DISPOSITIVO PARA O REABASTECIMENTO EM VOO DE UMA AERONAVE

Abstract

The invention relates to an in-flight refueling device (100), in particular for a refueling aircraft (118), comprising a pipe (102) intended for transferring a fluid, comprising - a first end (102a) able to be connected to a fluid source (106), and - a second end (102b) equipped with an in-flight refueling connection (108), characterized in that it further comprises a light system (114) arranged along at least part of the pipe (102) and comprising at least one series of radiation sources (120) distributed along that part of the pipe (102).

Description

1 / 11 “DEVICE FOR IN-FLIGHT REFUELING OF AN AIRCRAFT” TECHNICAL FIELD OF THE INVENTION

[0001] The present invention relates to the general field of aeronautics. More specifically, it relates to a device for in-flight refueling of an aircraft and an aircraft comprising this in-flight refueling device. TECHNICAL BACKGROUND

[0002] The technical background comprises documents US-A12005 / 017130, US-A-5,539,624, DE-A1-10 2016 118302, CN-U-206 719 564, US-A12005 / 145751 and US-A2-2019 / 154173.

[0003] During a flight, it is known that an aircraft is refueled by transferring at least one fluid, such as fuel, to it.

[0004] This is the case, for example, when an aircraft cannot or should not land in an area over which it is flying. The aircraft must then be refueled in flight. This is particularly the case when the volume of fuel on board reaches a lower threshold value.

[0005] During this refueling, as shown schematically in figure 1, a first aircraft 14, also called a tanker 14 or refueling aircraft 14, is equipped with a device for in-flight refueling to which a second aircraft 22, also called a receiver 22 or refueling aircraft 22, is connected.

[0006] The in-flight refueling device comprises a tube 10 configured to transfer fluid, unrolled from the first aircraft to the second aircraft, which is located downstream of the first aircraft, in the direction of flight, and which is to be refueled.

[0007] Tube 10 can be unrolled or extended from a downstream end of a fuselage 12 of the refueling aircraft 14, as shown in figure 1, or from a wing of the refueling aircraft 14.

[0008] Alternatively, tube 10 can be extended from a Petition 870250085468, dated 09 / 22 / 2025, page 10 / 27 2 / 11 transporter, also called a nacelle, installed on the ventral point of an aircraft, in particular a combat aircraft, or from a transporter installed under the wing of an aircraft, in particular a refueling aircraft or a combat aircraft.

[0009] The tube 10, suitable for transferring fluid, comprises a first end 10a, connected to a fluid source 16 and comprising, for example, a reservoir and a pump, and a second end 10b, opposite the first end 10a and comprising a first connector 18.

[0010] The first connector 18 is configured to provide a fluidic connection with a second connector 20 that can cooperate in a complementary way. The second connector 20 is loaded, in particular by a rod, from the aircraft to be refueled 22. This type of connection is well known to those skilled in the art.

[0011] The first connector 18 comprises, for example, a pressure limiting member 24 and a truncated conical basket 26. For this purpose, the connector 18 may comprise a valve that allows the pressure at the outlet of the first connector 18 to be adjusted to the prevailing limit in the middle.

[0012] The truncated conical basket 26 helps to center and guide the second connector 20 inside the first connector 18. For this purpose, the second connector 20 has a pointed shape that cooperates with the pressure-limiting member 24 of the first connector 18.

[0013] The truncated conical basket 26 is also shaped to facilitate centering of the first connector 18 in the airflow.

[0014] Tube 10 is unrolled by means of a tube extension system 10 located inside the refueling aircraft 14 or inside the refueling aircraft transporter 14.

[0015] When refueling aircraft 14 takes off, tube 10 is coiled. During a refueling operation, the uncoiling of tube 10 is controlled so as to uncoil a sufficient length of tube 10, for example, over several tens of meters, in particular a length between Petition 870250085468, dated 09 / 22 / 2025, page 11 / 27 3 / 11 meters and 30 meters, so that the first connector 18 approaches the second aircraft 22 and can be connected to the second connector 20 of the second aircraft 22.

[0016] Tube 10 is relatively flexible and is likely to move and shift when unrolled and subjected to disturbances downstream of the first aircraft 14 or to turbulence.

[0017] If the movements of tube 10 are too large and uncontrolled, they may come into contact with refueling aircraft 14 and / or the second aircraft 22.

[0018] When tube 10 is connected to the second connector 20 on the aircraft 22 to be refueled and when the aircraft 22 to be refueled is refueled, waves are generated along tube 10 and result in ripples in the tube.

[0019] The characteristics of such waves are that they are liable to damage the second connector 20, in particular the rod, of the aircraft to be refueled 22.

[0020] Such waves may cause the second connector 20 to break, requiring an emergency landing of the aircraft to be refueled 22, after this damage.

[0021] Depending on flight conditions, the movements and undulations of tube 10 may not be perceptible to the refueling aircraft pilot 22 or may be difficult to perceive, particularly during a night flight.

[0022] A tube 10, configured to transfer a fluid during refueling, may comprise white annular stripes extending around the tube 10 and visible to the pilot of the aircraft 22 being refueled. Such annular stripes allow the pilot to see the length of the extended tube 10, but do not allow him to visualize a waveform or recognize its propagation speed.

[0023] When the pilot of the aircraft to be refueled 22 detects movement or a ripple in the tube 10, he can disconnect the second connector 20 from the tube 10 and free himself from a risky situation. Petition 870250085468, dated 09 / 22 / 2025, page 12 / 27 4 / 11

[0024] However, during night flight or in reduced visibility, for example, in the presence of fog and / or clouds, the pilot of the aircraft to be refueled 22 is unable to see the type of movement or undulation using the current technique.

[0025] In addition, the truncated cone basket 26 carried by the tube 10 can be fitted with a light system configured to make it easier for the pilot of the aircraft 22 to be refueled to locate it.

[0026] However, when the second connector 20 of the aircraft to be refueled 22 is connected to the pressure limiting member 24, the truncated cone basket 26 no longer follows the movements and undulations of the tube 10.

[0027] The aircraft to be refueled 22 may include a spotlight. However, such a spotlight is generally not powerful enough to illuminate several tens of meters and may lose effectiveness depending on weather conditions.

[0028] The purpose of the present invention is to provide a solution to at least some of the problems of the prior art, which is simple, effective and economical. SUMMARY OF THE INVENTION

[0029] The invention relates to a device for in-flight refueling, in particular for a refueling aircraft, comprising a tube configured for the transfer of a fluid, said tube comprising:

[0030] a first end suitable for connection to a fluid source and

[0031] a second end fitted with an in-flight refueling connector,

[0032] The in-flight refueling device also comprises a lighting system arranged along at least part of the tube, capable of being connected to a power source, in particular located on the first end of the tube and comprising at least one series of radiation sources distributed along the tube part, in particular the radiation sources are uniformly distributed along the tube part.

[0033] The invention proposes equipping the tube with a light system, that is, a system capable of emitting radiation, in particular light. The light system is Petition 870250085468, dated 09 / 22 / 2025, p. 13 / 27 5 / 11 distributed along part or all of the length of the tube. When the tube is subjected to movements or undulations, the light system follows these movements and undulations. It is then possible to see these movements with the naked eye, even in semi-darkness or poor visibility, particularly at night.

[0034] The lighting system can be connected to a power source that supplies it with the energy needed to emit radiation. The power source is chosen according to the nature of the lighting system.

[0035] The in-flight refueling device according to the invention may also have one or more of the following features, taken alone or in combination with each other:

[0036] The radiation sources are separated by a distance between 20 cm and 100 cm, preferably between 40 cm and 60 cm and, for example, 50 cm;

[0037] The radiation source is chosen from a light-emitting diode, a light-emitting fiber, an optical fiber and / or a piezoelectric strip;

[0038] The light system comprises at least two series of radiation sources, respectively distributed over at least two lines extending along the tube and angularly spaced from each other around the tube;

[0039] The light system comprises two lines of radiation sources located 180° apart from each other around the tube;

[0040] The light system comprises three lines of radiation sources separated from each other by an angle between 60° and 120°;

[0041] The light system comprises four lines of radiation sources separated at an angle between 60° and 90°;

[0042] The radiation sources are distributed in a straight line along the tube;

[0043] The radiation sources are distributed in a line wound helically around the tube;

[0044] The light system is fixed to an outer periphery of the tube;

[0045] The light system is integrated into the tube;

[0046] The pipe is multilayered; Petition 870250085468, dated 09 / 22 / 2025, page 14 / 27 6 / 11

[0047] The tube comprises at least one metal layer, one elastomer layer and one textile layer;

[0048] The lighting system is integrated, for example, by weaving into the textile layer; this allows for improved durability and visibility of the lighting system;

[0049] The energy source is a light and / or electrical energy source; and / or

[0050] The lighting system is configured to allow radiation in the visible, infrared and / or ultraviolet range.

[0051] The invention also relates to an assembly comprising an in-flight refueling device as described above and a fluid source, such as fuel, capable of being connected to the first end of the tube.

[0052] The present invention also relates to an aircraft comprising an in-flight refueling device and / or an assembly as described above. BRIEF DESCRIPTION OF THE FIGURES

[0053] Additional features and advantages of the invention will become apparent from the following detailed description, for the understanding of which reference is made to the accompanying drawings, in which:

[0054] Figure 1 is a schematic view of a refueling aircraft equipped with a device for in-flight refueling of an aircraft to be refueled;

[0055] Figure 2 is a schematic view of an embodiment of an in-flight refueling device according to the invention;

[0056] Figure 3 is a schematic view of another embodiment of an in-flight refueling device according to the invention;

[0057] Figure 4 is another schematic view of the in-flight refueling device in Figure 3 being subjected to a wave;

[0058] Figure 5 is a schematic view of a variant embodiment of an in-flight refueling device according to the invention; and

[0059] Figure 6 is a schematic view of another variant embodiment of an in-flight refueling device according to the invention. DETAILED DESCRIPTION OF THE INVENTION Petition 870250085468, dated 09 / 22 / 2025, p. 15 / 27 7 / 11

[0060] Figure 2 illustrates one embodiment of a device for in-flight refueling 100 according to the invention.

[0061] More specifically, figure 2 is a perspective view of the in-flight refueling device embodiment 100 according to the invention.

[0062] The in-flight refueling device 100 comprises a tube 102 configured to allow fluid transfer.

[0063] Tube 102 comprises a first end 102a configured to be connected to a fluid source 106 and a second end 102b fitted with an in-flight refueling connector 108.

[0064] For example, pipe 102 has a length L of around ten meters or several tens of meters, in particular a length between 10 m and 30 m.

[0065] Tube 102 is preferably a multilayer tube comprising, for example, a metal layer, an elastomer chamber and a textile layer.

[0066] The fluid source 106 may comprise at least one fluid reservoir and one pump. The fluid is, for example, fuel.

[0067] The in-flight refueling connector 108 is of the type described above in relation to figure 1 and comprises, for example, a pressure limiting member 110 and a truncated conical basket 112.

[0068] Tube 102 can be associated with an extension system 104 configured to allow tube 102 to be extended, in particular by winding and unwinding tube 102.

[0069] The 104 extension system for the 102 tube is capable of winding the 102 tube around a geometric axis and unwinding it to a desired length to ensure in-flight refueling. The 104 extension system is, for example, of the winch type.

[0070] The extension system 104 may comprise a part for attachment to a refueling aircraft structure 118. Such an attachment part may be, for example, a mounting flange, not shown in the figures. Petition 870250085468, dated 09 / 22 / 2025, page 16 / 27 8 / 11

[0071] The in-flight refueling device 100 also comprises a radiation system 114, in particular a light system 114, arranged along at least part of the tube 102. The radiation system 114 can be connected to a power source 116.

[0072] The power source 116 may be located on the side of the first end 102a of the tube 102, in particular located on the aircraft. Alternatively, the power source 116 may be located at the level of the in-flight refueling connector 108 or the extension system 104.

[0073] The light system 114 comprises at least one radiation source 120, in particular a series of radiation sources 120, in particular a series of light points 120.

[0074] The light system 114 extends, for example, over a length L1, in tube 102, for example, several meters, in particular over more than a third, in particular over more than half, more specifically over more than three-quarters of a total length L of tube 102.

[0075] Radiation sources 120 can be distributed uniformly along tube 102 or a part of tube 102. More particularly, radiation sources 120 can be regularly spaced apart by a distance H, in particular between 20 cm and 100 cm, preferably between 40 cm and 60 cm, and for example, 50 cm.

[0076] The radiation source 120 can be selected from a light-emitting diode (LED), a light fiber, an optical fiber and / or a piezoelectric strip.

[0077] Radiation source 120 is configured to emit light in the visible, infrared and / or ultraviolet range.

[0078] If a light-emitting diode or a light fiber is used, the radiation source 120 can be connected to the power source 116 by at least one electrical conductor 122, such as a wire. The electrical conductor 122 can extend along the tube 102. In this configuration, the power source 116 is an electrical power source. Petition 870250085468, dated 09 / 22 / 2025, page 17 / 27 9 / 11

[0079] If an optical fiber is used, the optical fiber can extend along the tube 102. The optical fiber can be connected to the power source 116. In this configuration, the power source 116 is a light power source.

[0080] If a piezoelectric strip is used, when tube 102 is deformed, the piezoelectric strip also deforms and generates a voltage used as a power source 116.

[0081] Tube 102 may also comprise white annular stripes 124, as mentioned above.

[0082] Figure 3 is a schematic view of another embodiment of the in-flight refueling device 100 according to the invention. More particularly, Figure 3 shows another embodiment of the in-flight refueling device 100 in which the power source 116 is located in the refueling aircraft 118. For example, in such a configuration, the power source 116 may be located next to or in the extension system 104 of the tube 102.

[0083] The energy source 116 may be an electric generator, of the dynamoelectric machine type, configured to generate electrical energy when the tube 192 is extended, in particular when it is unrolled and rolled up.

[0084] For example, tube 102 is unwound over a drum that can rotate around the aforementioned geometric axis, the electric generator comprising, for example, a rotor rotated by the drum.

[0085] Figure 4 is another schematic view of the in-flight refueling device 100 of Figure 3 being subjected to a wave. In particular, Figure 4 illustrates the general principle of the invention.

[0086] During an in-flight refueling, tube 102 was extended over several meters. A wave is likely to be generated and propagate along the tube. This could be, for example, as a result of the in-flight refueling connector 108 impacting the second connector 20, in particular the rod, of the aircraft being refueled.

[0087] The wave can take the form of a ripple in tube 102, which can have a period P between 2 m and 4 m and a maximum amplitude B between 50 cm and 150 cm. Petition 870250085468, dated 09 / 22 / 2025, page 18 / 27 10 / 11

[0088] The wave may cause the second connector 20, in particular the rod, to break, requiring an emergency landing of the aircraft to be refueled after such damage.

[0089] The presence of radiation sources 120 at regular intervals allows the pilot of the aircraft being refueled to visualize the overall shape of the tube 102. As a result, the pilot of the aircraft being refueled can see the formation of the ripples.

[0090] If the detected ripples are too large, the pilot of the aircraft to be refueled may then decide to disconnect the second connector 20, in particular the rod, from the aircraft to be refueled from tube 102.

[0091] The presence of radiation sources 120 allows the pilot of the aircraft being refueled to recognize the shape and speed of the wave, even during a night flight, which is particularly advantageous.

[0092] In one embodiment, the radiation sources 120 are distributed along a line, which may be a straight line parallel to a longitudinal geometric axis A of the tube 102.

[0093] Figures 5 and 6 are schematic views of alternative embodiments of the in-flight refueling device 100 according to the invention.

[0094] Radiation sources 120 can be distributed in a line wound helically around the tube 102.

[0095] The light system 112 may comprise two or more series of radiation sources 120, respectively distributed in two or more lines extending along the tube 102.

[0096] The radiation source lines 120 can be spaced angularly from each other or relative to each other around the tube 102.

[0097] In the event that tube 102 or light system 114 comprises two lines L1, L2 of radiation sources 120, the lines L1, L2 may be situated at an angle α of 180° to each other around the tube, that is, diametrically opposite to each other with respect to the longitudinal geometric axis A of tube 102.

[0098] In the event that tube 102 or light system 114 comprises three Petition 870250085468, dated 09 / 22 / 2025, page 19 / 27 11 / 11 radiation source lines 120, these lines can be separated by an angle α between 60° and 120°.

[0099] In the case where tube 102 or light system 114 comprises four lines of radiation sources 120 separated from each other by an angle α between 60° and 90°.

[0100] The light system 114 can be adapted and fixed, for example by gluing, to an outer periphery of the tube 102.

[0101] Alternatively, the light system 114 can be integrated into the tube 102. In the above-mentioned case where the tube 102 is of the multilayer type, the light system 114 can be integrated into a textile layer, for example by weaving.

[0102] The in-flight refueling device 100 according to the invention may, in particular, be arranged:

[0103] Inside refueling aircraft 118;

[0104] At one downstream end of a fuselage of refueling aircraft 118;

[0105] Under a wing of refueling aircraft 118 and / or

[0106] On a conveyor, also called a nacelle, installed a. At a belly point of the refueling aircraft 118 and / or b. Under the wing of refueling aircraft 118.

[0107] The invention improves the safety of refueling missions, particularly at night, by allowing the pilot of the aircraft being refueled to perform an emergency disconnection if deemed necessary. With current technology, the pilot of the aircraft being refueled cannot predict the generation of a wave and is entirely dependent on the overall behavior of the in-flight refueling device. Petition 870250085468, dated 09 / 22 / 2025, page 20 / 27

Claims

1 / 2 CLAIMS 1. Device for in-flight refueling (100), in particular for a refueling aircraft, comprising: - a tube (102) configured to transfer a fluid, said tube (102) comprising a first end (102a) suitable for connection to a fluid source (106) and a second end (102b) fitted with an in-flight refueling connector (108), and - a light system (114), disposed along at least part of the tube (102), capable of being connected to a power source and comprising at least one series of radiation sources (120) distributed along part of the tube (102), characterized in that the tube (102) is of the multilayer type and comprises at least one metal layer, one elastomer layer and one textile layer and in which the light system is integrated into the textile layer.

2. In-flight refueling device (100), according to claim 1, characterized in that the radiation sources (120) are separated by a distance (H) between 20 cm and 100 cm, preferably between 40 cm and 60 cm and, for example, 50 cm.

3. In-flight refueling device (100), according to any one of claims 1 or 2, characterized in that the radiation source (120) is chosen from a light-emitting diode, a light-emitting fiber, an optical fiber and / or a piezoelectric strip.

4. Device for in-flight refueling (100), according to any one of claims 1 to 3, characterized in that the light system (114) comprises at least two series of radiation sources (120), respectively distributed over at least two lines (L1, L2) extending along the tube (102) and angularly spaced from each other around the tube (102).

5. In-flight refueling device (100), according to claim 4, characterized in that the light system (114) comprises two lines of radiation sources (120) located 180° apart around the tube. Petition 870250085468, dated 22 / 09 / 2025, page 21 / 27 2 / 2 6. In-flight refueling device (100), according to claim 4, characterized in that the light system (114) comprises three lines of radiation sources (120) separated from each other by an angle between 60° and 120°.

7. In-flight refueling device (100), according to claim 4, characterized in that the light system (114) comprises four lines of radiation sources (120) separated at an angle between 60° and 90°.

8. Device for in-flight refueling (100), according to any one of claims 1 to 7, characterized in that the radiation sources (120) are distributed in a straight line along the tube (102).

9. Device for in-flight refueling (100), according to any one of claims 1 to 7, characterized in that the radiation sources (120) are distributed in a line helically wound around the tube (102).

10. Device for in-flight refueling (100), according to any one of claims 1 to 9, characterized in that the light system (114) is fixed to an outer periphery of the tube (102).

11. Device for in-flight refueling (100), according to any one of claims 1 to 9, characterized in that the light system (114) is integrated into the tube (102).

12. In-flight refueling device (100), according to claim 11, characterized in that the light system is integrated by weaving into the textile layer.

13. Assembly characterized by comprising an in-flight refueling device (100) as defined in any of claims 1 to 12 and a fluid source (106), such as fuel, capable of being connected to the first end of the tube.

14. Aircraft (14), characterized by comprising an in-flight refueling device (100) as defined in any of claims 1 to 12 and / or an assembly as defined in claim 13. Petition 870250085468, dated 22 / 09 / 2025, page 22 / 27

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