WO2011071664A2 - Groupe électrogène de parc pour aéronef - Google Patents

Groupe électrogène de parc pour aéronef Download PDF

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Publication number
WO2011071664A2
WO2011071664A2 PCT/US2010/056880 US2010056880W WO2011071664A2 WO 2011071664 A2 WO2011071664 A2 WO 2011071664A2 US 2010056880 W US2010056880 W US 2010056880W WO 2011071664 A2 WO2011071664 A2 WO 2011071664A2
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WO
WIPO (PCT)
Prior art keywords
signal
output
power
switched
converter
Prior art date
Application number
PCT/US2010/056880
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English (en)
Other versions
WO2011071664A3 (fr
Inventor
Milind Ratnaparkhi
Keith Welker
Original Assignee
Illinois Tool Works Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Illinois Tool Works Inc. filed Critical Illinois Tool Works Inc.
Publication of WO2011071664A2 publication Critical patent/WO2011071664A2/fr
Publication of WO2011071664A3 publication Critical patent/WO2011071664A3/fr

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Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
    • H02M7/02—Conversion of ac power input into dc power output without possibility of reversal
    • H02M7/04—Conversion of ac power input into dc power output without possibility of reversal by static converters
    • H02M7/12—Conversion of ac power input into dc power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
    • H02M7/21—Conversion of ac power input into dc power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal
    • H02M7/217—Conversion of ac power input into dc power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/35—Ground or aircraft-carrier-deck installations for supplying electrical power to stationary aircraft
    • B64F1/352—Mobile units
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/36—Arrangements for transfer of electric power between ac networks via a high-tension dc link
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/36—Other airport installations
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M1/00—Details of apparatus for conversion
    • H02M1/0067—Converter structures employing plural converter units, other than for parallel operation of the units on a single load
    • H02M1/007—Plural converter units in cascade
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M3/00—Conversion of dc power input into dc power output
    • H02M3/22—Conversion of dc power input into dc power output with intermediate conversion into ac
    • H02M3/24—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters
    • H02M3/28—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac
    • H02M3/325—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal
    • H02M3/335—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
    • H02M3/33569—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only having several active switching elements
    • H02M3/33573—Full-bridge at primary side of an isolation transformer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management

Definitions

  • the present disclosure relates generally to ground support equipment for aircraft and, more specifically, to ground power units for providing electrical power to an aircraft.
  • ground support equipment In the aviation industry, a wide variety of ground support equipment is available to provide electrical power and conditioned air, among other things, to aircraft. As will be appreciated, many aircraft are capable of generating their own electric power, such as through the use of onboard generators powered by the aircraft engines. However, because the generation of power by the aircraft engines consumes fuel, it is generally desirable to disable such engines when an aircraft will be stationary on the ground for any sustained period.
  • GPUs external ground power units
  • GPUs may be advantageously utilized to provide electric power to aircraft parked at airport terminals, in hangers, on runways, or at some other location, which facilitates operation of a number of aviation systems, including communications systems, lighting systems, avionics, air conditioning systems, and the like, while the aircraft engines are powered down.
  • the power provided by GPUs may supplement power provided during operation of the engines while an aircraft is on the ground.
  • Embodiments of a ground power unit are disclosed for providing power to a grounded vehicle, such as an aircraft.
  • the ground power unit accepts a wide range of AC input voltages and is capable of providing a range of DC output voltages.
  • the GPU may include a switched rectifier that converts an AC input power to a DC link power.
  • the DC link power is then converted to a switched DC signal that simulates an AC-like sine wave using a high frequency DC-to-DC switching converter.
  • a single-phase transformer modulates and isolates the switched DC signal, which is subsequently converted to a DC output signal using diode rectifiers coupled to the secondary winding of the transformer.
  • the disclosed GPU may be controlled using a software-based control algorithm that controls the AC input parameters independently of the DC voltage parameters.
  • the GPU includes control logic that measures the AC input voltage and determines an appropriate switching pattern for the switched rectifier. The output of the rectifier (e.g., a DC link power) is then measured, and the DC-to-DC switching converter is controlled to operate at a duty cycle that achieves a desired output voltage.
  • FIG. 1 illustrates a perspective view of an aircraft coupled to a ground power unit, in accordance with one embodiment of the present technique
  • FIG. 2 illustrates a perspective view of an aircraft coupled to a ground power unit, in accordance with another embodiment of the present technique
  • FIG. 3 illustrates a perspective view of an aircraft coupled to a ground power unit that is integrated into a jet bridge, in accordance with a further embodiment of the present technique
  • FIG. 4 is a functional block diagram depicting components of a ground power unit, in accordance with an embodiment of the present technique.
  • FIG. 5 is a circuit schematic illustrating certain components of the functional block diagram of FIG. 4, in accordance with an embodiment of the present technique.
  • ground power unit may support a wide range of AC input voltages and provide a range of DC output voltages.
  • the GPU may include a switched rectifier configured to convert an AC input signal to a DC link signal.
  • a high frequency DC-to-DC switching converter then converts the DC link signal to a switched DC signal that simulates a sine wave based upon a duty cycle determined by control circuitry for achieving a desired DC output level.
  • a single-phase transformer modulates and isolates the switched DC signal, which is then rectified to the desired DC output signal using diode rectifiers coupled to the secondary winding of the transformer.
  • the GPU may be controlled using a software- based algorithm that controls the AC input parameters independently of the DC voltage parameters. For instance, in one embodiment, the control algorithm measures the AC input signal and determines an appropriate switching pattern for the switched rectifier. The output of the rectifier (e.g., a DC link power) is then measured, and the DC-to-DC switching converter is controlled to operate at a duty cycle that achieves the desired output voltage.
  • FIG. 1 illustrates a grounded aircraft system 10 that includes a grounded aircraft 12 and a ground power unit (GPU) 14 in accordance with aspects of the present disclosure.
  • the GPU 14 may supply power to the aircraft 12 while the aircraft 12 is grounded.
  • the grounded aircraft 12 may be a military aircraft, such as a military jet, helicopter, or carrier airplane, or may be any commercial or private aircraft, such as a commercial aircraft for transporting civilian passengers, or a cargo or freight aircraft.
  • the system 10 may include a cart 16 for supporting the GPU 14 and facilitating the transport of the GPU 14 from one location to another.
  • the GPU 14 may thus provide output power for powering one or more components of the grounded aircraft 12 by way of the power cable 18.
  • power may be supplied to the GPU 14 from an external power source or grid by way of an input power cable 20.
  • the aircraft 12 may continue to operate a variety of onboard systems, such as air conditioning systems and electrical systems, without having to generate its own power via onboard generators (e.g., aircraft engines), thereby conserving fuel.
  • the GPU 14 may have wheels integrally coupled thereto to facilitate transportation of the GPU 14.
  • the GPU 14 may be configured to accept a wide range of AC input voltages (V AC ) and frequencies, and to convert the AC input to a desired DC voltage for supporting a variety of aircraft types.
  • V AC AC input voltage
  • the configuration of the GPU 14 to accept different AC inputs is automatically set by a control algorithm (e.g., does not require manual intervention when a change in input voltage is detected) that senses the AC input and adjusts the switching of certain components (e.g., a rectifier and DC-to-DC converter) automatically.
  • the GPU 14 may accept any input voltage between approximately 200 V AC and 600 V AC -
  • the GPU 14 may also be configured to accept single-phase or three-phase AC input voltage at line frequencies of 50 or 60 Hz.
  • the GPU 14 may further be configured to accept a 400 Hz AC input voltage.
  • Table 1 below depicts a range of AC input voltages, as well as frequencies and phases that may be supported by an embodiment of the GPU 14.
  • the GPU 14 may be configured to accept input voltages between approximately 200 V AC and 600 V AC , with a tolerance of 10 percent.
  • FIG. 2 illustrates an alternate embodiment of the system 10, in which the GPU 14, rather than receiving power from a grid, receives power by a combination of an engine and generator 22 (e.g., an engine- generator unit).
  • the GPU 14 may be electrically coupled to a standalone engine- generator unit 22.
  • the cart 16 may be designed to support both the GPU 14 and the engine- generator 22, or separate respective carts may support each of the GPU 14 and the engine-generator unit 22.
  • such a configuration may be particularly well-suited in situations where grid power is not readily available or is not conveniently located in close proximity to the aircraft 12.
  • FIG. 3 illustrates a further embodiment of the system 10, in which the GPU 14 is integrated into a jet bridge 26 connected to an airport terminal or gate 28.
  • the GPU 14 may be coupled to an outer wall 30 of the jet bridge 26.
  • power may be supplied to the GPU 14 from the airport power source 30 (e.g., grid power) by way of a power cable 32, and the GPU 14 may provide output power to the aircraft by way of a power cable 34.
  • the power cables 32 and 34 may be enclosed within the walls of the jet bridge 26 and hidden from the view of passengers entering and exiting the aircraft 12 through the jet bridge 26.
  • the jet bridge 26 may also include a 400 hertz converter 36.
  • the GPU 14, instead of receiving power from the airport power source 30, may receive power from the 400 hertz converter 36.
  • the GPU 14 may receive an AC input power signal 40 from either a grid or an engine-generator unit 22.
  • the input power signal 40 may be single-phase or three-phase, and may be between 200 to 600 V AC - Additionally, the input power signal 40 may have a frequency of 50, 60, or 400 Hz.
  • a switched rectifier 42 receives the input power signal 40 and rectifies it to a high DC link voltage, referred to herein by reference number 44.
  • the AC input power signal 40 may also be received by a DC power supply unit 46 configured to convert the AC input voltage into multiple DC voltage inputs 48.
  • the DC inputs 48 may include a 24 V DC signal for powering the control logic 50, and a 15 V DC signal, which may be used to drive the switching devices in the DC-to-DC switched converter 56, as will be discussed further below.
  • the switched rectifier 42 may include one or more solid-state semiconductor switching devices, such as silicon controller rectifiers, thyristors, diodes, and so forth.
  • the switching of the rectifier 42 may be controlled via control signals 52 determined by control logic 50.
  • the rectifier 42 under the control of the signals 52, may produce a DC link voltage 44 that is approximately 1.34 times the V RMS of the AC input voltage.
  • the DC link voltage 44 is then received by stabilization circuitry 54 which may be configured to provide power factor and/or harmonic improvements to the DC link voltage signal 44.
  • the rectified DC link voltage may be a high level DC voltage, such as between approximately 600 to 900 V DC -
  • the DC link voltage 44 is then brought down to a lower level voltage by the DC-to-DC switched converter 56.
  • the DC- to-DC switched converter 56 may be implemented in one embodiment as a full bridge converter, which may include insulated-gate bipolar transistors (IGBTs) configured in an H-bridge arrangement.
  • the duty cycle of the converter 56 may be modulated using a control algorithm executed by the control logic 50. For instance, as shown in FIG. 3, the control logic 50 may measure the DC link voltage 44 and output the control signals 58 to the converter 52 to control switching of the transistors, and thus the duty cycle of the converter 52, to achieve a desired output voltage level. In this manner, the controls needed for generating the desired DC levels are independent of the AC inputs.
  • the converter 56 may utilize high speed switching frequencies of between approximately 10 kHz to 20 kHz, and may output DC square wave pulse signals 60 that simulate a sine wave. In one embodiment, the converter 56 may operate at a generally constant 20 kHz switching frequency to reduce or substantially eliminate noise. By utilizing this high switching frequency, the GPU 14 is able to accept 400 Hz AC inputs directly.
  • the converter 56 may also utilize a zero voltage switching technique, such that the pulse width is modulated only when required by the output load (e.g., on the output terminal 88 side). By utilizing zero voltage switching, voltage spikes, switching losses, heat, and electromagnetic interference (EMI) may be reduced.
  • EMI electromagnetic interference
  • the DC output signal 60 of the converter 56 drives a primary winding of a single-phase transformer 62, which drops the switched DC voltage signal 60 to a desired output level.
  • the secondary pulse of the transformer 62 is center tapped (e.g., grounded), as indicated by reference number 72, to provide a floating reference point for the DC output.
  • the current across the transformer 62 is provided to the control logic 50, as indicated by reference number 64, where it is used for controlling the switching of the IGBTs in the converter 56 via diode conduction.
  • the use of a single phase transformer 62 replaces larger and bulkier multi-phase transformers common in conventional ground power units.
  • the GPU 14 may exhibit substantial weight reduction and less complex components compared to certain conventional GPU devices.
  • the GPU 14 may exhibit a weight reduction of between 250 to 750 pounds when compared to certain conventional GPU devices.
  • the positive and negative outputs of the secondary winding of the transformer 62 are then rectified by the diode bridges 68 and 70, respectively, to produce the desired DC output.
  • the diode bridges 68 and 70 may be arranged in a parallel configuration to accommodate large startup currents.
  • the rectified DC output 74 from the diode bridges 68 and 70 is further stabilized by filtering circuitry 76.
  • the filtering circuitry 76 may filter and reduce current ripple and/or voltage ripple in the rectified DC signal 74.
  • a shunt resistor 80 is coupled in the path of the filter DC output 78, and typically has a very low resistance (e.g., milliohms).
  • the shunt resistor 80 functions to supply a current feedback 82 to the control logic 50 for control and safety purposes without noticeably affecting the DC output 78.
  • the DC output 78 is then supplied to the output terminals 88, whereby it may be transmitted via a power cable (e.g., 18 in FIGS. 1 and 2, or 34 in FIG. 3) to a load (e.g., aircraft 12).
  • the GPU 14 may be configured to provide a DC output voltage of 28 V DC -
  • the GPU 14 may be capable of providing anywhere from between approximately 14 to 56 V DC -
  • the desired DC output voltage may be modulated by adjusting the duty cycle of the converter 56.
  • the control logic 50 may include one or more processors, such as a microprocessor, ASIC, or FPGA configured to execute a control algorithm.
  • the control algorithm may be provided as machine-readable encoded instructions stored on a machine-readable medium, such as memory, a hard-drive, an optical storage device, an EEPROM, a flash memory device, or the like.
  • the control algorithm may provide the control signals 52 and 58 for controlling the switching of the rectifier 42 and the converter 56, respectively, as mentioned above.
  • the control algorithm measures the AC input voltage 40, and computes the desired switching sequence (e.g., an SCR firing sequence) for the rectifier 42 to achieve the desired DC link voltage 44.
  • the control algorithm also measures the resulting DC link voltage 44 and computes the duty cycle needed to achieve the desired DC output voltage 78.
  • the DC output of the GPU 14 is driven by controlling the duty cycle of the converter 56 independently of the AC input voltage.
  • the control algorithm may also adjust the DC output voltage 78 for line drop compensation.
  • the various levels of compatible AC inputs e.g., Table 1
  • DC outputs e.g., 14 to 56 V DC
  • the disclosed GPU 14 may provide for automatic realignment of variable power inputs by adjusting the rectifier switching sequence (e.g., control signals 52) and/or the converter duty cycle (e.g., control signals 58).
  • the disclosed GPU 14 may support a number of applications having different power requirements without requiring the maintenance and upkeep of separate GPUs for different power standards.
  • the control logic 50 may include a controller area network (CAN) protocol interface 90, enabling the control logic 50 to communicate with the user interface board 92.
  • the user interface board 92 may provide additional commands, such as start, stop, reset, or manual stop (e-stop) commands that may be initiated or called by an operator.
  • the operator may operate a service terminal 94, which may be located locally or remotely with respect to the GPU 14, and may include an LCD or VFD display panel.
  • the display panel may display current operating parameters, which may be edited or adjusted by an operator.
  • the service terminal 94 may communicate with the user interface board 92 via several interfaces, including universal serial bus (USB), Ethernet, or by the Recommended Standard 232 (RS-232) protocol, as represented by reference number 96.
  • USB universal serial bus
  • RS-232 Recommended Standard 232
  • the CAN interface 90 may also provide for communication between the control logic 50 and an engine- generator controller 100.
  • an operator may also control one or more operating parameters of an engine 102 and/or a generator 104 of the engine- generator unit 22 from the service terminal 94.
  • the control logic 50 may include a flash memory card or some other type of storage device for storing operation data (e.g., statistics), fault and/or failure data, and so forth.
  • FIG. 5 shows a circuit schematic that depicts certain functional components of the GPU 14 illustrated in FIG. 4 in more detail.
  • the switched rectifier 42 may be an SCR bridge rectifier that includes the SCRs 110, 112, 114, 116, 118, 120, as arranged in FIG. 5.
  • the SCRs 110- 120 may rectify a single-phase or three-phase AC input signal 40 to a DC link voltage 44.
  • the stabilization circuitry 54 receives the DC link voltage 44 and provides power factor and/or harmonic improvements.
  • the stabilization circuitry 54 may include the inductor 122, resistors 124 and 126, and capacitors 128 and 130.
  • the inductor 122 may be configured to provide power factor and/or harmonic improvements. Further, the capacitors 128 and 130 are configured to maintain the high level DC link voltage output from the SCR bridge rectifier 42. The resistors 124 and 126 are arranged to balance an even voltage across each of the capacitors 128 and 130.
  • the DC-to-DC converter 56 includes the capacitors 132 and 134, a first set of IGBTs 136 and 138 coupled to the negative side of the primary winding 154 of the transformer 62, and a second set of IGBTs 140 and 142 coupled to the positive side of the primary winding 154.
  • the IGBTs 136, 138, 140, and 142 are configured in an H-bridge arrangement and are coupled to the diodes 144, 146, 148, and 150, respectively.
  • the switching of the IGBTs 136-142 may be controlled by the control logic 50 based upon the DC link voltage 44 to achieve a duty cycle that produces a desired output voltage.
  • the IGBTs 136 and 142 may be switched on, and on the second half of the cycle, the IGBTs 138 and 140 may be switched on. This results in a switched DC square wave signal 60 that simulates a sine wave.
  • the switched DC output 60 of the IGBT H-bridge converter 56 is provided to the primary winding 154 of the transformer 62.
  • the secondary winding 156 is centered tapped 72 (e.g., grounded) to providing a floating reference point for the DC output.
  • the secondary winding 156 provides the DC switched signal 60 to the diode bridges 68 and 70, which rectify the switched DC signal 60 to produce the desired DC output 78.
  • the diode bridge 68 may include the diodes 160, 164, 168, and 172
  • the diode bridge 70 may include the diodes 162, 166, 170, and 174, configured as shown in FIG. 5.
  • the output of diode bridges 68 and 70 may be filtered by the inductors 176 and 178, respectively, to produce the DC output signal 78 that is provided to the output terminals 88 which may be coupled to a power cable for delivering the DC output to a load, such as an aircraft (e.g., 12). That is, the inductors 176 and 178 may make up part of the filtering circuitry 76 of FIG. 4. Further, while only the inductors 176 and 178 are shown in FIG. 5, it should be appreciated that in other embodiments, the filtering circuitry 76 may also include capacitors, as well as a combination of capacitor and inductors.
  • embodiments of the GPU disclosed herein offer several technical advantages over conventional GPUs.
  • the arrangement of components within the disclosed GPU 14 provides that the AC input signal is converted to a DC link signal and then to a switched DC signal prior to being transformed.
  • This allows for the use of a single-phase transformer (e.g., transformer 62), which provides for reduced cost and overall equipment size compared to conventional GPUs, which commonly use bulky multi-phase transformers for transforming the AC input signal directly.
  • transformer 62 single-phase transformer
  • transformer 62 transformer e.g., transformer 62
  • a transforming element is located downstream of a rectifier that receives the AC input.
  • the GPU 14 utilizes a DC-to-DC converter 56 that operates at a high frequency of between approximately 10-20 kilohertz. This allows for the GPU 14 to accept 400 hertz AC input signals directly due to the controller being able to modulate the duty cycle as needed (e.g., "on the fly") according to the input frequency. In certain embodiments, input frequencies of between 10 hertz to 1000 hertz (1 kilohertz) may be accepted by the GPU 14. In contrast, conventional GPUs commonly accept only 50 or 60 hertz signals. Moreover, the DC-to-DC converter 56 is self-controlled in the sense that the duty cycle of the converter may be modulated independently of the AC input signal. Additionally, the DC-to-DC converter 56 utilizes zero volt switching, such that the pulse width of the switched DC output is modulated only when needed by the output load.

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Dc-Dc Converters (AREA)
  • Rectifiers (AREA)

Abstract

La présente invention concerne des modes de réalisation d'un groupe électrogène de parc destiné à alimenter un véhicule au sol, tel qu'un aéronef. Selon certains modes de réalisation, le groupe électrogène de parc (GPU) accepte une large gamme de tensions d'entrée alternatives, et peut fournir toute une gamme de tensions de sortie continues. Le GPU peut comprendre un redresseur commuté qui convertit un signal d'entrée de courant alternatif en un signal de renvoi de courant continu. Le signal de renvoi de courant continu est ensuite converti en un signal de courant continu commuté qui simule une onde sinusoïdale semblable à une onde alternative en utilisant un convertisseur à commutation continu-continu à haute fréquence. Un transformateur monophasé module et isole le signal de courant continu commuté, qui est par la suite converti en un signal de sortie de courant continu en utilisant des redresseurs à diode couplés à l'enroulement secondaire du transformateur. Le GPU décrit peut être commandé en utilisant un algorithme de commande basé sur un logiciel qui commande les paramètres d'entrée de courant alternatif indépendamment des paramètres de tension continue.
PCT/US2010/056880 2009-12-07 2010-11-16 Groupe électrogène de parc pour aéronef WO2011071664A2 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US26735109P 2009-12-07 2009-12-07
US61/267,351 2009-12-07
US12/723,365 2010-03-12
US12/723,365 US9413264B2 (en) 2009-12-07 2010-03-12 Ground power unit for aircraft

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Publication Number Publication Date
WO2011071664A2 true WO2011071664A2 (fr) 2011-06-16
WO2011071664A3 WO2011071664A3 (fr) 2012-06-14

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