Aircraft Power Systems

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Pericle Zanchetta - One of the best experts on this subject based on the ideXlab platform.

  • Power conversion for a novel AC/DC Aircraft electrical distribution system
    IET Electrical Systems in Transportation, 2014
    Co-Authors: Patrick Wheeler, Pericle Zanchetta, Jon Clare, Andrew Trentin
    Abstract:

    This study proposes a novel and compact AC/DC electrical distribution system for new generation Aircraft. In these new Aircraft Power Systems, all loads are fed by two DC bus Systems: at 28 V and at �270 V. The electrical distribution system, whose design and implementation are described in this study, has only one primary AC source (360-900 Hz at 230 V) with all the required DC voltage levels being derived from this source. This solution enables elimination of the complex mechanical coupling apparatus currently used, for fixed frequency AC Systems, to maintain the generator speed at constant level while the engines operate at variable speed. Under the proposed solution, all the conversion stages needed to generate various output voltage levels are implemented by using Power converters assembled in one unit. Each converter has a current control loop in order to regulate the output current even during output line short circuits and also to limit the inrush current to the circuit at turn-on. To prove the concept, a 5 kW prototype was designed and tested, and demonstrated to meet all the specifications within the relevant standards regarding input and output Power quality.

  • Iterative Learning Control With Variable Sampling Frequency for Current Control of Grid-Connected Converters in Aircraft Power Systems
    IEEE Transactions on Industry Applications, 2013
    Co-Authors: Pericle Zanchetta, M. Degano, Paolo Mattavelli
    Abstract:

    This paper investigates the feasibility of an iterative learning control (ILC) with variable sampling frequency for current control of Power converters in frequency-wild Power Systems. The proposed solution is explained and demonstrated for the case of a shunt active filter in new-generation Aircraft, where a variable-speed variable-frequency Power system, typically between 360 and 900 Hz, is nowadays used. Due to the high supply frequency, such application is particularly demanding for both Power and control devices, requiring control capabilities even for frequencies up to several kilohertz. Furthermore, variable supply frequency leads to variable frequency harmonics in the Aircraft grid that are challenging to track and compensate. An original and effective solution based on an ILC approach, where both the number of samples per period and the sampling frequency are changed, is studied and implemented. Experimental results confirm the validity of the proposed strategy.

  • Variable sampling frequency in iterative learning current Control for Shunt Active Filter in Aircraft Power Systems
    2011 IEEE Energy Conversion Congress and Exposition, 2011
    Co-Authors: Pericle Zanchetta, M. Degano, Paolo Mattavelli
    Abstract:

    This paper investigates the feasibility of an Iterative Leaning current Control (ILC) with variable sampling frequency to realize a 3-phase Shunt Active Filter (SAF) used for harmonic compensation in new generation Aircrafts, where a Variable Speed Variable-Frequency (VSVF) Power system, typically between 360 and 900Hz, is nowadays used. Due to the high supply frequency, such applications are particularly demanding for both Power and control devices, requiring control capabilities even for frequencies up to several kHz. Furthermore variable supply frequency leads to variable frequency harmonics in the Aircraft grid that are challenging to track and compensate. An original and effective solution based on an iterative learning control approach, where both the number of samples per period and the sampling frequency are changed, is studied and implemented. Experimental results confirm the validity of the proposed solution.

  • Improved dead beat control of a shunt active filter for Aircraft Power Systems
    2010 IEEE International Symposium on Industrial Electronics, 2010
    Co-Authors: V. Biagini, Milijana Odavic, Pericle Zanchetta, M. Degano, P. Bolognesi
    Abstract:

    This paper investigates the application of an improved dead beat digital control strategy to a 3-phase shunt active filter used for compensation of load harmonics in Aircraft Power Systems. Due to the high rated frequency (400 Hz) such applications result particularly demanding for both Power and control devices. To compensate the inherent delay of digital control Systems, a simple method for predicting the values of relevant variables is proposed and analyzed. The converter topology, its analytical modeling and its control are described. Significant results obtained by experimental tests are finally reported and commented, referring to a prototype system purposely implemented.

  • Control of a multi-level active shunt Power filter for More Electric Aircraft
    2009 13th European Conference on Power Electronics and Applications, 2009
    Co-Authors: Milijana Odavic, Mark Sumner, Pericle Zanchetta
    Abstract:

    The proposed increase of Power electronic subSystems for More Electrical Aircraft (MEA) brings severe challenges to Aircraft Power distribution. Current Aircraft Power Systems work at a fundamental frequency of 400 Hz while proposed AC MEA Power networks for next generation Aircrafts will have a fundamental frequency which varies most probably between 360 and 900 Hz. An active shunt filter (ASF) is recognized as an effective device for reducing harmonic pollution. However for the AC Aircraft Power system, harmonics for a 400 Hz fundamental (an in the future up to 900 Hz) should be controlled. A five-level active shunt filter with a high-bandwidth current controller combined together with an enhanced pulse-width modulation algorithm is proposed. The effective reference tracking of the proposed modulation combined with the employed current control approach is experimentally verified for frequencies of up to 2.8 kHz (corresponding to the 7th harmonic component when a fundamental frequency of 400 Hz is employed) with a device switching frequency of just up to 5 kHz. The proposed active filtering system therefore is suitable for more electric Aircraft applications on current Aircraft and can evolve to a viable solution also for the next generation Aircrafts with a higher and variable supply frequency.

Andrew J. Forsyth - One of the best experts on this subject based on the ideXlab platform.

  • Behavioral Modeling of a Switched Reluctance Generator for Aircraft Power Systems
    IEEE Transactions on Industrial Electronics, 2014
    Co-Authors: Virgilio Valdivia, Rebecca Todd, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, Andrew J. Forsyth
    Abstract:

    A system-level modeling technique for a switched reluctance generator (SRG) is described for aerospace applications. Unlike existing techniques, this model is very simple and only reproduces the average behavior of the input-output variables that are required for system-level analysis of the Aircraft Power distribution system. The model is parameterized from the measured generator response, avoiding the need for a detailed knowledge of the equipment structure, which may be unavailable. The modeling procedure is described in detail and validated by measurements on an SRG within an Aircraft test facility.

  • Behavioural modelling of a switched reluctance motor drive for Aircraft Power Systems
    IET Electrical Systems in Transportation, 2014
    Co-Authors: Rebecca Todd, Virgilio Valdivia, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, Andrew J. Forsyth
    Abstract:

    A system-level behavioural modelling technique is described for a switched reluctance motor drive. The model enables simple and efficient analysis or simulation of multiple drive Systems such as pumps, actuators and engine starters within a more-electric network, for example, on-board an Aircraft. The behavioural model is based on a Power balance analysis. The transfer functions in the model are parameterised from experimental tests on the drive system, resulting in a simple model that only reproduces the average behaviour of the input-output variables necessary for system-level analysis. No data from the manufacturer is required to develop the model. The technique is discussed and validated using an engine starter in an Aircraft test facility.

  • DC-bus Power quality for Aircraft Power Systems during generator fault conditions
    IET Electrical Systems in Transportation, 2011
    Co-Authors: Rebecca Todd, Andrew J. Forsyth
    Abstract:

    Higher-voltage, 540 V, Aircraft DC-bus Power quality is examined experimentally and by computer simulation during a short-circuit fault across the phase terminals of a 70 kW, five-phase, permanent magnet fault-tolerant generator. The DC-bus transients caused by the short-circuiting of the generator phases are seen to exceed the limits in MIL-STD-704F and a control algorithm is proposed for a supercapacitor-based energy storage device that mitigates the transients. The controller performance is illustrated by computer simulations for a range of bus switching scenarios.

Rebecca Todd - One of the best experts on this subject based on the ideXlab platform.

  • Behavioral Modeling of a Switched Reluctance Generator for Aircraft Power Systems
    IEEE Transactions on Industrial Electronics, 2014
    Co-Authors: Virgilio Valdivia, Rebecca Todd, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, Andrew J. Forsyth
    Abstract:

    A system-level modeling technique for a switched reluctance generator (SRG) is described for aerospace applications. Unlike existing techniques, this model is very simple and only reproduces the average behavior of the input-output variables that are required for system-level analysis of the Aircraft Power distribution system. The model is parameterized from the measured generator response, avoiding the need for a detailed knowledge of the equipment structure, which may be unavailable. The modeling procedure is described in detail and validated by measurements on an SRG within an Aircraft test facility.

  • Behavioural modelling of a switched reluctance motor drive for Aircraft Power Systems
    IET Electrical Systems in Transportation, 2014
    Co-Authors: Rebecca Todd, Virgilio Valdivia, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, Andrew J. Forsyth
    Abstract:

    A system-level behavioural modelling technique is described for a switched reluctance motor drive. The model enables simple and efficient analysis or simulation of multiple drive Systems such as pumps, actuators and engine starters within a more-electric network, for example, on-board an Aircraft. The behavioural model is based on a Power balance analysis. The transfer functions in the model are parameterised from experimental tests on the drive system, resulting in a simple model that only reproduces the average behaviour of the input-output variables necessary for system-level analysis. No data from the manufacturer is required to develop the model. The technique is discussed and validated using an engine starter in an Aircraft test facility.

  • DC-bus Power quality for Aircraft Power Systems during generator fault conditions
    IET Electrical Systems in Transportation, 2011
    Co-Authors: Rebecca Todd, Andrew J. Forsyth
    Abstract:

    Higher-voltage, 540 V, Aircraft DC-bus Power quality is examined experimentally and by computer simulation during a short-circuit fault across the phase terminals of a 70 kW, five-phase, permanent magnet fault-tolerant generator. The DC-bus transients caused by the short-circuiting of the generator phases are seen to exceed the limits in MIL-STD-704F and a control algorithm is proposed for a supercapacitor-based energy storage device that mitigates the transients. The controller performance is illustrated by computer simulations for a range of bus switching scenarios.

Graeme Burt - One of the best experts on this subject based on the ideXlab platform.

  • evaluating the reliability availability of more electric Aircraft Power Systems
    International Universities Power Engineering Conference, 2012
    Co-Authors: R. D. Telford, Stuart Galloway, Graeme Burt
    Abstract:

    With future Aircraft designs increasingly embracing the more-electric concept, there is likely to be a greater reliance on electrical Systems for safe flight. More-electric Aircraft (MEA) will have a greater number of electrical loads which are critical to the Aircraft flight. It therefore is essential that the design of Aircraft Power Systems embraces new technologies and methods in order to achieve targets for Aircraft certification. The various design drivers (e.g. weight, space) for Aircraft will also have to be considered when incorporating reliability into future MEA. This paper will investigate options for future platforms to meet reliability and availability targets whilst continuing to improve overall efficiency. The paper proposes a software tool that has the ability to determine the reliability of a number of potential alternative design architectures. This paper outlines present designs of such Systems and how reliability is enhanced through the use of redundancy and back-up generation. The regulatory challenges associated with Aircraft are summarised, including a discussion on reliability targets for various loads. Techniques for assessing the reliability of Aircraft Systems are described and simple examples of their application to Aircraft electrical Systems are provided. These examples will highlight the advantages and drawbacks attributed to each method and the reasoning behind the selection of these techniques on which an analysis tool can be based.

  • Impact of Converter Interface Type on the Protection Requirements for DC Aircraft Power Systems
    SAE International Journal of Aerospace, 2012
    Co-Authors: Steven Fletcher, Patrick Norman, Stuart Galloway, Graeme Burt
    Abstract:

    The utilization of converter interfaces has the potential to significantly alter the protection system design requirements in future Aircraft platforms. However, the impact these converters will have can vary widely, depending on the topology of converter, its filter requirements and its control strategy. This means that the precise impact on the network fault response is often difficult to quantify. Through the analysis of example converter topologies and literature on the protection of DC networks, this paper tackles this problem by identifying key design characteristics of converters which influence their fault response. Using this information, the converters are classified based on their general fault characteristics, enabling potential protection issues and solutions to be readily identified. Finally, the paper discusses the potential for system level design benefits through the optimisation of converter topology and protection system design.

  • Average-value diode rectifier modeling for aerospace applications
    SAE Technical Paper Series, 2011
    Co-Authors: Patrick Norman, Stuart Galloway, Graeme Burt
    Abstract:

    Modern aerospace Power Systems commonly make use of uncontrolled rectifiers to satisfy many Power conversion needs on board the Aircraft. Whilst being highly accurate, an analytically detailed simulation of the Aircraft Power system, which includes all electric machine dynamics, semiconductor switching states, and Power system dynamics, is often very computationally demanding. Average-value models of Power electronic converters, with their reduced computational requirement, offer one potential solution to this issue. However, of the many converter topologies presented in the literature, average-value models of uncontrolled diode rectifiers are perhaps the most challenging to develop. The dependence of the rectifier's operating state on its loading conditions and the surrounding network topology complicates the derivation of average-value models. As a result, multiple methods, often with unique attributes, have been published, many of which are accurate only for certain modes of operation. This extensive array of methods, each with their unique limitations, makes the selection of an appropriate modeling approach for any given application a difficult task. With the growing utilization of diode based converters within modern Aircraft Systems, and the increasing dependence on modeling and simulation in their design and analysis, this paper presents a timely review on average-value diode rectifier modeling methods and considers their applicability to the demands of modeling and simulation of Aircraft Power Systems. Of the methods reviewed, the parametric approach offers the greatest value to Aircraft Power Systems modeling and simulation. The potential errors incurred with the use of the parametric approach are then illustrated and quantified, and revised guidelines to achieve greater simulation accuracy in the application and further development of the parametric method are then proposed.

  • Solid state circuit breakers enabling optimised protection of DC Aircraft Power Systems
    Proceedings of the 2011 14th European Conference on Power Electronics and Applications, 2011
    Co-Authors: Steven Fletcher, Stuart J. Galloway, Graeme M. Burt, Patrick Norman, Stuart Galloway, Graeme Burt
    Abstract:

    Greater utilisation of DC Power distribution within Aircraft Systems is still largely prevented by the significant challenge of developing lightweight, effective DC protection Systems. By considering circuit breaker, fault detection and Power network design aspects, this paper proposes new performance criteria for optimised protection of DC Aircraft Power Systems and discusses the resulting system level design and operability benefits which can be attained. Through the analysis and simulation of a representative DC Aircraft electrical system, fast acting fault detection and solid state circuit breaker technologies are identified as being critical to this scheme. This paper then presents analysis to help assess the impact of successfully implementing this protection scheme on the circuit breaker's design and operation requirements.

Virgilio Valdivia - One of the best experts on this subject based on the ideXlab platform.

  • Behavioral Modeling of a Switched Reluctance Generator for Aircraft Power Systems
    IEEE Transactions on Industrial Electronics, 2014
    Co-Authors: Virgilio Valdivia, Rebecca Todd, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, Andrew J. Forsyth
    Abstract:

    A system-level modeling technique for a switched reluctance generator (SRG) is described for aerospace applications. Unlike existing techniques, this model is very simple and only reproduces the average behavior of the input-output variables that are required for system-level analysis of the Aircraft Power distribution system. The model is parameterized from the measured generator response, avoiding the need for a detailed knowledge of the equipment structure, which may be unavailable. The modeling procedure is described in detail and validated by measurements on an SRG within an Aircraft test facility.

  • Behavioural modelling of a switched reluctance motor drive for Aircraft Power Systems
    IET Electrical Systems in Transportation, 2014
    Co-Authors: Rebecca Todd, Virgilio Valdivia, Frank J. Bryan, Andrés Barrado, Antonio Lázaro, Andrew J. Forsyth
    Abstract:

    A system-level behavioural modelling technique is described for a switched reluctance motor drive. The model enables simple and efficient analysis or simulation of multiple drive Systems such as pumps, actuators and engine starters within a more-electric network, for example, on-board an Aircraft. The behavioural model is based on a Power balance analysis. The transfer functions in the model are parameterised from experimental tests on the drive system, resulting in a simple model that only reproduces the average behaviour of the input-output variables necessary for system-level analysis. No data from the manufacturer is required to develop the model. The technique is discussed and validated using an engine starter in an Aircraft test facility.