Landing gear for aircraft, aircraft and electric energy transmission system

Abstract

The invention relates to an undercarriage for an aircraft, an aircraft and an electric energy transmission system. The invention relates to a landing gear (1) comprising a leg and a wheel support and two wheels fixed to the leg by means of the wheel support, said wheels being spaced apart from each other such that a space, referred to as an internal volume, is defined between the two wheels, the landing gear comprising an electrical energy receiving device comprising a receiver (4) configured to receive electrical energy transmitted by a transmitter (5), the electrical energy receiving device is movably mounted between a retracted position and a deployed position in which the receiver (4) is arranged outside the internal volume, the electrical energy receiving device comprising an end fixed to the wheel support.

Description

Technical Field

[0001] The present invention relates to landing gear equipped with an electrical power receiving device for moving an aircraft during taxiing. Background Technology

[0002] Before takeoff or after landing, an aircraft moves along the ground by traversing taxiways between its parking area and the takeoff and landing runways within the airport facility. This is called taxiing. During this phase, the aircraft uses thrust generated by its propulsion components.

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

[0004] The purpose of this invention is to overcome these disadvantages, at least in part. Summary of the Invention

[0005] To this end, a landing gear for an aircraft is proposed, comprising legs and wheel supports, and two wheels fixed to the legs by the wheel supports, the wheels being spaced apart from each other such that a space, referred to as an internal volume, is defined between the two wheels. The landing gear includes an electrical energy receiving device comprising an electrical energy receiving element, referred to as a receiver, configured to receive electrical energy emitted by an electrical energy transmitting element, referred to as a transmitter, which is arranged at a distance from the landing gear. The electrical energy receiving device is movably mounted between a retracted position and an extended position, in which the receiver is arranged outside the internal volume. The electrical energy receiving device includes an end fixed to the wheel support.

[0006] By means of the landing gear according to the invention, the electric motor of the aircraft's landing gear can be powered, which makes it possible to avoid the need to use the aircraft's propulsion components and auxiliary power units, and thus makes it possible to reduce the aircraft's onboard mass and fuel consumption, since the aircraft no longer consumes fuel to move along the ground.

[0007] One aspect of the present invention is a landing gear for an aircraft, the landing gear including legs and wheel supports, and two wheels fixed to the legs by the wheel supports, the wheels being spaced apart from each other such that a space called an internal volume is defined between the two wheels. The landing gear includes an electrical power receiving device, which includes an electrical power receiving element called a receiver, the receiver being configured to receive electrical energy emitted by an electrical power transmitting element called a transmitter. The electrical power receiving device includes a structure for holding the receiver. The electrical power receiving device is movably mounted between a retracted position and an extended position. In the retracted position, the electrical power receiving device is arranged in the internal volume, and in the extended position, the receiver is arranged outside the internal volume. The electrical power receiving device includes an end fixed to the wheel support.

[0008] According to another aspect, the power receiving device includes a structure for holding the receiver.

[0009] According to another aspect, the retaining structure includes a fixing component and a component hinged to the fixing component, the fixing component having an electrical energy receiving device fixed to the end of the wheel support.

[0010] On the other hand, the receiver is fixed to the end of the hinged component of the structure.

[0011] On the other hand, the receiver is mounted in a movable manner relative to the hinged parts of the structure.

[0012] According to another aspect, the power receiving device includes an actuator for controlling the receiver.

[0013] According to another aspect, the receiver includes a sensing pad for cooperating with the transmitter in a non-contact manner and / or a contactor for cooperating with the transmitter by contact.

[0014] According to another aspect, the landing gear includes an electric motor configured to control the wheels of the aircraft's landing gear and configured to be supplied with electrical power via a receiver. According to another aspect, the articulated component of this structure includes two parallel arms and at least one connecting arm connecting the parallel arms to each other. According to another aspect, each arm extends between a first end fixed to a fixed component via a hinge and a second end fixed to a receiver via a hinge. According to another aspect, the end of each arm fixed to the receiver defines an arc between a first position corresponding to a minimum angle and a second position corresponding to a maximum angle, the minimum being between 110° and 160°, and the maximum being between 120° and 170°. According to another aspect, the fixed component includes two parallel rods and a component resting on a wheel support, the two parallel rods being fixed to the parallel arms via a hinge, the angle defined by the component and each rod being between a minimum of 90° and a maximum of 90°.

[0015] Another subject of the present invention is an aircraft that includes the aforementioned landing gear.

[0016] Another subject of the present invention is an electrical power transmission system comprising an electrical power transmitter and an aircraft as described above, the electrical power transmitter being configured to supply electrical power to a receiver when the electrical power receiving device is in the deployed position. Attached Figure Description

[0017] Further features, details, and advantages will become apparent by reading the following detailed description and analyzing the accompanying drawings, in which:

[0018] Figure 1 This is a schematic perspective side view of the front portion of an aircraft that can be equipped with landing gear according to the present invention.

[0019] Figure 2 For use in positioning power receiving devices Figure 1 A schematic three-dimensional view of detail II in the image.

[0020] Figure 3 This is a side view of the landing gear according to the invention in the retracted position.

[0021] Figure 4 For the unfolded position Figure 3 A schematic diagram of the landing gear.

[0022] Figure 5 This is a side view of the landing gear in the retracted position, a variation of an embodiment of the present invention.

[0023] Figure 6 For the unfolded position Figure 5 A schematic diagram of the landing gear.

[0024] Figure 7 for Figure 6 A schematic rear view of the landing gear. Detailed Implementation

[0025] The examples and related conditions detailed herein are primarily intended to help the reader understand the principles of the invention, and not to limit its scope to these specific examples and conditions. It will be understood that those skilled in the art will envision various arrangements, which, although not explicitly described or depicted herein, still embody the principles of the invention and are included within its spirit and scope.

[0026] Furthermore, for ease of understanding, the following description illustrates a relatively simplified implementation of the invention. As those skilled in the art will understand, other implementations of the invention may be more complex.

[0027] In some cases, examples of modifications to the invention may also be presented. This is done merely to aid understanding and is not intended to limit the scope of the invention or to impose any restrictions on it. These modifications are not exhaustive, and those skilled in the art can make other modifications while still remaining within the scope of the invention.

[0028] Furthermore, all statements below relating to the principles, aspects, and implementations of the invention, as well as specific examples thereof, are intended to cover both structural and functional equivalents of the invention, whether they are currently known or will be developed in the future.

[0029] To make this description easier to read, an orthogonal reference system (X, Y, Z) has been illustrated in the accompanying drawings. The X direction corresponds to the direction of the aircraft's forward motion, and the Z direction corresponds to the vertical direction. The aircraft is illustrated as being in a glide.

[0030] As from Figures 1 to 7 It is evident that one aspect of the present invention is the landing gear, designated 1 in the accompanying drawings. The landing gear 1 includes an electrical power receiving device, designated 2.

[0031] As in Figure 1 and Figure 2 As can be seen, the landing gear 1 is intended to equip the aircraft A, and another subject of the invention is the aircraft A equipped with the landing gear 1.

[0032] The power receiving device 2 includes a power receiving element, designated 4, referred to as a receiver. The receiver 4 is configured to receive electrical energy transmitted by the power receiving element, referred to as a transmitter 5. The transmitter 5 is distinct from the landing gear 1; the transmitter 5 is not formed as part of the landing gear 1.

[0033] According to a variation of the first embodiment, such as in Figure 3 and Figure 4 As illustrated, receiver 4 takes the form of pad 6, while according to the second variation, as in Figure 5 , Figure 6 and Figure 7 As shown in the diagram, receiver 4 takes the form of a set of contactors 7.

[0034] The pad 6 is designed to transmit electrical energy emitted by the transmitter 5 in a non-contact manner. For example, using induction technology, the transmitter 5, preferably located on the ground S, is configured to generate an electromagnetic field, and the receiver 6 is an electromagnetic induction element configured to generate a current when positioned in the magnetic field generated by the transmitter 5. In this case, the receiver 6 includes at least one coil.

[0035] Each contactor 7 is designed to transmit electrical energy emitted by the transmitter 5 when the contactor 7 contacts the transmitter 5, which may, for example, take the form of a rail located on the ground S.

[0036] As can be seen in the attached diagram, device 2 is movably mounted. Figure 3 and Figure 5 The retraction position shown in the figure is the same as... Figure 4 , Figure 6 and Figure 7 Between the unfolded positions shown in the figure, in the unfolded position, the receiver 4 is arranged to receive energy emitted by the transmitting element 5.

[0037] As can also be clearly seen from the accompanying drawings, the landing gear 1 includes legs 8 fixed to the fuselage F of the aircraft A. When the aircraft A is taxiing, the legs 8 extend approximately orthogonally to the ground S. The landing gear 1 also includes wheel supports 9 extending linearly between two ends 10, 11, each of which supports a wheel 12.

[0038] The volume defined by the space between the two wheels 12 is called the internal volume V.

[0039] Now, let's describe device 2.

[0040] The device 2 includes a support 13 for the receiver 4 that is movably mounted, and a structural element 14 that is fastened to the wheel support 9.

[0041] Even more special, as in Figure 7 As can be seen, the support member 13 has an overall H-shaped form and advantageously includes two parallel arms 15, 16 and at least one connecting arm 17 connecting the parallel arms 15, 16 to each other. Each connecting arm 17 is preferably arranged orthogonally to the parallel arms 15, 16. In the illustrated embodiment, and in a non-limiting manner, the support member 13 includes a single connecting arm 17.

[0042] Each of arms 15 and 16 extends between a first end 18 and a second end 20, the first end 18 being secured to structural element 14 via a hinge 19, such as a pivot connection, and the second end 20 being secured to receiver 4 via a hinge 21, such as a pivot connection.

[0043] As can be seen in the accompanying drawings, structural element 14 is fastened to wheel support 9 by fastening attachment 22 and hinged to support 13.

[0044] In particular, such as in Figure 7As can be seen, structural element 14 includes two parallel rods 24, 25 and a component 23 resting on wheel support 9. The two parallel rods 24, 25 are fixed to the parallel arms 15, 16 of support 13 by hinges 19. Component 23 advantageously includes a straight portion 26 and a curved portion 27 spaced apart from the straight portion 26, which strengthens structural element 14 while increasing mass as little as possible.

[0045] The angle defined by each of component 23 and rods 25 and 26 is called the first hinge angle, which is denoted as α.

[0046] The end of each of the rods 25 and 26 fixed to the support member 13 is defined by an arc between a first position corresponding to the minimum value of angle α and a second position corresponding to the maximum value of angle α. Advantageously, and in a non-limiting manner, the minimum value is less than or equal to 90°, for example between 45° and 90°, for example between 50° and 70°, for example 60°. Advantageously, and in a non-limiting manner, the maximum value is greater than or equal to 90°, for example between 90° and 150°, for example between 110° and 140°, for example 130°.

[0047] The first position corresponds to the folded position of the support member 13 relative to the structural element 14, while the second position corresponds to the extended position of the support member 13 relative to the structural element 14.

[0048] The landing gear 1 advantageously includes means for driving the support between the folded position and the extended position, such as an actuator, like a hydraulic or pneumatic actuation cylinder not shown in the drawings.

[0049] The angle defined by each of arms 15 and 16 and receiver 4 is called the second hinge angle, which is denoted as β.

[0050] The end 21 of each of arms 15 and 16, fixed to receiver 4, describes an arc between a first position corresponding to the minimum value of angle β and a second position corresponding to the maximum value of angle β. Advantageously, and in a non-limiting manner, the minimum value is between 110° and 160°, for example, 130°, and the maximum value is between 120° and 170°, for example, 160°.

[0051] The first position corresponds to the folded position of the receiver 4 relative to the support member 13, while the second position corresponds to the extended position of the receiver 4 relative to the support member 13.

[0052] The landing gear 1 advantageously includes means for driving the support between the folded and extended positions, such as an actuator, denoted as 28 in the figures, like a hydraulic or pneumatic actuator. The actuator 28 can also press the contactor 7 against the ground S to transmit electrical energy via friction between the transmitter 5 and the contactor 7. The actuator 28 includes a cylinder 28-1 fixed to the wheel support 9, as described in detail below, and a rigid rod 28-2 fixed to the bracket 30 at one end.

[0053] When the receiver 4 is in the folded position relative to the support member 13 and the support member 13 is in the folded position relative to the structural element 14, the power receiving device 2 is in the retracted position.

[0054] When the receiver 4 is in the extended position relative to the support member 13 and the support member 13 is in the extended position relative to the structural element 14, the power receiving device 2 is in the unfolded position.

[0055] In the retracted position, receiver 4 is housed within the internal volume V until it is potentially tangent to wheel 12. In the extended position, receiver 4 is positioned outside the internal volume V, against the ground S, and as explained, this allows receiver 4 to cooperate with transmitter 5 to transmit electrical energy from transmitter 5.

[0056] As can be seen in the accompanying drawings, device 2 includes a bracket 30 supporting receiver 4. The bracket 30 includes a platform 31 on which the hinges 21 of the parallel arms 15, 16 are mounted. The bracket 30... Figure 3 and Figure 4 The first variant of the model has wheels 32, or as shown in the example. Figures 5 to 7 As shown in the second embodiment variant illustrated, wheel 32 is absent.

[0057] Advantageously, the landing gear 1 includes an electric motor (not shown) and potentially also includes a unit for distributing electrical energy received by the receiver 4. The landing gear also includes two cables 33 or electrical wiring harnesses, in the illustrated embodiment, for transmitting electrical energy to the aircraft. The electrical energy received by the receiver 4 can potentially be transmitted via this unit to the electric motor to control the movement of the landing gear wheels 12. The invention is not limited to this configuration, and the electrical energy received by the system 1 can be transmitted to an electric motor disposed externally on the landing gear 1.

[0058] The operation of landing gear 1 when it is equipped on aircraft A will now be described.

[0059] During flight, landing gear 1 is in a stationary position within the compartment of aircraft A, and device 2 is in a retracted position. In this position, device 2 adds a small amount of mass to aircraft A and folds the system between the wheels within volume V, making it unnecessary to adjust the geometry of the landing gear hatches or their aerodynamic shape.

[0060] During the landing phase, landing gear 1 is removed from the compartment, and device 2 remains in the retracted position so that device 2 does not affect the movement of wheel 12.

[0061] During gliding, device 2 is driven, for example by a control unit, to be in an extended position: support 13 unfolds, changing from a folded position to an extended position. Then, actuator 28 pushes platform 31 against the ground S, and this ensures either a constant distance between pad 6 and the ground (first variant) or continuous contact between contactor 7 and the ground (second variant).

[0062] Once the device 2 is in the deployed position, the device 2 can receive electrical energy from the transmitter 5 in a non-contact manner or by contact, as described above.

[0063] Conversely, when the aircraft is in the takeoff position, device 2 retracts into its internal volume V.

[0064] Therefore, with the aid of device 2, landing gear 1 constitutes a device for making the aircraft's movement during taxiing not only more environmentally friendly but also quieter. Specifically, with the aid of device 2, the aircraft no longer consumes fuel during taxiing and reduces NO emissions. X and CO X The emission of toxic gases of this type.

[0065] Those skilled in the art can modify and improve the above-described implementations of the present invention. In particular, the described embodiments and variations can be combined, provided they are incompatible. The above description is illustrative by way of example and not limitation. Therefore, the scope of the present invention is limited only by the scope of the following claims.

Claims

1. Landing gear for an aircraft (A) comprising a leg and a wheel support and two wheels fixed to the leg by means of the wheel support, the wheels being spaced apart from each other so that a space, called internal volume, is delimited between the two wheels, the landing gear comprising an electric energy receiving device (2) comprising an electric energy receiving element, called receiver (4), configured to receive electric energy emitted by an electric energy emitting element, called emitter (5), the electric energy receiving device (2) being movably mounted between a retracted position and a deployed position, in which the receiver (4) is arranged outside the internal volume (V), the electric energy receiving device (2) comprising an end fixed to the wheel support.

2. The landing gear of claim 1, wherein, The electric energy receiving device (2) comprises a structure for holding the receiver (4).

3. The landing gear of claim 2, wherein, The structure comprises a fixed part (14) having the end of the electric energy receiving device (2) fixed to the wheel support and a part (13) hinged on the fixed part (14).

4. The landing gear of claim 3, wherein, The receiver (4) is fixed to an end of the hinged part (13) of the structure.

5. The landing gear of claim 4, wherein, The receiver is movably mounted with respect to the hinged part (13) of the structure.

6. The landing gear according to any of the preceding claims 1 to 5, wherein, The electric energy receiving device (2) comprises an actuator (28) for controlling the receiver (4).

7. The landing gear according to any of the preceding claims 1 to 5, wherein, The receiver (4) comprises an inductive pad for cooperating in a contactless manner with the emitter (5) and / or a contactor for cooperating by contact with the emitter (5).

8. Landing gear according to any one of the preceding claims 1 to 5, comprising an electric motor configured to control the wheels of the landing gear of the aircraft and to be supplied with electric energy via the receiver (4).

9. Aircraft comprising a landing gear according to any one of the claims 1 to 8.

10. Electric energy transmission system comprising an electric energy emitter configured to supply the receiver (4) with electric energy when the electric energy receiving device (2) is in the deployed position and an aircraft according to claim 9.

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