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Plenary Speakers Chart New Path for Power technologies at APEC 2024

IEEE POWER ELECTRONICS MAGAZINE 2024年第2期11卷 57-63页

作者： Bindra, Ashok Clarkson Univ Clarkson Coll Technol Dept Elect & Comp Engn Potsdam NY 13699 USA Univ Bombay Phys Mumbai India

This year, the 39th global applied power electronics event, the IEEE Applied Power Electronics conference and Exposition (APEC) 2024 was held in Long Beach, CA, USA, from 25-29 February. Breaking all previous records, APEC 2024 registered over 6000 attendees from around the world, who convened in Long Beach Convention Center to discuss and showcase latest advances in power semiconductors, electronic components, modules, packaging, test and measurement equipments, modeling and simulation tools, and much more. It was well represented by both academia and industry. While the exhibit floor was filled with over 300 booths, with the exhibitors enthusiastically displaying their latest products and services that deliver solutions to existing and emerging problems. The conference was cosponsored by the IEEE Power Electronics Society (PELS), Power Sources Manufacturers Association (PSMA), and the IEEE Industry Applications Society (IAS).

关键词： Industries Semiconductor device measurement Power measurement Electronic components Packaging Power electronics Floors

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modeling and simulation of Pre-Apogee Trajectories for Low Altitude Rockets 10

Modeling and Simulation of Pre-Apogee Trajectories for Low A...

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10th International conference on Recent Advances in Air and Space technologies (RAST)

作者： Yilmaz, Ahmet Nuri Cihan, Melahat Samsun Univ Dept Aerosp Engn Samsun Turkiye

ISBN: (纸本)9798350323023

The objective of this study is develop a mathematical model of a rocket's trajectory during flight, a fundamental aspect of sounding rocket design and performance analysis. To this end, the equations of motion of the rocket are integrated using the fourth-order Runge-Kutta method to simulate a set of rocket parameters. In this context, the variation of altitude, velocity, acceleration, and pitch angle values of the rocket with time during flight are investigated. The accuracy of the numerical results assessed by comparing them to real flight data and open source software. The research highlights the significance of mathematical modeling and simulation in design and optimization of rockets.

关键词： Rocket Trajectory Sounding Rocket 6DoF Flight simulation

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modeling and simulation of a Parallel Hybrid-Electric Propulsion System - Electrified Powertrain Flight Demonstration (EPFD) Program

Modeling and Simulation of a Parallel Hybrid-Electric Propul...

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IEEE/aiaa Transportation Electrification conference / Electric Aircraft technologies Symposium (ITEC+EATS)

作者： Milios, Konstantinos Hall, Christopher Burrell, Andrew Brooks, Joshua Kenny, James Gladin, Jonathan Mavris, Dimitri Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA

ISBN: (纸本)9781665405607

Electrified aircraft propulsion concepts have been proposed to meet aggressive future performance and environmental goals for the next generation of aircraft. However, electrified aircraft present a unique modeling and simulation challenge as they introduce multiple energy sources to the propulsion system, providing various means to meet thrust requirements, compared to conventional gas turbine propulsion architectures where only fuel is available. Additionally, the introduction of an electric powertrain to the existing system enables multiple electrified flight modes to exist (i.e. eTaxi, climb boost, takeoff boost, etc.), further increasing the complexity of the modeling environment. As part of the Electrified Powertrain Flight Demonstration program, this paper presents a modeling and simulation framework for a parallel hybrid-electric propulsion concept using the Environmental Design Space simulation tool. Electrical components are modeled in NPSS, and an overall sizing methodology is introduced. Finally, various operational modes of the electric powertrain are modeled and tested and their impact on key performance parameters is evaluated.

关键词： Analytical models Green design Atmospheric modeling Mechanical power transmission Power systems Fuels Aircraft propulsion

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1D simulation of a Single Engined VLA Class Aircraft's Fuel System 10

1D Simulation of a Single Engined VLA Class Aircraft's Fuel ...

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10th International conference on Recent Advances in Air and Space technologies (RAST)

作者： Senel, Enes Burak Boncu, Emre Suat, Yunus Konukseven, Erhan Ilhan Middle East Tech Univ Dept Mech Engn Ankara Turkiye TRMotor Power Syst Ankara Turkiye Turkish Aerosp Ind Ankara Turkiye

ISBN: (纸本)9798350323023

Aircraft fuel systems are more complex compared to the fuel systems used in other vehicles due to the high safety and quality standards which must be satisfied. Since aircraft have additional degrees of freedom during flight, disturbances and potential risks are more diverse, making system failures harder to foresee. modeling and simulating the fuel system numerically allows for a convenient way to examine the system's performance beforehand. AMESim 2021.2 is used in the Current study to focus on the modeling and simulation of the fuel system of a Very Light Aircraft (VLA) having three tanks while also demonstrating the system architecture and the system's behavior against steady flight conditions and refueling operations. Fuel pressures, flow rates, gas pressures, and shifts in the center of gravity in the fuel system are monitored and plotted while also evaluating the performance of the fuel gauging system.

关键词： aircraft fuel system numerical modeling digital twinning AMESim

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Detailed modeling and Investigation of Impact of Transient Loading on Electrical Power System of Military Aircraft F-35

Detailed Modeling and Investigation of Impact of Transient L...

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IEEE/aiaa Transportation Electrification conference / Electric Aircraft technologies Symposium (ITEC+EATS)

作者： Khan, Irfan A. Rahman, Syed Texas A&M Univ Elect & Comp Engn Dept College Stn TX 77843 USA Texas A&M Univ Clean & Resilient Energy Syst CARES Lab Galveston TX 77554 USA

ISBN: (纸本)9781665405607

Military aircraft have always been the flag-bearers of innovative technologies to enhance performance capabilities, reduce weight, improve reliability, and advance navigation/control automation. Military aircraft such as the F-35 is designed to achieve aerial surveillance, stealth operation, and dogfighting capabilities. To achieve an optimal design, an innovative integrated subsystem design approach is adopted in F-35. This concept has resulted in a set of innovative but complex subsystems being developed and employed in military aircraft F-35. This paper focuses on exploring and mathematical modeling of the electrical power system (EPS) of F-35 powering different load types, including critical avionic loads, high-power actuators, and environmental control system loads. A flight profile showing different modes of operation is used to highlight the intermittency and power requirement in various modes. Based on this, a detailed mathematical model is simulated in MATLAB/SIMULINK (R). Based on the simulation results, asymmetrical load distribution and intermittency of the electro-hydrostatic actuator system (EHAS) load resulted in a power imbalance of 5% and 15.8% of line rating, respectively, is highlighted. To address 747146 this concern, a modified EPS is proposed, with a triple-active bridge converter, capable of exchanging controlled bidirectional power between the two HVDC buses thereby improving dynamic balancing and operational efficiency with no extra cost and additional weight.

关键词： Actuators HVDC transmission Atmospheric modeling simulation Power system dynamics Loading Military aircraft

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Computation Fluids Dynamics simulation of Aero-Thermal Environment for Apollo Era Flight Test, FIRE-II using Two Temperature Model 25

Computation Fluids Dynamics Simulation of Aero-Thermal Envir...

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25th aiaa International Space Planes and Hypersonic Systems and technologies conference

作者： Kumar, Vivek Verma, Ishan Jadeja, Harshrajsinh Mahapatra, Debabrata Injeti, Phaninder Shrivasatava, Sourabh Patwardhan, Saurabh Singh, Lalan Nakod, Pravin Ansys Software Pvt Ltd Hinjewadi Rajiv Gandhi Infotech Pk Pune 411057 Maharashtra India Ansys Software Pvt Ltd Prestige Tech Pk2nd FloorMercury Block 2B Varthur Hobli 560103 Bengaluru India

ISBN: (数字)9781624107108

ISBN: (纸本)9781624107108

Hypersonic vehicles travel faster than five times the speed of sound and enable faster access to space, faster means of commercial air travel, and rapid military response for extended range. As the speed of hypersonic vehicles increases, the non-equilibrium thermal and chemical effects become prominent. Performing tests under such conditions is expensive and time-consuming. Therefore, computational fluid dynamics simulations are popular for understanding aspects like shock stand-off distance, heat transfer, peak temperature, ablation, and so on at hypersonic flows. Project FIRE-II ballistic reentry to Earth at a nominal velocity of around 11.35 km/s is one of the best sources of aerothermal heating data for designing sample return capsules. The data from this flight experiment encompasses both the thermochemical non-equilibrium and equilibrium regimes and includes radiative and total heating measurements on the forebody and afterbody. In the present work, five operating conditions of FIRE-II at velocities of 11.36 km/s,11.31 km/s, 11.25 km/s, 11.14 km/s, and 10.97 km/s at corresponding altitudes of 76.42 km, 71.04 km, 67.05 km, 63.11 km, and 59.26 km are simulated considering a two-temperature model for thermal non-equilibrium phenomena and Gupta's 11 species, 20 reaction model for air dissociation modeling. The simulation results for all five case studies are compared with the available data from the literature [1]. The comparison shows good agreement of the present results with the available data highlighting the importance of such numerical methods in hypersonic flow studies.

关键词： Hypersonic flows FIRE-II Thermal Non-equilibrium Chemical Non-equilibrium Shock Standoff

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Subgrid-scale stress model for large-eddy simulation of turbulence using an artificial neural network

Subgrid-scale stress model for large-eddy simulation of turb...

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2024 International conference on Algorithms, High Performance Computing, and Artificial Intelligence, AHPCAI 2024

作者： Yang, Lei Li, Dong Zhang, Kai Department of Mechanics School of Aerospace Engineering Beijing Institute of Technology Beijing100081 China Tangshan Research Institute Beijing Institute of Technology Tangshan063099 China

ISBN: (纸本)9781510685840

Subgrid-scale (SGS) stress modeling based on filtered variables is one of the crucial scientific challenges in large-eddy simulation. With the rapid development of machine learning technologies in recent years, data-driven turbulence modeling methods have gained its popularity. In this study, an SGS stress model based on artificial neural network (ANN), with strain-rate tensor and modified Leonard tensor as inputs, is developed for incompressible isotropic homogeneous turbulence. The proposed ANN model demonstrates a substantial enhancement in the prediction of the SGS stress. Also, the ANN model could provide better predictions of turbulence statistics, as compared to the traditional models. It is suggested that the ANN methods exhibit obvious advantages and considerable potentials for the development of turbulence models with high accuracy. © 2024 SPIE.

关键词： Neural network models

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modeling and simulation of a Parallel Hybrid Electric Regional Aircraft for the Electrified Powertrain Flight Demonstration (EPFD) Program

Modeling and Simulation of a Parallel Hybrid Electric Region...

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IEEE/aiaa Transportation Electrification conference and Expo / Electric Aircraft technologies Symposium (ITEC+EATS)

作者： Cinar, Gokcin Cai, Yu Denney, Russell K. Mavris, Dimitri N. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA

ISBN: (纸本)9781665405607

This paper presents a parametric modeling and integrated sizing approach for a charge-depleting parallel hybrid electric aircraft. The hybrid powertrain model is integrated within a regional aircraft with an entry-into-service of 2030-2035. In addition to the physical architecture, different operational modes enabled by the hybridization of the propulsion system are modeled parametrically. The modes of operation presented in this paper are peak power shaving, climb power electric boost, in-flight battery recharging, and electric taxi. The aircraft and powertrain sizing is performed within the multidisciplinary analysis and optimization environment, E-PASS. The consideration of the physical system and its operation together provides a holistic approach where the propulsion system and the airframe are designed under an optimized power and energy management strategy. The parametric nature of the work enables the design space exploration for electrification and lays the groundwork for future technology projection and uncertainty quantification studies. The developed capability is generic and can be applied to other aircraft classes. The work is done as part of the Electrified Powertrain Flight Demonstration program.

关键词： Analytical models Atmospheric modeling Mechanical power transmission Mathematical models Space exploration Batteries Aircraft manufacture

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modeling of RMS Current in CSI Filter Capacitor and Minimum Conduction Loss Operation of CSI-Fed PMSM Drives for Traction Applications

Modeling of RMS Current in CSI Filter Capacitor and Minimum ...

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IEEE/aiaa Transportation Electrification conference / Electric Aircraft technologies Symposium (ITEC+EATS)

作者： Lee, Sangwhee Feng, Wenda Chen, Feida Chen, Ken Jahns, Thomas M. Sarlioglu, Bulent Univ Wisconsin Madison Wisconsin Elect Machines & Power Elect Consortium Madison WI 53706 USA

ISBN: (纸本)9781665405607

This paper presents a new minimum conduction loss (MCL) torque control algorithm for current source inverter(CSI-) fed permanent-magnet synchronous machine drives that improves the overall machine drive efficiency by minimizing the combined conduction losses in the inverter and machine at each operating point. First, analytical models of conduction losses in CSI-fed motor drives are presented, and a closed-form expression for optimal d-axis stator current to achieve MCL operation is derived. An expression for the rms current in both wye- and delta-connected CSI output capacitors is derived. A detailed simulation model that emulates the operation of a 100 kW SiC CSI-fed integrated machine drive (IMD) has been developed based on experimental results and finite element analysis. This simulation model is used to evaluate the proposed MCL control algorithm applied to a CSI-fed IMD system for a battery-electric vehicle traction drive, and the predicted total drive system loss with MCL control is compared to predicted losses with maximum-torqueper-ampere (MTPA) and minimum dc-link current (MDCC) control. Results show that MCL control can achieve loss reductions compared to the other two control algorithms over a wide range of operating conditions, with significant loss reductions >20% in the medium-speed regime.

关键词： Analytical models Closed-form solutions Silicon carbide simulation Capacitors Torque control Predictive models

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Performance Improvement of Surface Permanent Magnet Vernier Motor by Adjusting Current Control Angle Considering Magnetic Saturation

Performance Improvement of Surface Permanent Magnet Vernier ...

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IEEE/aiaa Transportation Electrification conference / Electric Aircraft technologies Symposium (ITEC+EATS)

作者： Zhu, Jingwei Chen, Feida Chen, Jiahao Zuo, Yuefei Chen, Hao Lee, Christopher H. T. Nanyang Technol Univ Sch Elect & Elect Engn Singapore 639798 Singapore Univ Wisconsin Dept Elect & Comp Engn Madison WI 53706 USA Chalmers Univ Technol Dept Elect Engn S-41296 Gothenburg Sweden

ISBN: (纸本)9781665405607

Surface permanent magnet vernier motors (SPMVMs) possess the characteristics of high torque density and simple structure, making them a compelling technology for gearless applications, such as in-wheel motors and robots. This paper investigates the impact of current control angle on the magnetic saturation at the rated operating point for SPMVMs. The magnetic saturation analysis is conducted on motors with various magnet thickness to identify the effect of magnetic saturation level on the performance metrics. Focus is placed on selecting the optimal current angle to achieve both high torque density and power factor at the rated point. It shows that SPMVMs with small magnet thickness exhibit higher torque density and power factor simultaneously than those with thick magnet, if appropriate current control angle is set at the rated operating point. Moreover, the selection of the current angle has no significant impact on the flux weakening capability. This finding can be used to define the optimal current control angle of SPMVMs at the rated operating point for improved performance and reduced power burden on the inverter. The simulation results show that a high torque density of 23 Nm/L and a high power factor of 0.92 is achieved. Part of the experiment has been conducted for SPMVMs.

关键词： Current control Magnetic flux Reactive power Torque simulation Permanent magnet motors Permanent magnets

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