzing and enforcing these power quality metrics within a fully integrated electrical power system based solely on measurements of relevant signals (commonly voltages and currents measured at certain points within the system) is a different challenge that requires a separate framework containing rules for data acquisition, metric calculations, and applicability of metrics in certain operating conditions/modes.
Technical Paper
2014-09-16
Ralf Cremer, Alfred Engler
The implementation of power electronics in aircraft is progressively going up on the last aircraft developments. For instance, the power-by wire technique leads to significant weight and performance improvements on the A380 airplane implementing two independent electro-hydrostatic actuators into the standard hydraulic flight controls. These actuators are driven by power electronics systems that needed to be adapted to the aerospace constraints. Other systems have the potential to become more electrical or all electrical like the environmental climate system, the wing ice protection system, the landing gear or the taxiing for instance. The increase of power electronics system will also strongly influence the architecture of the aircrafts e.g. high voltage DC networks, electrical distribution power centers, and centralized and modular power converters issues. The range of applications is wide and the flexibility and the intelligence of power electronics system will surely optimize the future airplanes in term of consumption and performance.
Technical Paper
2014-09-16
Yves C.J. Lemmens, Tuur Benoit, Rob De Roo, Jon Verbeke
Vives College University and Kulab (KU Leuven University campus Ostend) in Belgium are undertaking an aeronautical research program about the development of a new Unmanned Aerial Vehicle (UAV). The UAV is aimed at performing scientific missions along the Belgian coast line above the North Sea. The main performance requirement of the UAV, named Litus, is a range of 160km with a payload up to 5kg. A canard configuration with swept wings and a vertical tail at each wing tip was chosen. A propulsion system of two electrical brushless DC motors had been selected in order to minimize the environmental impact during operations by avoiding gas emissions and reducing noise emissions. Test flights of the Litus are planned in the summer of 2014. The Litus has a wing span of 6m and has a total mass of 65kg. Since the UAV is completely electrically powered, the analysis of the energy management of the integrated electrical system is critical to the development of the UAV. LMS, A Siemens Business, is involved in the project to support the development of a multi-physics simulation model for electro-thermal analysis of the aircraft [1].
Technical Paper
2014-09-16
Rudolf Neydorf, Youriy Sigida
Identification of propeller traction power specifications in aircraft mathematical description problems Under the mathematical simulation of the aircraft dynamic motion, an identification problem for a number of constants and functions which cannot be analytically calculated appears. Dependences of aerodynamic gap coefficients of the aircraft body and the airflow, as well as the traction power specifications of the active propulsors used in flight by the aircraft, are related to such functions. Nowadays, propellers only are used in the airships and other aerial vessels with the aerostatic keeping in-flight principle. In the automatic flight control systems, they act as actuation devices. When constructing a mathematical aircraft model, the thrust developed by the propulsor is often taken for an input control. However, there are a great many phases of transforming forces, moments, and kinds of energy, between the real input control (customarily, it is introducing fuel or power supply to the servomotor input) and the rotor thrust load.
Technical Paper
2014-09-16
Matthieu Hutchison, Grégoire Lenoble, Umberto Badiali, Yannick Sommerer, Olivier Verseux, Eric Desmet
Fuel pressure surge is an essential topic for modern aircrafts and a main driver for airframe fuel system sizing. This phenomenon can occur both during normal and abnormal operations, notably resulting from a sudden change of fluid velocity due to the opening or closure of an engine valve. During aircraft development phase, Airbus specifies to engine manufacturers a pressure limit at the interface between the engine and airframe. The verification activities performed by engine manufacturers shall then ensure that the maximum pressure surge will not exceed these requirements. The purpose of this paper is to present the methodology developed by Airbus with the support of LMS Engineering (a Siemens PLM Software division) for the assessment of accurate fuel pressure surge at early program stages in the complete aircraft and engine environment. This methodology will help to avoid late airframe fuel system redesign and secure entry-into-service by driving the engine manufacturer verification & validation process.
Technical Paper
2014-09-16
Michael Baldwin
This paper will illustrate how the increasing electrical demands to power military and aerospace applications can continue to successfully be met by high performance electromechanical relays. To meet these higher demands engineering compatibility must be properly understood between the intended application demands and relay switching performance parameters. With high performance electromechanical relays continuing to play a critical part in military and aerospace applications it is more important than ever that engineers capture all of the military and aerospace electrical power switching requirements. A critical area within powering military and aerospace systems is relay life when capacitive load switching. Capacitive loads generate high current levels that are transient in duration and often adversely affect the relay lifespan at the component level and reliability of military or aerospace application at the systems level. In this paper practical examples of inrush current reduction of capacitive transient high current loads and corresponding increase of relay contact life rating will be reviewed and the explored in detail.
Technical Paper
2014-09-16
Darcy Allison, Edward Alyanak
The design challenges associated with advanced supersonic aircraft are best handled with a multidisciplinary approach. These aircraft are highly coupled in that small changes to one subsystem can have far-reaching effects on others. For the class of aircraft called the efficient supersonic air vehicle (ESAV), particular attention must be paid to the propulsion system design as a whole including installation effects in the airframe design. The propulsion system assumed for the ESAV is a three-stream variable cycle engine. A computational model has been built with the Numerical Propulsion System Simulation (NPSS) software to analyze this engine. Along with the variable cycle NPSS model, a three-ramp external compression inlet model meant for conceptual design has been developed. This inlet model will be used to capture installation effects so that they are accounted for during the aircraft conceptual design. The NPSS and inlet models are parameterized so that they can be used in a multidisciplinary design optimization (MDO) process.
Technical Paper
2014-09-16
Arthur V. Radun
There is a continuing need to simulate power electronic circuits that include magnetic components. It is necessary to determine the interaction of the magnetic component with the rest of the power electronic system so that a dynamic circuit model of the magnetic components including material saturation and iron losses is required. The magnetic component model must be valid when the magnetic component’s excitation is not sinusoidal. A dynamic magnetic circuit model is derived from Maxwell’s equations along with useful theorems for building circuit models from the structure of the magnetic device. The developed circuit models are general including magnetic saturation and iron losses Dynamic magnetic circuit models are developed for selected magnetic components to illustrate the application of the modeling technique. Simulation results for a DC/DC converter employing a conventional gapped inductor and a gapped coupled inductor are presented. Extensions to more complex components are also shown.
Technical Paper
2014-09-16
Arthur V. Radun
An important aspect of the Integrated Vehicle Energy Technology (INVENT) program has been the development of an integrated aircraft system model. The Robust Electric Power System (REPS) modeling poses particular challenges because of the highly dynamic and short time constant line replaceable units employed. In addition to the technical challenges is the challenge of protecting proprietary information that could be lost in the exchange of models. This paper describes simplified non-physics based line replaceable unit models for units anticipated to be part of a 6th generation aircraft power system. A typical 6th generation power system model is constructed as an example using the unit models. Selected model verification and validation results will be presented.
Viewing 1 to 30 of 3479

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