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More Electric Aircraft (MEA) is a promising aircraft, replacing air pressure system, hydraulic systems and mechanical systems by power system. Nevertheless, the increase of electrical equipment inevitably leads to more problems in aircraft safety problems, of which the arc fault has a great influence. This manuscript is aimed at series arc in because it's not easy to detect. To solve the problem of...
The current trend for future aircraft is the adoption of the More Electric Aircraft (MEA) concept. The electrical based starter-generator (S/G) system is one of the core ideas from the MEA concept. The PI based control scheme has been investigated in various papers for the permanent magnet based S/G system. Different control schemes are to be considered to improve the control performance of the S/G...
This paper investigates the dynamic stability of a droop-controlled multi-generator system in the more electric aircraft (MEA). Based on the developed state-space model of the potential dc electrical power system (EPS) architecture, the stability boundaries of EPS operation depending on parameter variations including component parameters and operating conditions are investigated. The effect of multiple...
This paper deals with the coordinated control of load sharing among multiple sources in DC microgrid with energy storage system. The DC electrical power system (EPS) with parallel sources in the more electric aircraft (MEA) are under study in this paper. Permanent magnet synchronous generators (PMSGs) are the main sources to supply power to meet the load demand on board. An adaptive droop characteristic...
This paper deals with the modeling and small-signal stability analysis of a dc-distribution electrical power system (EPS) sourced by a permanent magnet synchronous generator (PMSG). The topology employed here is one of the main candidates for future more electric aircraft (MEA). A detailed mathematical model is developed and comprehensive EPS modal analysis is performed. Eigenvalue sensitivity and...
This paper deals with the small-signal stability analysis of a dc-distribution electrical power system (EPS) sourced by permanent-magnet synchronous generator (PMSG), which is one of the main topology candidate for future more-electric aircraft (MEA). A detailed mathematical model is developed and comprehensive EPS modal analysis including eigenvalues sensitivity and participation factor performed...
Under certain conditions Electro-Mechanical Actuators are able to regenerate, rather than consume electrical power. Within the More Electric Aircraft this possibility must be carefully considered in order to ensure safe and stable operation of the electrical systems. This paper assesses various strategies for the management of regenerated power in the More Electric Aircraft. A range of options are...
The More Electric Aircraft (MEA) has been identified to be a major trend for future aircrafts. One of the key improvements introduced in MEA is its electrical power generation system. The generator system studied in this paper comprises of a permanent magnet machine and an active front-end rectifier. Rather than just using PI controllers to control the generation system, Model Predictive Control (MPC)...
This paper has details the theoretical background, development and application of a newly developed Automated Stability Assessment Tool for More Electric Aircraft Electrical Power Systems. This tool is shown to provide an easy to use and extremely flexible way for system designers to analyze Electrical Power System stability. It is shown how system parameters can be easily varied in order to investigate...
This paper presents a modeling study of an electrical power source for more electric aircrafts. It was designed with a PI (proportional-integrator) automated control for dq currents of the electrical machine, using the non-linear model of it. Using the dimensionless linear model, it was designed an optimal control structure based on a quadratic quality criterion (LQR) to validate the theoretical results...
The presence of constant power loads in novel aircraft electrical power systems may cause overall system instability if a power limit range is exceeded. This paper deals with stability analysis of the proposed aircraft power system in order to determine the power limit range and possible differences when varying system parameters such as DC bus capacitance, electrical frequency, and controller parameters...
In this paper an algorithm for non-linear magnetic analysis of surface-mounted permanent-magnet machines is presented. It is based on the equivalent magnetic circuit method and can be used as a useful design and computing tool. The duplication of an elementary cell of the machine allows building whatever typology of windings and ampere-turns distribution in a pole pair. The direct modification of...
In this paper are presented modeling and analysis of the three-phase synchronous generator in closed-loop. The field winding voltage controller is modeled initial as a classical PI controller and then is modeled as a PI fuzzy controller. The performance of the system with fuzzy logic controller is compared with the system having classical controller PI. Simulation is performed on synchronous generator...
In a power distributed system of More Electric Aircraft with many loads on the dc or ac bus, there are harmonic and reactive currents when a large load is loaded or unloaded from the bus. The bus conditioner can compensate the harmonic and reactive currents on dc and ac bus in power system. This paper presents a sample of a power distributed system of More Electric Aircraft with an ac bus conditioner...
The development of future more electric aircraft systems is a challenging process: The respective subsystems are highly integrated to achieve an optimum efficiency and performance both at aircraft and at systems level. For master this multi-disciplinary challenge, the use of powerful modeling and simulation technologies such as Modelica in all phases of the system development process is a key success...
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