Ground-based power supply system suitable for an aircraft operating on a taxiway at an airport facility

Abstract

Ground power supply system adapted for an aircraft operating on a taxiway of an airport facility. The invention relates to a ground power supply system for an aircraft operating on the ground along a guidance line (30), comprising: on the ground, at least one first power supply terminal (34) at zero potential parallel to the guidance line (30) and a plurality of second power supply terminals (36), at non-zero potential, regularly distributed on at least one second power supply line parallel to the guidance line (30), integral with the aircraft, at least one support configured to occupy at least one state in which it is positioned close to the ground, at least one first contact zone (44) and at least one second contact zone (46), integral with the support and configured to cooperate with the first and second power supply terminals (34, 36),as well as at least one cover configured to cover all first and second contact areas (44, 46). Figure 3,

Description

Title of the invention: Ground-based power supply system adapted for an aircraft operating on a taxiway of an airport facility

[0001] The present application relates to a ground power supply system adapted for an aircraft travelling on a taxiway of an airport facility.

[0002] Before takeoff or after landing, an aircraft moves on the ground by taxiing along a taxiway of an airport facility between its parking area and the runway. To move on the ground, the aircraft uses the thrust generated by its propulsion systems and / or by its auxiliary power unit (APU).

[0003] This solution is not optimal because the aircraft consumes energy in the form of fuel stored in its tanks to move on the ground, which leads to increased fuel consumption and the aircraft's onboard mass.

[0004] In the field of land vehicles, a tram can be electrically powered from the ground. In this case, the railway track comprises two running rails to guide the tram and a power rail located equidistant from the running rails and configured to supply the tram with electricity. During operation, a power supply circuit is configured to bring the power rail to an electrical potential of several hundred volts, on the order of 750 V. In parallel, at least one running rail is connected to the ground of the power supply circuit.

[0005] To avoid any risk of electrocution, the power supply rail is segmented into sections that are only energized when they are completely covered by the tram. The different sections are insulated from each other and their power supply is controlled by control boxes that detect the presence of the tram.

[0006] In addition, the tram includes several runners which are in contact by friction with the power rail. The return current is carried out via at least one of the tram's wheels in contact with one of the running rails connected to the ground of the electrical power supply circuit.

[0007] Taking into account the electrical energy to be transferred and the speed of movement of the tram, each section has a length of about ten meters and the tram includes several runners in contact with the power rail.

[0008] This solution, suitable for a tram, is not suitable for an aircraft. Indeed, when moving on the ground, an aircraft is not guided. Therefore, an A skid attached to the aircraft cannot reliably and precisely follow a ground-mounted power rail. Furthermore, unlike a tram, an aircraft's fuselage is raised off the ground, making it impossible to cover a significant section of the power rail to prevent electrocution. Finally, in the case of an airport structure, there is no running rail to provide electrical feedback.

[0009] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0010] To this end, the invention relates to a ground-based electrical power supply system for an aircraft travelling on at least one taxiway having at least one guidance line, said ground-based electrical power supply system comprising at least one ground part which includes at least one first power supply terminal at a first zero potential, positioned on the ground along at least one first parallel power supply line or coinciding with the guidance line, as well as at least one on-board part attached to the aircraft and configured to cooperate in operation with the ground part.

[0011] According to the invention, the ground portion comprises a plurality of second power supply terminals, at a second non-zero potential at at least one given instant, regularly distributed along at least one second parallel power supply line or one that coincides with the guide line. In addition, the on-board portion comprises at least one support configured to occupy at least one state in which it is positioned near the ground, at least one first contact zone and at least one second contact zone attached to said at least one support, and at least one cover configured to cover all the first and second contact zones, the first and second contact zones being configured so that they are, at any given instant, respectively in contact with at least one first power supply terminal and at least one second power supply terminal of the ground portion of the ground-based power supply system.

[0012] This solution makes it possible to obtain a safe power supply system limiting the risks of electrocution and a compact on-board part limiting the impact of the power supply system on the on-board mass.

[0013] According to another feature, the first and second power supply terminals are positioned alternately on at least one power supply line.

[0014] According to another feature, the first and second power supply terminals are positioned along two separate power supply lines.

[0015] According to another feature, at least one power line is coincident with the guide line.

[0016] According to another feature, the onboard part includes at least one support, to which the first and second contact zones are connected, connected to the aircraft and movable between a deployed state in which the first and second contact zones rub against the first and second power terminals and a folded state in which the first and second contact zones are moved away from the ground.

[0017] According to another feature, the support includes at least one pad which has a lower face oriented towards the ground when the support is in the deployed state, the lower face of each pad being split into first and second contact zones.

[0018] According to another feature, the support includes an alignment axis substantially parallel to the operating guide line and several pads spaced apart from each other along the alignment axis.

[0019] According to another feature, the support comprises at least one pair of first and second pads, each of which has a lower face oriented towards the ground when the support is in the deployed state, the lower face of each first pad forming a first contact zone, the lower face of each second pad forming a second contact zone.

[0020] According to another feature, the first and second pads are aligned along an alignment axis, spaced apart from each other so that each of the first and second pads is in contact only with a first or second power supply terminal and is never simultaneously in contact with a pair of first and second power supply terminals.

[0021] According to one variant, the first(s) and second(s) skates are positioned symmetrically with respect to the alignment axis.

[0022] According to another variant, each first skate is offset on one side relative to the alignment axis, each second skate being offset on a second side, opposite to the first side, relative to the alignment axis.

[0023] According to another feature, the embedded part includes first and second supports, the first support supporting first(s) and / or second(s) pads configured to cooperate with a first power line, the second support supporting first(s) and / or second(s) pads configured to cooperate with a second power line.

[0024] According to another feature, each second power terminal is configured to occupy an activated state in which the second power terminal has a non-zero second potential and a deactivated state in which the second power terminal has a zero potential, the ground power supply system comprising at least one control configured to control the activated / deactivated state of each second power terminal according to the position of the onboard part.

[0025] According to another feature, the ground power supply system includes a guidance device configured to correct, if necessary, the position of the first and second contact zones relative to the first and second power supply terminals.

[0026] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0027] [Fig. 1] is a side view of an aircraft operating on an airport facility illustrating one embodiment of the invention,

[0028] [Fig.2] is a schematic top view representation of an installation airport illustrating one embodiment of the invention,

[0029] [Fig.3] is a top view of a ground-level portion of a ground-level power supply system illustrating a first embodiment of the invention,

[0030] [Fig.4] is a front view of an embedded part of a power supply system electric ground, adapted to the ground part visible in [Fig.3], illustrating a first embodiment of the invention at a first instant on part (A) and at a second instant on part (B),

[0031] [Fig.5] is a top view of a ground-level portion of a ground-level power supply system illustrating a second embodiment of the invention,

[0032] [Fig.6] is a front view of an on-board part of a ground-based power supply system, adapted to the ground-based part visible in [Fig.5],

[0033] [Fig.7] is a top view of a ground-level portion of a power supply system electric ground connection illustrating a third embodiment of the invention.

[0034] [Fig.8] is a front view of an on-board part of a ground-based power supply system, adapted to the ground-based part visible in [Fig.7],

[0035] [Fig.9] is a top view of a ground-level portion of a power supply system electric ground connection illustrating a fourth embodiment of the invention.

[0036] [Fig. 10] is a front view of an on-board part of a ground power supply system, adapted to the ground part visible in [Fig.9].

[0037] According to an embodiment visible in [Fig.1], an aircraft 10 comprises a fuselage 12 extending between a front tip 12.1 and a rear tip 12.2, wings 14 connected to the fuselage 12, a front landing gear 16 connected to the fuselage 12 and positioned at or near the front tip 12.1, and two main landing gears 18 connected to the fuselage 12 or to the wings 14.

[0038] Each front or main landing gear 16, 18 is movable between a deployed position, as illustrated in [Fig.1], and a retracted position in a landing gear box (not shown).

[0039] The front or main landing gear 16, 18 is in the deployed position when the aircraft 10 is moving on the ground S and in the retracted position when the aircraft is in flight, particularly during the cruise phase.

[0040] According to one embodiment, a front or main landing gear 16, 18 comprises a leg 20 extending between first and second ends, a joint connecting the first end of the leg 20 and the fuselage 12 and a wheel support positioned at the second end of the leg 20 and supporting at least one wheel.

[0041] According to one configuration, the aircraft 10 includes at least one electric motor for rotating at least one wheel of at least one front or main landing gear 16, 18. This motor may be integrated into the wheel or remote from it.

[0042] The front or main landing gear 16, 18 are not further described as they may be identical to those of the prior art.

[0043] As illustrated in [Fig.2], an airport facility 22 comprises at least one parking area 24, at least one runway 26 and at least one taxiway 28 connecting the parking area 24 and the runway 26.

[0044] Prior to takeoff, the aircraft 10 follows a first guidance line 30 on a first taxiway 28 from the parking area 24 to the runway 26. After landing, the aircraft 10 follows a second guidance line 30' on a second taxiway 28' connecting the runway 26 and the parking area 24. The airport facility 22 may include a single taxiway 28 and the aircraft may follow a single guidance line 30 between the parking area 24 and the runway 26.

[0045] Each guide line 30 is positioned in the center of the traffic lane 28, equidistant from the edges of the traffic lane 28.

[0046] According to one embodiment, each guide line 30 is a colored marking on the ground, such as a white or yellow painted stripe applied to the ground S, for example. To give an order of magnitude, the guide line 30 has a width of approximately 15 cm.

[0047] Regardless of the embodiment, the airport infrastructure 22 includes at least one taxiway 28, 28' having at least one guidance line 30, 30' configured to guide the aircraft 10.

[0048] For the remainder of the description, a longitudinal axis X is substantially parallel to the guide line 30 at a given point.

[0049] A ground-based power supply system adapted to the aircraft 10 comprises at least one ground portion which includes at least one power supply circuit 32 positioned on or in the ground S. This power supply circuit 32 comprises at least one first power supply terminal 34 positioned on the ground along the guidance line 30 and connected to a first portion 32.1 of the power supply circuit 32 at a first potential, as well as a plurality of second power supply terminals 36 positioned on the ground S, regularly spaced along the guidance line 30, and connected to a second portion 32.2 of the power supply circuit 32 at a second potential (different from the first potential). In one configuration, the first potential is equal to 0 and corresponds to ground, the second potential being non-zero and greater than 100 V.

[0050] According to embodiments visible in Figures 3 and 5, the ground part of the ground power supply system comprises a plurality of first power supply terminals 24 regularly distributed along the guide line 30 and connected to the first circuit part 32.1 at the first potential.

[0051] The first and second power supply terminals 34, 36 each have a contact surface on their upper part, the contact surfaces of the different first and second power supply terminals 34, 36 being substantially identical. In one arrangement, the contact surface of each of the first and second power supply terminals 34, 36 is substantially rectangular and has a first dimension DI between 5 and 20 cm, substantially equal to the width of the guide line 30, and a second dimension D2 less than 50 cm, on the order of 35 cm. The contact surfaces are spaced by a third minimum distance D3 less than the second dimension D2, on the order of 10 cm.

[0052] According to a first embodiment visible in [Fig.3], the first and second power supply terminals 34, 36 are positioned on or opposite the guide line 30, the first and second power supply terminals 34, 36 being positioned alternately, each of the first power supply terminals 34 being positioned between two second power supply terminals 36, each of the second power supply terminals 36 being positioned between two first power supply terminals 34.

[0053] According to a second embodiment shown in [Fig. 5], the first and second power supply terminals 34, 36 are positioned on at least one first power supply line 38 parallel to and spaced from the guide line 30, the first and second power supply terminals 34, 36 being positioned alternately. The first power supply line 38 is spaced a fourth distance D4 between 5 and 20 cm, on the order of 10 cm. According to a preferred arrangement, the ground portion of the ground power supply system comprises first and second power supply lines 38, 38' positioned symmetrically on either side of the guide line 30, each of them being spaced from the guide line. 30 of a fourth distance D4 between 5 and 20 cm, of the order of 10 cm, the first and second supply terminals 34, 36 being positioned alternately on each of the first and second supply lines 38, 38'.

[0054] According to third and fourth embodiments shown in Figures 7 and 9, the ground portion of the ground power supply system comprises a single first continuous power supply terminal 34 extending along the guide line 30. Since this first power supply terminal 34 is at zero potential, it does not need to be protected to prevent the risk of electrocution. According to these embodiments, the first power supply terminal 34 extends along a first power supply line 40, and the second power supply terminals 36 are distributed along a second power supply line 40' spaced apart from the first power supply line 40.

[0055] According to a third embodiment visible in [Fig.7], the first and second lines 40, 40' are positioned on either side of the guide line 30.

[0056] According to a fourth embodiment visible in [Fig.9], the guide line 30 separates the ground into first and second zones Z1, Z2. The first and second supply lines 40, 40' are respectively positioned in the first and second zones Z1, Z2.

[0057] Of course, the invention is not limited to these embodiments for the ground-based portion of the ground-based power supply system. Regardless of the embodiment, the ground-based portion of the ground-based power supply system comprises at least one first power supply terminal 34 at a first zero potential, positioned on the ground along at least one first power supply line 38, 40 parallel to or coinciding with the guide line 301, and a plurality of second power supply terminals 36 regularly distributed along at least one second power supply line 38', 40' parallel to or coinciding with the guide line 30 at a second non-zero potential at at least one given instant. The first and second power supply lines 38, 38', 40, 40' may coincide as illustrated in Figures 3 and 5 or be distinct as illustrated in Figures 7 and 9.At least one of the first and second feed lines 38, 38', 40, 40' can be confused with the guide line 30.

[0058] The ground power supply system comprises, at the aircraft 10, at least one onboard component configured to cooperate in operation with the ground component, which includes at least one onboard circuit 42. The latter comprises at least one first contact zone 44 integral with the aircraft and connected to a first potential, and at least one second contact zone 46 integral with the aircraft and connected to a second potential different from the first potential. In one embodiment, the onboard circuit 42 comprises at least one electrical component 48 having first and second terminals 48.1, 48.2 to which the first and second contact zones 44, 46 are respectively connected.

[0059] The onboard part of the ground power supply system includes at least one support 50, to which the first and second contact zones 44, 46 are connected, connected to the aircraft 10 and configured to move on the ground S or near S so that the first and second contact zones 44, 46 are respectively in contact against at least one first power terminal 34 and at least one second power terminal 36. Thus, when the aircraft 10 moves on the taxiway 28, 28' following the guidance line 30, 30', the first and second contact zones 44, 46 rub against the first and second power terminals 34, 36.

[0060] According to one embodiment, the support 50 is mobile between a deployed state in which the first and second contact zones 44, 46 rub against the first and second power supply terminals 34, 36 and a folded state in which the first and second contact zones 44, 46 are away from the ground S, the support 50 being folded into a cavity so as not to generate aerodynamic disturbances, in particular when the aircraft 10 is in flight.

[0061] According to one configuration, the support 50 is integral with the leg 20 of a front or main landing gear 16, 18.

[0062] According to another configuration shown in [Fig. 1], the aircraft 10 comprises at least one mast 52 extending between first and second ends, at least one joint 52.1 connecting the first end of the mast 52 and the fuselage 12, and at least one actuator configured to rotate the mast 52 between first and second positions corresponding respectively to the deployed and retracted states. At least one support 50 is connected to the second end of the mast 52,

[0063] According to a first configuration visible in figures 4, 6 and 10, the support 50 comprises at least one pair of first and second pads 54, 56, respectively for each of the first and second contact zones 44, 46, which each have a lower face oriented towards the ground when the support 50 is in the deployed state, the lower face of each first pad 54 forming a first contact zone 44, the lower face of each second pad 56 forming a second contact zone 46.

[0064] According to a second configuration visible in [Fig.8], the support 50 includes at least one pad 58 which has a lower face oriented towards the ground when the support 50 is in the deployed state, the lower face of each pad 58 being split into first and second contact zones 44, 46. According to this configuration, the same pad 58 includes first and second contact zones 44, 46.

[0065] According to a first embodiment, visible in [Fig. 4], adapted to operate with the ground part of the ground power supply system visible in [Fig. 3], the aircraft circuit 42 comprises several first and second pads 54, 56 having first and second contact zones 44, 46 respectively. The first and second pads 54, 56 are aligned along an alignment axis AA and spaced apart so that each of the first and second pads 54, 56 is in contact with only one or second power supply terminal 34, 36 and is never in simultaneous contact with a pair of first and second power supply terminals 34, 36. The support 50 is a straight support oriented along the alignment axis AA to which the first and second pads 54, 56 are connected. According to one embodiment, these first and second pads 54, 56 are positioned symmetrically with respect to the alignment axis AA.

[0066] Alternatively, as illustrated in [Fig.6], each first skate 54 is offset on one side relative to the alignment axis AA and each second skate 56 is offset on a second side (opposite to the first side) relative to the alignment axis AA.

[0067] In operation, the support 50 is moved so that the alignment axis AA is substantially parallel to the guide line 30 (or to the longitudinal axis X) and vertically below the guide line 30.

[0068] The first and second skates 54, 56 have substantially identical lower surfaces. According to one embodiment, the lower surface of each of the first and second skates 54, 56 is substantially rectangular and has a first dimension D1' (oriented along a direction perpendicular to the alignment axis AA) between 5 and 20 cm, substantially equal to 10 cm, as well as a second dimension D2' (oriented along a direction parallel to the alignment axis AA) between 5 and 20 cm, substantially equal to 10 cm. The first and second skates 54, 56 are spaced apart by a spacing distance DE (measured along a direction parallel to the alignment axis AA) greater than the third dimension D3 which corresponds to the distance separating the first and second power supply terminals 34, 36. The spacing distance DE measures approximately 15 cm.

[0069] According to one arrangement, the support 50 supports three first(s) and second(s) pads 54, 56. According to this arrangement, the latter have a front edge B1 and a rear edge B2 of the front edge B1 spaced at a distance of approximately 60 cm.

[0070] According to a second embodiment, visible in [Fig. 6], adapted to operate with the ground portion of the ground power supply system, visible in [Fig. 5], unlike the first embodiment, the first and second pads 54, 56 are not positioned symmetrically with respect to the alignment axis AA. According to this second embodiment, each first pad 54 is offset on one side with respect to the alignment axis AA, and each second pad 56 is offset on a second side (opposite the first side) with respect to the alignment axis AA.

[0071] According to this second embodiment, the first and second skates 54, 56 have dimensions substantially identical to those of the first and second skates of the first embodiment. In one arrangement, the support 50 supports three first skates 54 and two second skates 56, these first and second skates 54, 56 having a front edge B1 and a rear edge B2 spaced from the front edge B1 by a distance of approximately 90 cm.

[0072] According to a first variant shown in bold in [Fig. 6], the on-board part of the ground power supply system comprises a single support 50, the first pads 54 being configured to rub against the first and second terminals of the first power supply line 38, the second pads 56 being configured to rub against the first and second terminals of the second power supply line 38'. According to this first variant, in operation, the support 50 is configured to move so that its alignment axis AA is parallel to the guide line 30 (or the longitudinal axis X) and vertically aligned with the guide line 30.

[0073] According to a second variant visible in bold and dashed lines on [Fig.6], the onboard part of the ground power supply system comprises first and second supports 50, 50', the first and second pads 54, 56 of the first support 50 being configured to rub with the first and second power supply terminals 34, 36 of the first power supply line 38, the first and second pads 54, 56 of the second support 50' being configured to rub with the first and second power supply terminals 34, 36 of the second power supply line 38'.According to this second variant, in operation, the first support 50 is configured to move so that its alignment axis AA is parallel to the guide line 30 (or to the longitudinal axis X) and approximately vertically above the first feed line 38 and the second support 50' is configured to move so that its alignment axis AA is parallel to the guide line 30 (or to the longitudinal axis X) and approximately vertically above the second feed line 38'.

[0074] According to a third embodiment, visible in [Fig. 8], adapted to operate with the ground-based part of the ground power supply system visible in [Fig. 7], the on-board part of the ground power supply system comprises several pads 58 connected to a support 50 oriented along an alignment axis AA, the pads 58 being spaced from each other along the alignment axis AA. These pads 58 are substantially identical and each has, on their undersides, first and second contact zones 44, 46, the first contact zones 44 being located on one side of the alignment axis AA, the second contact zones 46 being located on a second side (opposite the first side) of the alignment axis AA.

[0075] According to this third embodiment, the skates 58 have a front edge B1 and a rear edge B2 spaced from the front edge B1 by a distance of approximately 30 cm.

[0076] In operation, the support 50 moves so that its alignment axis AA is parallel to the guide line 30 (or to the longitudinal axis X) and vertically below the guide line 30. Thus, the first contact areas 44 of the various pads 58 are located vertically below the first power line 40 and in contact with the first power terminal 34 and the second contact areas 46 of the various pads 58 are located vertically below the second power line 40' and in contact with the second power terminals 36.

[0077] According to a fourth embodiment, visible in [Fig.1], adapted to operate with the ground part of the ground power supply system visible in [Fig.9], the on-board part of the ground power supply system comprises a first support 50 supporting first pads 54 each having a first contact zone 44, a second support 50' supporting second pads 56 each having a second contact zone 46 and at least one cross member 60 connecting the first and second supports 50, 50';the first and second supports 50, 50' having respectively first and second alignment axes AA, AA' parallel to each other and spaced at a fixed distance so that in operation, the first and second alignment axes AA, AA' are parallel to the guide line 30 (or to the longitudinal axis X) and positioned approximately vertically above respectively the first and second power lines 40, 40' so that the first contact areas 44 of the first pads 54 are in contact with the first power terminal 34 and the second contact areas 46 of the second pads 56 are in contact with the second power terminals 36. ;

[0078] Of course, the invention is not limited to the embodiments described above. Regardless of the embodiment, the on-board part of a ground power supply system comprises at least one support 50 configured to occupy at least one state in which it is positioned near the ground S, at least one first contact zone 44 attached to said at least one support 50 and connected to a first potential, and at least one second contact zone 46 attached to said at least one support 50 and connected to a second potential different from the first potential, the first and second contact zones 44, 46 being configured so that they are, at a given instant, respectively in contact with at least one first power supply terminal 34 and at least one second power supply terminal 36 of the ground part of the ground power supply system.Regardless of the method of implementation, the support 50 has a length, measured according to a . direction parallel to the longitudinal axis X, less than 1m, which helps to limit the increase in the mass carried.

[0079] The on-board part of the ground power supply system includes at least one cover 62 (visible in Figures 1 and 6), separate from the pads 54, 56, configured to cover all the contact areas 44, 46 so that when the on-board part moves above the ground S, the cover 62 isolates the contact areas 44, 46 and the power supply terminals 34, 36 in contact with said pads 54, 56. Thus, the risks of electrocution are limited.

[0080] According to one embodiment, the hood 62 comprises a wall substantially parallel to the floor S when the support 50 is in the deployed state, approximately rectangular, and optionally a skirt around the perimeter of the wall, reducing the spacing between the hood 62 and the floor S.

[0081] The hood 62 has a length, measured along a direction parallel to the guide line 30 (or to the longitudinal axis X), of less than 1m. Thus, the hood 62 is relatively compact and allows the on-board mass to not increase too much.

[0082] According to one configuration, each second power supply terminal 36 is configured to occupy an activated state in which the second power supply terminal 36 has a non-zero potential and a deactivated state in which the second power supply terminal 36 has a zero potential. In addition, the ground power supply system includes at least one control configured to control the activated / deactivated state of each second power supply terminal 36 based on the position of the onboard part and to switch it to the activated or deactivated state based on the position of the support 50, as well as a system for determining the position of the support 50.Thus, at any given moment, knowing the position of the support 50, the control switches to the activated state or maintains in the activated state each second power supply terminal 36 positioned under the first and second contact zones 44, 46 connected to the support 50 and switches to the deactivated state or maintains in the deactivated state all other second power supply terminals 36. Thus, as the support 50 moves, the second power supply terminals 36 are activated and then deactivated.

[0083] According to one configuration, the ground power supply system includes a guidance device 64 configured to correct, if necessary, the position of the first and second contact zones 44, 46 relative to the first and second power supply terminals 34, 36. According to an embodiment shown in [Fig. 4], the guidance device 64 includes at least one sensor, preferably two sensors 64.1, 64.2, configured to detect the guidance line 30, and a processing unit 64.3 configured to, based on the information acquired by each sensor 64.1, 64.2, correct the position of the aircraft 10 and / or each support 50 so that the first and second contact zones 44, 46 are correctly positioned with respect to the first and second supply terminals 34, 36. This guide system 64 can be used with the different embodiments previously described of the first and second contact zones 44, 46.

[0084] According to a first variant, each support 50 cannot move in a direction perpendicular to the alignment axis AA. In this case, if the position of the support 50 needs to be corrected, the trajectory of the aircraft 30 is modified.

[0085] According to a second embodiment, the ground power supply system comprises, for each support 50, at least one joint connecting the support 50 and the aircraft 10, configured to allow the support 50 to translate at least in a transverse direction perpendicular to the alignment axis AA, and at least one actuator configured to move the support 50 in the transverse direction. In this case, if the position of the support 50 needs to be corrected, the trajectory of the aircraft 30 is modified and / or the position of the support 50 relative to the aircraft in the transverse direction is modified.

[0086] In operation, when the aircraft 10 moves on the ground S, the first and second contact zones 44, 46 collect an electric current that can vary depending on the surface area in contact between the first and second contact zones 44, 46 and the first and second power supply terminals 34, 36 as the aircraft 10 moves, or if the first and second power supply terminals 34, 36 are positioned alternately on the same power supply line 38, 38', 40, 40'. According to one embodiment, the ground power supply system includes a processing system 66 for regulating the collected electric current.

Claims

Demands

1. Ground power supply system for an aircraft (10) operating on at least one taxiway (28, 28') having at least one guidance line (30, 30'), said ground power supply system comprising at least one ground portion having at least one first power supply terminal (34) at a first zero potential, positioned on the ground along at least one first power supply line (38, 40) parallel to or coinciding with the guidance line (30), and at least one onboard portion integral with the aircraft (10) and configured to cooperate in operation with the ground portion; characterized in that the ground portion comprises a plurality of second power supply terminals (36), at a second non-zero potential at at least one given instant, regularly distributed along at least one second power supply line (38',40') parallel to or coinciding with the guide line (30) and in that the on-board part comprises at least one support (50) configured to occupy at least one state in which it is positioned close to the ground (S), at least one first contact zone (44) and at least one second contact zone (46) integral with said at least one support (50) and at least one cover (62) configured to cover all the first and second contact zones (44, 46), the first and second contact zones (44, 46) being configured so that they are, at any given time, respectively in contact with at least one first power supply terminal (34) and at least one second power supply terminal (36) of the ground part of the ground power supply system.

2. Ground power supply system according to the preceding claim, characterized in that the first and second power supply terminals (34, 36) are positioned alternately on at least one power supply line (38, 38').

3. Ground power supply system according to the preceding claim, characterized in that the first and second power supply terminals (34, 36) are positioned along two separate power supply lines (38, 38', 40, 40').

4. Ground power supply system according to any one of the preceding claims, characterized in that at least one line the supply line (38, 38', 40, 40') is confused with the guide line (30).

5. Ground power supply system according to any one of the preceding claims, characterized in that the on-board part comprises at least one support (50), to which the first and second contact zones (44, 46) are connected, connected to the aircraft (10) and movable between a deployed state in which the first and second contact zones (44, 46) rub against the first and second power supply terminals (34, 36) and a folded state in which the first and second contact zones (44, 46) are away from the ground (S).

6. Ground power supply system according to the preceding claim, characterized in that the support (50) comprises at least one pad (58) which has a lower face oriented towards the ground when the support (50) is in the deployed state, the lower face of each pad (58) being split into first and second contact zones (44, 46).

7. Ground power supply system according to the preceding claim, characterized in that the support (50) comprises an alignment axis (AA) substantially parallel to the guide line (30) in operation and several pads (58) spaced apart from each other along the alignment axis (AA).

8. Ground power supply system according to claim 5, characterized in that the support (50) comprises at least one pair of first and second pads (54, 56) each having a lower face oriented towards the ground when the support (50) is in the deployed state, the lower face of each first pad (54) forming a first contact zone (44), the lower face of each second pad (56) forming a second contact zone (46).

9. Ground power supply system according to the preceding claim, characterized in that the first and second pads (54, 56) are aligned along an alignment axis (AA), spaced apart from each other so that each of the first and second pads (54, 56) is in contact with only one first or second power supply terminal (34, 36) and is never simultaneously in contact with a pair of first and second power supply terminals (34, 36).

10. Ground power supply system according to the preceding claim, characterized in that the first(s) and second(s) pads (54, 56) are positioned symmetrically with respect to the alignment axis (AA).

11. Ground power supply system according to claim 9, characterized in that each first pad (54) is offset on a first side with respect to the alignment axis (AA) and in that each second pad (56) is offset on a second side, opposite to the first side, with respect to the alignment axis (AA).

12. Ground power supply system according to claim 8, characterized in that the onboard part comprises first and second supports (50, 50'), the first support (50) supporting first and / or second pads (54, 56) configured to cooperate with a first power line (38, 40), the second support (50') supporting first and / or second pads (54, 56) configured to cooperate with a second power line (38', 40').

13. Ground power supply system according to any one of the preceding claims, characterized in that each second power supply terminal (36) is configured to occupy an activated state in which the second power supply terminal (36) has the second non-zero potential and a deactivated state in which the second power supply terminal (36) has a zero potential and in that the ground power supply system includes at least one control configured to control the activated / deactivated state of each second power supply terminal (36) according to the position of the onboard part.

14. Ground power supply system according to any one of the preceding claims, characterized in that the ground power supply system includes a guidance device (64) configured to correct, if necessary, the position of the first and second contact zones (44, 46) with respect to the first and second power supply terminals (34, 36).

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