The specifications and tactical data of an aircraft depend considerably on its power loading. Recently, the determining trend has been to a wider electrification of the aircraft. The parameters, characteristics, and structure of the power-supply system are determined by the level of development of electric engineering and electronics. The profound improvement of the IGBT and MOSFET modules and the sharply increased output and resources of microprocessors has made it possible to introduce new-generation power-supply systems into the vehicles using the latest achievements of smart power electronics. This paper discusses the results of the development and testing of an auxiliary 30 kVA variable speed constant frequency (VSCF) electric power generation system (EPGS) in Russia for an aircraft. The system contains a permanent magnet synchronous generator, a controlled rectifier, a voltage-inverter-based frequency converter, filters, and a microprocessor control system. The EPGS generates the 400 Hz, 115 V, three-phase ac power in the standard operation and a 28.5 V dc current due to the autorotation mode in the failure of the aircraft engine. In order to improve the quality of the output voltage, to tackle the problem of electromagnetic compatibility, and to raise the operation reliability, a voltage inverter is implemented in the form of four channels operating in parallel. In the voltage-inverter control, a shift of the PWM (Pulse-Width Modulator) reference signal is applied according to the number of parallel channels. To control the voltage inverters, a modified vector control algorithm with compensation for the exciting actions is implemented. The vector algorithm modification stems from the necessity of introducing the zero sequence as a controlled coordinate in the voltage inverter output voltage and currents. The block diagram of the voltage inverter control algorithm shows the voltage signal setter, the voltage and current regulators, the dc link voltage compensator, the coordinate converters, the modulating signal limiter, and the PWM. The current and voltage control circuits are connected according to the master-slave control principle. The internal circuit provides control of the inverter output current, and the external circuit stabilizes the load voltage. The control algorithm implemented allows for the in-phase operation of the EPGS with an airfield power source or with another channel of the electricity supply system. The electric power generation system operates in a generation mode within a synchronous generator shaft speed range 6000 rpm to 10400 rpm. The electric power generation system yields a shortcircuit current equal to no less than three rated magnitudes in a minimum of 7 s. The system can directly start an aircraft induction motor of the power up to 30 % of the EPGS power.


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    Titel :

    Variable speed constant frequency power generation system based on a synchronous generator excited from permanent magnets and voltage inverters


    Weitere Titelangaben:

    Stromversorgungssystem mit konstanter Frequenz für ein Flugzeug auf der Grundlage eines permanenterregten Synchrongenerators und eines Spannungsumrichters


    Beteiligte:
    Kharitonov, S.A. (Autor:in) / Korobkov, D.V. (Autor:in) / Maslov, M.A. (Autor:in) / Borodin, N.I. (Autor:in) / Levin, A.V. (Autor:in) / Yukhin, M.M. (Autor:in) / Livshits, E.Y. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2008


    Format / Umfang :

    6 Seiten, 14 Bilder, 5 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch







    SYNCHRONOUS GENERATOR APPARATUS WITH EXCITATION FROM PERMANENT MAGNETS

    AVANESOV LEONID STEPANOVICH / ALEKSEEVA NINA MIKHAJLOVNA / BAVYKIN VALENTIN VIKTOROVICH et al. | Europäisches Patentamt | 2021

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