IMPROVED INTERFACE FOR CONTROLLING AND NEUTRALIZING AN ELECTRICAL POWER SUPPLY LINE OF AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH AN INTERFACE.

Abstract

The invention relates to an improved interface for controlling an aircraft electrical power supply line, the interface being configured to easily and quickly control an absence of electrical potential at at least one determined point of an aircraft electrical installation comprising high-voltage equipment. The invention also relates to an aircraft comprising such an improved interface. Advantageously, it is thus possible to simplify procedures for securing intervention on said installation and to increase safety. Fig. 1

Description

Title of the invention: IMPROVED INTERFACE FOR CONTROLLING AND NEUTRALIZING AN ELECTRICAL POWER SUPPLY LINE OF AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH AN INTERFACE. Technical field

[0001] The present invention relates to an interface for controlling and neutralizing an electrical power supply line intended to supply at least one piece of equipment on board an aircraft. The invention relates more particularly to an interface making it possible to control an absence or presence of electrical potential at one or more points of an electrical power supply line and to neutralize the electrical power supply line if necessary by connection to a reference equipotential. STATE OF THE PRIOR ART

[0002] A control or maintenance intervention on an electrical power supply line involves compliance with safety procedures aimed at checking the electrical condition of the power supply line and neutralizing the power supply line in order to be able to intervene there without risk of electrocution.

[0003] Voltmeter or multimeter type control tools, discharge poles and conductors with earth connection clamps are conventionally used to carry out such control and neutralization operations prior to an intervention on an electrical distribution line or in an electrical distribution panel. The environment of an aircraft appears specific with regard to the distribution of electrical energy since numerous pieces of equipment are gathered in reduced, even cramped, spaces. The electrical energy density of some of the circuits on board an aircraft is such that the usual means of control and neutralization are not very suitable for the specific environment inside an aircraft, particularly in technical spaces. There is therefore a need to optimize the means of control and neutralization of the electrical supply lines on board an aircraft and the situation can be improved. Statement of the invention

[0004] An object of the present invention is to provide simple and rapid possibilities for controlling an electrical power supply line on board an aircraft. To this end, an interface for controlling an electrical power supply line of an aircraft is proposed, the electrical power supply line being configured to power electrical equipment of the aircraft, the control interface comprising an insulation box electrically crossed by at least one electrically conductive element of the electrical supply line, connected to the equipment and provided with an electrically insulating sheath outside the equipment and the electrical insulation box and having a surface free of electrical insulation inside the electrical insulation box, the control interface being arranged such that: - a calibrated opening is arranged in the electrical insulation box opposite the surface devoid of electrical insulation of each of the electrically conductive elements, - each of the electrically conductive elements is electrically connected to a connection pad arranged on an outer surface of the electrically insulating housing, and, - a removable neutralizing conductor, connected to a reference equipotential and having a terminal connector configured for connection to a connection pad of the electrical insulation box is available for connection to said pad.

[0005] The control interface of an electrical power supply line according to the invention may further have the following characteristics, considered alone or in combination: - Two electrically conductive elements pass through the electrically insulating housing, which housing comprises two calibrated openings respectively arranged opposite two surfaces devoid of electrical insulation each arranged on one of the two electrically conductive elements, two connection pads respectively connected to the two electrically conductive elements and the interface comprises two removable neutralization conductors connected to a reference equipotential and each comprising a terminal connector each configured to operate an electrical connection to one of said pads. - A calibrated opening of the electrical insulation box is a bore with a diameter less than or equal to 12.5 mm and whose central longitudinal axis passes through the surface devoid of electrical insulation of the electrical element opposite which it is arranged in the electrical insulation box. - Any connection pad of the electrical insulation box and any neutralizing conductor is electrically insulated to prevent any tactile contact with an element electrically connected to an electrically conductive element. - The control interface is arranged on one side of an aircraft's electrical equipment.

[0006] The invention also relates to an electrical system of an aircraft comprising electrical equipment and a control interface as previously described.

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[0015] According to one embodiment, the aircraft electrical system as described above further comprises at least one measuring or discharge probe arranged to be inserted into a calibrated opening of the interface and to establish electrical contact with the surface devoid of electrical insulation arranged opposite the opening. The invention also relates to an aircraft comprising at least one control interface as previously described or a system as mentioned above. Finally, the invention relates to a method for controlling and neutralizing an electrical power supply line of an aircraft, the method being executed via a control interface as mentioned above and the method comprises: - a measurement of the electrical potential of at least one electrically conductive element, relative to the reference equipotential, by inserting a measuring probe into the calibrated opening arranged opposite said surface devoid of electrical insulation of said electrically conductive element, - an electrical potential discharge of at least one electrically conductive element by inserting a discharge probe into the calibrated opening arranged opposite said surface devoid of electrical insulation of said electrically conductive element, and, - neutralization of at least one electrically conductive element of the power supply line by connecting a terminal connector of a removable neutralization conductor to the connection pad of the control interface connected to this electrically conductive element of the power supply line. Brief description of the drawings The above-mentioned and other features of the invention will become more clearly apparent from the following description of an exemplary embodiment, said description being made in conjunction with the accompanying drawings: [Fig.l] schematically and symbolically illustrates a power supply control interface according to one embodiment; [Fig.2] schematically illustrates an aircraft comprising a control interface as illustrated in [Fig.l] or an electrical system comprising such an interface; and, [Fig.3] is a diagram illustrating a method of controlling and neutralizing an electrical power line according to one embodiment. DETAILED PRESENTATION OF IMPLEMENTATION METHODS [Fig.l] schematically and symbolically represents a control and neutralization interface 10 of a power supply line of electrical equipment 11 arranged on board an aircraft. The control and neutralization interface 10 is named control interface in the remainder of this description. The terms "power supply line control interface" here designate a set of means made available to an operator to determine the electrical state of an electrical power supply line of a piece of equipment and to neutralize this electrical power supply line, if necessary, so as to ensure the safety of the operator. According to the exemplary embodiment illustrated in [Fig.l], the electrical power supply line of the electrical equipment 11 comprises a first electrically conductive element 12a and a second electrically conductive element 12b. The two electrically conductive elements 12a and 12b pass through an electrical insulation box 11i made of an electrically insulating material. The insulation box 11i has a closed or more precisely almost closed volume insofar as one or more openings are cleverly arranged therein, which openings are described below.The insulating housing 1 11 is preferably arranged against the electrical equipment 11 and in physical contact with it. The electrically conductive elements 12a and 12b are respectively surrounded by insulating sheaths 12a' and 12b' at least for their parts (or portions) which are both external to the insulating housing 1 11 and external to the electrically powered electrical equipment 11, and outside any other electrically insulated equipment. The terminal parts of the electrically conductive elements 12a and 12b are connected on the one hand to electrical circuits internal to the electrical equipment 11 and on the other hand to a source of electrical energy, or to an intermediate power element arranged between a source of electrical energy and the electrical insulating housing 1 11 (for example a power switch). These elements are not illustrated here in detail to the extent that they are not useful for understanding the invention.Cleverly, calibrated openings 13a and 13b are arranged in the insulation box 11', respectively positioned opposite the electrically conductive elements 12a and 12b, to respectively face surfaces 14a and 14b of the electrically conductive elements 12a and 12b, devoid of electrical insulation, and internal to the insulation box 11i.

[0016] The term "calibrated openings" herein refers to openings whose shape and dimensions imply an orientation of measurement probes configured to enter into mechanical and electrical contact with the electrically conductive elements 12a and 12b and intended to carry out an electrical measurement of the electrical state of the conductive elements 12a and 12b. Thus, for example, the calibrated openings 13a and 13b are bores with a diameter not exceeding 12.5 mm so as to each allow a probe of generally cylindrical shape to pass through and to prevent any tactile contact of an operator with one of the electrically conductive elements 12a and 12b. A measurement via the insertion of probes into the calibrated openings 13a and 13b makes it possible to avoid contact of the operator with an element presenting a dangerous electrical potential in view of carrying out a control or maintenance operation on board, in relation to the electrical supply line of the equipment 11. According to one embodiment, sealed plugs are arranged in the calibrated openings 13a and 13b outside of any measurement or control operation. According to one embodiment, these plugs (not shown in [Fig.l]) are attached to the electrical insulation box 11i, so as to prevent their loss. Advantageously again, the electrically conductive elements 12a and 12b are respectively electrically connected to external connection pads 16a and 16b each arranged on one face of the insulation box 11i. The external connection pads 16a and 16b are also called connection pads 16a and 16b here.The connection between an electrically conductive element and a connection pad is made via electrical connections internal to the insulation box 111 implemented by cables or conductive elements of the “bus bar” type, as examples. The connection pads 16a and 16b advantageously make it possible to neutralize the electrical potential of each of the electrically conductive elements 16a and 16b by operating an electrical link (connection) between each of the pads and a reference equipotential. For example, the electrical power supply line mainly consisting of the electrically conductive elements 12a and 12b can be neutralized by connecting the connection pads 16a and 16b to a reference ground of an electrical system of the aircraft. Cleverly, the control interface 10 comprises two removable neutralization conductors 18a and 18b connected to a reference equipotential 10g.According to the illustrated example, the equipotential 10g is a reference mass of the aircraft allowing the neutralization of the electrically conductive elements 12a and 12b at a zero electrical potential. According to one embodiment, each of the removable neutralization conductors 18a and 18b ends with a terminal connector. Thus, the removable neutralization conductor 18a ends with a terminal connector 18a' configured to make an electrical connection with the connection pad 16a or with the connection pad 16b and the removable neutralization conductor 18b ends with a terminal connector 18b' configured to make an electrical connection with the connection pad 16a or with the connection pad 16b.A "removable" character of a neutralization conductor here describes the fact that the terminal connector of this neutralization conductor can be connected and disconnected at will from the connection pad which is complementary to it on the control interface, depending on whether the electrically conductive element connected to the connection pad must be neutralized or not. According to an embodiment, a single conductor comprises two terminal connection elements to operate a simultaneous connection of the electrically conductive elements 12a and 12b to the reference equipotential 10g, via the connection pads 16a and 16b. The removable neutralization conductors 18a and 18b are . preferably electrically insulated to prevent direct contact with an operator. According to one embodiment, the terminal connectors 18a' and 18b' are also provided with an insulating covering (a sheath, for example) to prevent any tactile contact with an element whose electrical potential may present a danger. According to one embodiment, the connection pads 16a and 16b are configured to each receive an electrically insulating cap, plug or cover in the absence of connection of a removable conductive element intended to electrically neutralize the electrically conductive element which is electrically connected thereto.

[0017] The arrangement of the control interface 10 advantageously makes it possible to carry out control and neutralization operations in a reduced space, simply and quickly, prior to any subsequent control and / or maintenance intervention on the electrical supply line and / or the electrical equipment 11.

[0018] [Fig.2] illustrates an aircraft 1 comprising at least one control interface of an electrical power supply line such as the control interface 10.

[0019] The invention is not limited to the embodiments described above and may relate to variants. For example, the control interface 10 may comprise three or four electrically conductive elements, or more. Furthermore, the insulation housing 11 may be a subassembly of the electrical equipment 11. According to further variants, the calibrated openings 13a and 13b may have various shapes and orientations defined to facilitate measurement operations in a confined environment.

[0020] [Fig. 3] is a diagram illustrating steps of a method for controlling and disabling an electrical line on board an aircraft by means of a control and disabling interface similar to the control and disabling interface 10. According to the example method described below, the interface used for executing the method is the control and disabling interface 10. A step S0 is an initial step at the end of which a maintenance operator (or an aircraft systems installer) is normally equipped and ready to carry out operations for controlling and disabling an aircraft electrical power supply line via the control and disabling interface 10.In a step SI, the operator uses a measuring probe of calibrated shape complementary to the shape of the calibrated opening 13a and inserts it into the calibrated opening 13a until the end of the measuring probe makes it possible to establish electrical contact with a part 14a devoid of electrical insulation of the electrically conductive element 12a. The probe is further connected to a measuring device or equipment, which measuring device is further connected to the reference equipotential 10g, so as to make it possible to measure the electrical potential of the electrically conductive element 12a, and to verify, if necessary, that this electrical potential is harmless in terms of protection of the . people. In a step S2, the operator inserts a discharge probe into the calibrated opening 13a, after having removed the measuring probe previously used for the measurement. The discharge probe also has a shape complementary to the shape of the calibrated opening, so as to be correctly oriented to establish electrical contact with a part 14a devoid of electrical insulation of the electrically conductive element 12a. The discharge probe is also connected to the reference equipotential 10g so as to evacuate any electrical charges via this equipotential, if necessary.Finally, during a step S3, the operator removes the protective cap or plug from the connection pad 16a and connects to the connection pad 16a the terminal element 18a' of the removable neutralization conductor 18a (or the terminal element 18b' of the neutralization conductor 18b) which is also connected to the reference equipotential 10g, which has by definition and by design a neutral potential. Thus, it is advantageously possible to easily check and neutralize, and in a reduced space on board an aircraft, the conductive element 12a. The method is exactly similar for checking and neutralizing the electrically conductive element 12b, however using the calibrated opening 13b and the connection pad 16b.It should be noted that it is possible to discharge any residual electrical charges, during step S2 by directly connecting the conductive elements 12a and 12b by means of two discharge probes respectively inserted in the calibrated openings 13a and 13b and connected to each other, and preferably in addition, connected to the reference equipotential 10g.

[0021] According to one embodiment, one or more measuring and discharging probes are included in a control and neutralization system comprising the control and neutralization interface 10. According to one embodiment, the control and neutralization interface is configured to satisfy the protection conditions as defined in relation to the IP2X protection index, i.e. by presenting a level 2 of protection with respect to solid elements.

[0022] According to one embodiment, such a control and neutralization system comprising one or more measuring and discharging probes further comprises an electrical potential measuring device configured to measure an electrical potential greater than the maximum electrical potential for which the electrical supply line is intended.

Claims

Claims

1.

2. Control interface (10) of an electrical supply line of a aircraft, the electrical power supply line being configured to supply electrical equipment (11) of said aircraft, said control interface (10) comprising an electrical insulation box (1 li) crossed by at least one electrically conductive element (12a) of the electrical power supply line, connected to said equipment (11) and provided with an electrically insulating sheath (12a') outside said equipment (11) and said electrical insulation box (1 li) and having a surface free of electrical insulation (14a) inside said electrical insulation box (lli), said control interface (10) being characterized in that: a calibrated opening (13a) is arranged in said electrical insulation housing (1 li) opposite said surface devoid of electrical insulation (14a) of each of the electrically conductive elements (12a), each of the electrically conductive elements (12a) is connected to a connection pad (16a) arranged on an outer surface of said electrical insulation housing (1 li), and, a removable neutralization conductor (18a), connected to a reference equipotential (10g) and having a terminal connector (18a') configured for connection to a connection pad of said electrical insulation housing (lli) is available for connection to said pad. The control interface (10) of claim 1, wherein two electrically conductive elements (12a, 12b) pass through said electrically insulating housing (11), which housing (111) comprises two calibrated openings (13a, 13b) respectively arranged opposite two surfaces devoid of electrical insulation (14a, 14b) each arranged on one of said two electrically conductive elements (12a, 12b), two connection pads (16a, 16b) respectively connected to the two electrically conductive elements (12a, 12b) and two removable neutralization conductors (18a, 18b) connected to a reference equipotential (10g) and each comprising a terminal connector (18a', 18b') each configured for connection to one of said pads (16a, 16b).

3. Control interface (10) according to one of claims 1 and 2, in which a calibrated opening (13a, 13b) is a bore with a diameter less than or equal to 12.5 mm and whose central longitudinal axis passes through said surface devoid of electrical insulation (14a, 14b) of said electrical element (12a, 12b) opposite which it is arranged in said electrical insulation housing (lli).

4. Control interface (10) according to one of claims 1 to 3, in which each connection pad (16a, 16b) and each neutralizing conductor (18a, 18b) is electrically isolated to prevent any tactile contact with an element electrically connected to an electrically conductive element (12a, 12b).

5. Control interface (10) according to one of claims 1 to 4, arranged on a face of electrical equipment (11) of an aircraft.

6. Electrical system of an aircraft comprising electrical equipment (11) and a control interface (10) according to one of claims 1 to c

7. J. Electrical system of an aircraft according to claim 6, further comprising at least one measuring or discharge probe arranged to be inserted into a calibrated opening (13a) of said interface and establish electrical contact with said surface devoid of electrical insulation arranged opposite said opening.

8. Aircraft (1) comprising an electrical system according to one of claims 6 and 7 or a control interface (10) according to one of claims 1 to 5.

9. Method for controlling and neutralizing an electrical power supply line of an aircraft, the method being executed via a control interface (10) according to one of claims 1 to 5 and comprising: - carrying out a measurement (SI) of electrical potential of at least one electrically conductive element (12a, 12b), relative to the reference equipotential (10g), by inserting a measurement probe into the calibrated opening (13a, 13b) arranged opposite said surface (14a, 14b) devoid of electrical insulation of said electrically conductive element (12a, 12b), - carrying out a discharge (S2) of electrical potential of at least said electrically conductive element (12a, 12b) by inserting a discharge probe into the calibrated opening (13a, 13b) arranged opposite said surface (14a, 14b) devoid of electrical insulation of said electrically conductive element (12a, 12b), and, carrying out a neutralization (S3) of at least said electrically conductive element (12a, 12b) of the electrical supply line by connecting a terminal connector of a removable neutralization conductor to the connection pad of the control interface connected to this electrically conductive element of the supply line.

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