FR3066024A1 - Device for measuring reprogrammable leakage current - Google Patents

Device for measuring reprogrammable leakage current Download PDF

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Publication number
FR3066024A1
FR3066024A1 FR1753932A FR1753932A FR3066024A1 FR 3066024 A1 FR3066024 A1 FR 3066024A1 FR 1753932 A FR1753932 A FR 1753932A FR 1753932 A FR1753932 A FR 1753932A FR 3066024 A1 FR3066024 A1 FR 3066024A1
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France
Prior art keywords
sspc
measuring
means
power controller
current
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Granted
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FR1753932A
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French (fr)
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FR3066024B1 (en
Inventor
Loic Aoustin
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Zodiac Aero Electric
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Zodiac Aero Electric
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Priority to FR1753932A priority Critical patent/FR3066024B1/en
Priority to FR1753932 priority
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01RMEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R31/00Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
    • G01R31/50Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
    • G01R31/52Testing for short-circuits, leakage current or ground faults

Abstract

This device for measuring the leakage current reprogrammable for aircraft comprising at least one semiconductor power supply controller (SSPC '1, SSPC'2) for controlling the supply of an avionic load (CH'1, CH' 2) and comprising a plurality of outputs, the device comprising measuring means (T'11, T12, T'13, T'21, T'22, T'23) of the output current of the semiconductor power supply controller. drivers. Each output of said at least one semiconductor power controller is connected to a measuring means.

Description

Reprogrammable leakage current measurement device

The present invention relates to a reprogrammable leakage current measurement device and relates more particularly to a ground fault current detection device: GFI (“Ground Fault Interrupter”, in English) making it possible to carry out a differential current measurement reprogrammable.

During an electrical fault in an electrical circuit, measuring a leakage current between two or more components of the circuit makes it possible to detect the existence of a fault.

Leakage current is generated by a component connected in short circuit, improper connection of any element or during the degradation of a component.

The leakage current degrades the elements it passes through and presents a danger to people.

When a leakage current is detected, a breaking device is controlled. It cuts the circuit in order to isolate the faulty equipment. The actuation of the cut-off device preserves the elements of the circuit and protects people.

The detection of a leakage current is generally carried out using a transformer, several windings of which couple the different phases supplying the electric power distribution circuit, and a measurement winding enables the differential current to be measured.

Differential transformers are used to detect a leakage current in an aircraft electrical circuit. They are installed in the electrical cores on the current distribution bars of the primary power supply networks or on the electronic cards of the secondary networks. The secondary network electronic cards are generally solid state power controllers (SSPC). Each channel on the SSPC card controls the power supply to an aircraft electrical load.

FIG. 1 illustrates a GFI electrical circuit comprising a multi-path SSPC electronic card protected by a leakage current detection device in an aircraft according to the state of the art.

The circuit includes a three-phase generator G driven by an aircraft turbine powering an SSPC power controller via current distribution bars. The SSPC controller comprises n channels SSPC1, SSPC2, ... SSPCn, a CPU processor and a measurement transformer T. Each phase of the current distribution bars comprises a winding of the transformer T connected between the generator and the channels SSPC1, SSPC2, ..., SSPCn of the SSPC controller, and the measurement winding of the transformer T is connected to the processor CPU. The SSPC controller supplies n electrical loads to the aircraft.

The n channels of the SSPC controller are each connected to an avionics load CH1, CH2 ..., CHn. The SSPC1, ..., SSPCn channels are controlled by the CPU processor.

The magnetic field generated in the transformer T is proportional to the sum of the currents passing through it. The circuit is supplied by a balanced three-phase system. Consequently, when the circuit is not faulty, the magnetic field resulting in the transformer T is zero. The current I induced at the measurement winding of the transformer T is zero.

If the circuit is faulty, for example if a contact is established between a phase connecting the load CHn and the ground of the circuit by means of a metallic structure, a leakage current appears between the phase and the ground. The resulting magnetic field in the transformer T is not zero. Consequently, under the effect of the variation of the magnetic field, the current I is not zero. The processor CPU detects the variation in current and indicates the malfunction to the central management system of the aircraft and / or orders the opening of the different channels SSPC1, SSPC2, ..., SSPCn of the controller SSPC to isolate the faulty circuit and protect the rest of the electrical power system as well as people.

However, the measurement transformer T is large, and operates at low frequency (360-800Hz). It must also allow currents of 5 to 25 amps to pass. Consequently, a single measurement transformer T is used for several channels of the controller to reduce the size of the device. The disadvantage of using a single transformer is that it does not allow the faulty track to be identified. The CPU processor can either transmit information concerning the presence of a fault or disconnect all the current distribution bars. As a result, no more avionics loads connected to the SSPC controller are supplied.

In addition, certain avionic loads are connected directly between a phase and the mechanical mass, the neutral of the generator being connected to the mechanical mass. In the event of failure of such a configuration, the leakage current is equal to the functional current and makes it impossible to use the ground fault detection device GFI (“Ground Fault Interrupter”, in English) on all channels of the SSPC controller.

The object of the invention is therefore to overcome the drawbacks associated with the method of detecting leakage currents of an electrical circuit of an aircraft.

In view of the above, the invention provides a reprogrammable leakage current measurement device for aircraft, comprising at least one semiconductor power controller intended to control the supply of an avionics load and comprising several outputs , the device comprising means for measuring the current of the outputs of the power controller.

According to a characteristic of the device according to the invention, each output of said at least one semiconductor power controller is connected to a measuring means.

According to another characteristic, the measurement means comprise high frequency transformers for measuring the current.

Advantageously, the device further comprises means for controlling the at least one semiconductor power controller, first connection means connecting the measurement means to the control means and second connection means connecting the control means to said at least one power controller.

Preferably, the first connection means comprise one or more multiplexers. The invention also relates to a leakage current measurement method for the implementation of a reprogrammable leakage current measurement device for aircraft comprising at least one semiconductor power controller for the power supply. at least one avionics load and comprising several outputs, means for measuring the current of the outputs of the semiconductor power controller, means for controlling the semiconductor power controller.

According to a characteristic of the method according to the invention, as soon as a leakage current is detected by the control means on an output of the at least one semiconductor power controller, the control means cut off the electrical supply of the outputs of said at least one power controller.

Advantageously, the measurement means are high frequency transformers for measuring the current operating at zero magnetic flux.

According to another characteristic of the method, the at least one avionic load is connected between phases or between phase and ground.

Advantageously, the configuration of the measurement means is configurable. Other objects, characteristics and advantages of the invention will appear on reading the following description, given solely by way of nonlimiting example, and made with reference to the appended below in which: - Figure 1, which it has already was mentioned, is a schematic view of a device for detecting and measuring the leakage current in an electrical circuit of an aircraft according to the state of the art; - Figure 2 is a schematic view of a first embodiment of a device for detecting and measuring the leakage current in an electrical circuit of an aircraft, according to the invention; and - Figure 3 is a schematic view of a second embodiment of a device for detecting and measuring the leakage current in an electrical circuit of an aircraft, according to the invention.

Reference is made to FIG. 2 which illustrates a first embodiment of a device for measuring the leakage current according to the invention. This device detects and measures the leakage current in the event of a fault, and identifies the supply line for the faulty electrical load.

The current measurement device includes a multi-channel SSPC power controller.

In what follows, by way of nonlimiting example and for the sake of clarity, the power controller SSPC ’has two channels.

The electrical circuit includes a generator G ’driven by a turbine of the aircraft. The generator outputs are connected to the two-way SSPC ’power supply controller. The outputs of the SSPC controller ’feed the aircraft’s CH’b CH’2 loads.

The SSPC controller ’has two power supply lines ALIMi and ALIM2 supplying the associated loads CH’i and CH’2 and a processor CPU’ as control means.

Another example of control means that can also be cited is a logic gate system using an operational amplifier associated with a comparator.

The ALIMi and ALIM2 channels are of identical constitution. Subsequently, the architecture of the ALIM2 supply path is detailed.

The inputs of the supply line ALIM2 are connected to the generator G ’and to the ground of the aircraft GND’. The outputs of the ALIM2 channel are connected to the CH’2 load.

The ALIM2 channel includes a SSPC'2 semiconductor power controller, an MLX2 multiplexer and three high-frequency transformers for measuring the current of identical constitution T'2i, T'22, T'23 each comprising a primary circuit comprising a primary winding and a secondary circuit comprising a secondary winding.

The inputs of the SSPC’2 semiconductor power controller are connected to generator G ’and to GND’ of generator G ’. The outputs of the SSPC’2 semiconductor power controller are connected to the CH’2 load. Each first connection of the primary winding of a high-frequency transformer for measuring current T'2i, T'22, T'23 is connected to a different output of the semiconductor power controller SSPC'2 and the second connection of the primary winding of each transformer is connected to the phase of the load CH'2 corresponding to the output of the semiconductor power controller SSPC'2.

The connections of the secondary winding of transformers T’2i, T’22, T’23 are connected to the inputs of an MLX2 multiplexer. The output of the MLX2 multiplexer is connected to a PLC processing unit ’. For example, the processing unit is made from a processor, but it can be any device capable of controlling an SSPC controller. It can in particular be a microcontroller.

According to another embodiment illustrated in FIG. 3, the SSPC controller ’comprises an MLX multiplexer replacing the MLXi and MLX2 multiplexers. The connections of the secondary winding of all the high-frequency transformers for measuring the current T'n, T'i2, T'i3, T'2i, T'22 and T'23 of the SSPC 'controller are connected to the inputs of the multiplexer MUX. The output of the MUX multiplexer is connected to a CPU processing unit ’. The use of a transformer per phase and one or more multiplexers allow reprogramming the measurement of the differential current according to the phases to be measured.

The CPU selects and inhibits the measurement of the channels connected to the ground fault detection device GFI ("Ground Fault Interrupter" in English) via the MUX multiplexer or the MUXi and MUX2 multiplexers.

Channel selection can be done through any other known selection system.

The CPU ’is connected to the SSPC’i and SSPC’2 solid state power controllers.

In operation, the processor CPU ’selects the channels to be monitored via the MUX multiplexer or the MUXi and MUX2 multiplexers. The CPU ’can modify the configuration of the multiplexers at any time to select other channels to monitor, in particular according to the connected loads or alternately sweep the ALIMi and ALIM2 channels to detect a fault on one of the channels.

High frequency current measurement transformers operate at zero magnetic field. A current is injected into the secondary circuit of the transformers to regulate a zero output voltage and maintain an induction close to 0 tesla. From the value of the currents injected into the secondary circuits of the transformers, the value of the currents flowing in the phases of the selected channel is deduced.

Advantageously, the architecture described allows the reconfiguration of the GFI ground fault detection device on all channels. The use of high frequency current measurement transformers operating in zero magnetic fields reduces the volume of the magnetic circuit. Consequently, the size of the transformers is reduced. The space occupied by the printed circuit board (PCB) supporting the device therefore remains limited.

When a fault is detected on a phase, for example on the ALIM2 channel, the CPU processor controls the opening of the ALIM2 channel by controlling the semiconductor power controller SSPC’2.

Consequently, only the faulty channel is open.

When one or more channels are connected to loads connected between phases and ground, the architecture presented makes it possible to keep the GFI ground fault detection function on the other channels.

Advantageously, the leakage current measurement device measures the leakage current with sufficient precision to ensure the protection of people and equipment.

Claims (8)

1. Device for measuring the reprogrammable leakage current for aircraft comprising at least one semiconductor power controller (SSPC'i, SSPC'2) intended to control the supply of an avionics load (CH'i, CH '2) and comprising several outputs, the device comprising means of measurement (T'n, T'12, T'i3; T'21, T'22, T'23) of the current of the outputs of the power supply controller, characterized in that each output of said at least one semiconductor power controller is connected to a measuring means.
2. Measuring device according to claim 1, in which the measuring means comprise high frequency transformers for measuring the current (T'n, T'i2, T'13, T'2i, T'22, T'23) .
3. Measuring device according to one of claims 1 and 2, further comprising control means (CPU ') of the at least one semiconductor power controller (SSPC'i, SSPC'2), of the first connection means (MUXi, MUX2, MUX) connecting the measurement means to the control means and second connection means connecting the control means to said at least one power supply controller.
4. Measuring device according to claim 3, wherein the first connection means comprise one or more multiplexers (MUXb MUX2, MUX).
5. Leakage current measurement method for the implementation of a reprogrammable current measurement device for aircraft comprising at least one semiconductor power controller (SSPC'i, SSPC'2) for the power supply electrical of at least one avionics charge (CH'i, CH'2) and comprising several outputs, measuring means (T'n, T'i2, T'13, T'2i, T'22, T'23 ) the current of the outputs of the semiconductor power controller and the control means (CPU ') of the semiconductor power controller (SSPC'i, SSPC'2), characterized in that as soon as a leakage current is detected by the measuring means on an output of the at least one power controller, the control means cut off the electrical supply of the outputs of said at least one power controller.
6. Method according to claim 5, in which the measuring means are high frequency transformers for measuring the current (T'n, T'12, T'13, T'21, T'22, T'23) operating at zero magnetic flux.
7. Method according to one of claims 5 or 6, wherein the at least one avionics charge (CH’i, CH’2) is connected between at least one phase and one ground.
8. Method according to any one of claims 5 to 7, wherein the configuration of the measuring means is configurable.
FR1753932A 2017-05-04 2017-05-04 Device for measuring reprogrammable leakage current Active FR3066024B1 (en)

Priority Applications (2)

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FR1753932A FR3066024B1 (en) 2017-05-04 2017-05-04 Device for measuring reprogrammable leakage current
FR1753932 2017-05-04

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Application Number Priority Date Filing Date Title
FR1753932A FR3066024B1 (en) 2017-05-04 2017-05-04 Device for measuring reprogrammable leakage current
PCT/EP2018/061333 WO2018202769A1 (en) 2017-05-04 2018-05-03 Device for measuring the reprogrammable leak current

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FR3066024A1 true FR3066024A1 (en) 2018-11-09
FR3066024B1 FR3066024B1 (en) 2019-05-10

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0391812A1 (en) * 1989-04-06 1990-10-10 Merlin Gerin D.C. current network insulation monitoring system
US20110222200A1 (en) * 2010-03-09 2011-09-15 Honeywell International Inc. High power solid state power controller (sspc) solution for primary power distribution applications
EP2757647A2 (en) * 2013-01-21 2014-07-23 Hamilton Sundstrand Corporation Reconfigurable matrix-based power distribution architecture

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0391812A1 (en) * 1989-04-06 1990-10-10 Merlin Gerin D.C. current network insulation monitoring system
US20110222200A1 (en) * 2010-03-09 2011-09-15 Honeywell International Inc. High power solid state power controller (sspc) solution for primary power distribution applications
EP2757647A2 (en) * 2013-01-21 2014-07-23 Hamilton Sundstrand Corporation Reconfigurable matrix-based power distribution architecture

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FR3066024B1 (en) 2019-05-10
WO2018202769A1 (en) 2018-11-08

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