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Viewing 1 to 30 of 2454
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
2014-09-23
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
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
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
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.
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.
WIP Standard
2014-07-21
This SAE Aerospace Information Report (AIR) provides a tabular listing of materials, procurement specifications, and mechanical properties for bolts and screws developed for use on aerospace propulsion systems designed using the U.S. customary system or the SI system.

The list is intended to give a brief overview of the various kinds of SAE aerospace procurement specifications available when developing bolt and screw part standards.

WIP Standard
2014-07-21
No scope available.
Viewing 1 to 30 of 2454

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