Device for in-flight fueling of aircraft

Abstract

The invention relates to an in-flight refueling device (100), in particular for a refueling aircraft (118), comprising a conduit (102) intended to convey a fluid, comprising:-a first end (102a) connectable to a fluid source (106), and-a second end (102b) equipped with an in-flight refueling connector (108), characterized in that the in-flight refueling device further comprises an illumination system (114) arranged along at least a portion of the duct (102) and comprising at least one series of radiation sources (120) distributed along a portion of the duct (102).

Description

Technical Field

[0001] This invention relates to the general field of aviation. More specifically, this invention relates to an in-flight refueling device for an aircraft, and an aircraft including such an in-flight refueling device. Background Technology

[0002] Background technologies include documents US-A1-2005 / 017130, US-A-5,539,624, DE-A1-10 2016118302, CN-U-206 719 564, US-A1-2005 / 145751 and US-A2-2019 / 154173.

[0003] During flight, it is known to refuel an aircraft by delivering at least one fluid (e.g., fuel) to the aircraft.

[0004] This is the case, for example, when an aircraft cannot or is not permitted to land in the area it is flying over. In this situation, the aircraft must refuel in flight. This is especially true when the volume of onboard fuel reaches a low threshold.

[0005] During this refueling period, such as Figure 1 As illustrated, the first aircraft 14 (also known as a tanker 14 or a refueling aircraft 14) is equipped with an in-flight refueling device, and the second aircraft 22 (also known as a receiver 22 or an aircraft to be refueled 22) is connected to the in-flight refueling device.

[0006] The in-flight refueling device includes a conduit 10 configured to transport fluid from a first aircraft to a second aircraft located downstream of the first aircraft in the flight direction and to be refueled.

[0007] Pipe 10 can be unwound or deployed from the downstream end of the fuselage 12 of the refueling aircraft 14 (e.g.) Figure 1 (as shown), or it can unwind or unfold from the wings of the refueling aircraft 14.

[0008] Alternatively, the pipe 10 can be deployed from a carrier (also called a cabin) mounted on the ventral side of the aircraft (especially a combat aircraft), or from a carrier mounted under the wing of the aircraft (especially a refueling aircraft or a combat aircraft).

[0009] The conduit 10, which is suitable for conveying fluid, includes a first end 10a and a second end 10b. The first end 10a is connected to a fluid source 16 and includes, for example, a reservoir and a pump. The second end 10b is opposite to the first end 10a and includes a first connector 18.

[0010] The first connector 18 is configured to provide a fluid connection with the second connector 20, which can cooperate in a complementary manner. The second connector 20 is carried in particular by a boom from the aircraft 22 to be refueled. This type of connection is well known to those skilled in the art.

[0011] The first connector 18 includes, for example, a pressure limiting member 24 and a truncated conical basket 26. For this purpose, the connector 18 may include a valve that allows the pressure at the outlet of the first connector 18 to be set to a limit value commonly found in the medium.

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

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

[0014] The system deploys the pipe 10 by means of the pipe 10 located inside the refueling aircraft 14 or inside the carrier of the refueling aircraft 14 to unwind the pipe 10.

[0015] When the refueling aircraft 14 takes off, the pipe 10 is entangled. During the refueling operation, the unwinding of the pipe 10 is controlled to unwind a sufficient length (e.g., tens of meters, especially between 15 and 30 meters) of the pipe 10 so that the first connector 18 is close to the second aircraft 22 and can be connected to the second connector 20 of the second aircraft 22.

[0016] Pipe 10 is relatively flexible and may move and shift when it unwinds and is subjected to disturbances or turbulence downstream of the first aircraft 14.

[0017] If the movement of pipe 10 is too large and uncontrolled, the pipe may come into contact with refueling aircraft 14 and / or second aircraft 22.

[0018] When pipe 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 pipe 10 and cause fluctuations in the pipe.

[0019] The characteristic of this wave is that it is prone to damaging the second connector 20 of the aircraft 22 that is to be refueled, especially the boom.

[0020] Such a wave could cause the second connector 20 to break, making the aircraft 22, which needs to be refueled after such damage, make an emergency landing.

[0021] Depending on flight conditions, especially during nighttime flights, the pilot of the refueling aircraft 22 may not be able to detect or has difficulty detecting the movement and fluctuations of the pipe 10.

[0022] The conduit 10, configured to deliver fluid during refueling, may include a white annular band extending around the conduit 10 and visible to the pilot of the aircraft 22 being refueled. This annular band allows the pilot to see the length of the deployed conduit 10, but not to see the waveform or understand its propagation speed.

[0023] When the pilot of the aircraft 22 awaiting refueling detects movement or fluctuation in the pipe 10, he can disconnect the second connector 20 from the pipe 10 and evacuate himself from the dangerous situation.

[0024] However, when flying at night or in low visibility conditions, such as in the presence of fog and / or clouds, the pilot of aircraft 22 awaiting refueling cannot use current technology to see the type of movement or fluctuation.

[0025] In addition, the truncated conical basket 26 carried by the pipe 10 may be equipped with a lighting system configured to make it easier for the pilot of the aircraft 22 awaiting refueling to locate the pipe.

[0026] However, when the second connector 20 of the aircraft 22 awaiting refueling is connected to the pressure limiting member 24, the truncated conical basket 26 no longer follows the movement and fluctuation of the pipe 10.

[0027] The aircraft 22 awaiting refueling may include headlights. However, this type of headlight is typically insufficient to illuminate more than a few dozen meters and may become ineffective depending on weather conditions.

[0028] The purpose of this invention is to provide a simple, effective, and economical solution to at least some of the problems in the prior art. Summary of the Invention

[0029] This invention relates to an in-flight refueling device, particularly for refueling aircraft, comprising a conduit configured to deliver fluid, the conduit including:

[0030] - Suitable for connection to the first end of a fluid source, and

[0031] - Equipped with a second end of an in-flight refueling connector

[0032] The in-flight refueling device also includes a lighting system arranged along at least a portion of the pipe, the lighting system being connectable to an energy source, specifically located on one side of a first end of the pipe, and the lighting system including at least a series of radiation sources distributed along a portion of the pipe, particularly, the radiation sources being uniformly distributed along a portion of the pipe.

[0033] This invention proposes equipping pipelines with a lighting system, i.e., a system capable of emitting radiation (especially light). The lighting system is distributed along part or all of the length of the pipeline. When the pipeline experiences movement or fluctuation, the lighting system follows this movement or fluctuation. Therefore, even in semi-darkness or poor visibility, especially at night, this movement can be seen with the naked eye.

[0034] The lighting system can be connected to an energy source, which supplies the energy required for the lighting system to emit radiation. The energy source is selected based on 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, either individually or in combination:

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

[0037] - The radiation source is selected from light-emitting diodes, light-emitting fibers, optical fibers and / or piezoelectric strips;

[0038] - The lighting system includes at least two series of radiation sources, which are distributed along at least two lines that extend along the duct and are angularly spaced from each other around the duct;

[0039] - The lighting system consists of two lines of radiation source, which are positioned 180° apart around the duct;

[0040] - The lighting system consists of three lines of radiation source, which are spaced apart from each other at an angle between 60° and 120°;

[0041] - The lighting system consists of four lines of radiation source, which are spaced apart at an angle between 60° and 90°;

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

[0043] - The radiation sources are distributed along the lines that spiral around the pipe;

[0044] - The lighting system is attached to the outer perimeter of the pipe;

[0045] - The lighting system is integrated into the piping;

[0046] -The piping is multi-layered;

[0047] - The pipe includes at least one metal layer, an elastomer layer and a fabric layer;

[0048] - For example, integrating the lighting system into the fabric layer through weaving makes it possible to improve the durability and visibility of the lighting system;

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

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

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

[0052] The present invention also relates to an aircraft comprising, as described above, an in-flight refueling device and / or components. Attached Figure Description

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

[0054] -[ Figure 1 ] Figure 1 This is a schematic diagram of a refueling aircraft, which is equipped with an in-flight refueling device for aircraft awaiting refueling.

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

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

[0057] -[ Figure 4 ] Figure 4 yes Figure 3 Another schematic diagram of a refueling device during flight that experiences fluctuations;

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

[0059] -[ Figure 6 ] Figure 6 This is a schematic diagram of another variant embodiment of the in-flight refueling device according to the present invention. Detailed Implementation

[0060] Figure 2 An embodiment of the in-flight refueling device 100 according to the present invention is shown.

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

[0062] The in-flight refueling device 100 includes a conduit 102 configured to facilitate fluid transport.

[0063] The pipe 102 includes a first end 102a and a second end 102b, the first end 102a being configured to connect to a fluid source 106, and the second end 102b being equipped with an in-flight refueling connector 108.

[0064] For example, pipe 102 has a length L of about ten meters or tens of meters, especially between 10m and 30m.

[0065] Preferably, the pipe 102 is a multi-layer pipe including, for example, a metal layer, an elastomer layer, and a fabric layer.

[0066] The fluid source 106 may include at least one fluid reservoir and a pump. For example, the fluid may be fuel.

[0067] In-flight refueling connector 108 is mentioned above. Figure 1 The described type of in-flight refueling connector includes, for example, a pressure limiting member 110 and a truncated conical basket 112.

[0068] The pipe 102 may be associated with a deployment system 104, which is configured to enable the pipe 102 to be deployed, in particular by winding and unwinding the pipe 102.

[0069] The deployment system 104 for the pipe 102 is capable of winding the pipe 102 around an axis and unwinding the pipe 102 to a desired length to ensure refueling during flight. For example, the deployment system 104 is a winch-type deployment system.

[0070] The deployment system 104 may include attachment components for attaching to a structure of the refueling aircraft 118. For example, such attachment components may be attachment flanges not shown in the figures.

[0071] The in-flight refueling device 100 also includes a radiation system 114, particularly a lighting system 114, arranged along at least a portion of the conduit 102. The radiation system 114 may be connected to an energy source 116.

[0072] The power source 116 may be located on one side of the first end 102a of the conduit 102, particularly within the aircraft. Alternatively, the power source 116 may be located at the in-flight refueling connector 108 or the deployment system 104.

[0073] The lighting system 114 includes at least one radiation source 120, particularly a series of radiation sources 120, particularly a series of light spots 120.

[0074] The lighting system 114 extends, for example, along the conduit 102 by a length L1, for example, several meters, particularly more than one-third of the total length L of the conduit 102, particularly more than half of the total length L of the conduit 102, and even more particularly more than three-quarters of the total length L of the conduit 102.

[0075] The radiation sources 120 can be uniformly distributed along the conduit 102 or a portion thereof. More specifically, the radiation sources 120 can be regularly spaced apart from each other at a distance H, particularly between 20 cm and 100 cm, preferably between 40 cm and 60 cm, for example, 50 cm.

[0076] The radiation source 120 may be selected from light-emitting diodes (LEDs), light-emitting fibers, optical fibers and / or piezoelectric strips.

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

[0078] If a light-emitting diode or fiber optic cable is used, the radiation source 120 can be connected to the energy source 116 via at least one electrical conductor 122 (such as a wire). The electrical conductor 122 can extend along the conduit 102. In this configuration, the energy source 116 is an electrical energy source.

[0079] If optical fibers are used, they can extend along conduit 102. The optical fibers can be connected to power source 116. In this configuration, power source 116 is a light energy source.

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

[0081] As described above, the conduit 102 may also include a white annular band 124.

[0082] Figure 3 This is a schematic diagram of another embodiment of the in-flight refueling device 100 according to the present invention. More specifically, Figure 3Another embodiment of the in-flight refueling device 100 is shown, wherein the energy source 116 is located in the refueling aircraft 118. For example, in this configuration, the energy source 116 may be located in the deployment system 104 adjacent to the duct 102 or on the deployment system 104 of the duct 102.

[0083] The energy source 116 can be a generator of the type of electric motor, which is configured to generate electrical energy when the conduit 102 is unfolded, particularly when the conduit 102 is unwound and wound.

[0084] For example, pipe 102 is wound around a drum that can rotate about the aforementioned axis; for example, a generator includes a rotor that is rotated by the drum.

[0085] Figure 4 yes Figure 3 Another schematic diagram of the in-flight refueling device 100 experiencing fluctuations. Specifically, Figure 4 The general principles of the invention are illustrated.

[0086] During in-flight refueling, the conduit 102 extends several meters. Waves are likely to be generated and propagate along the conduit. For example, this could be because the in-flight refueling connector 108 strikes the second connector 20 (particularly the boom) of the aircraft being refueled.

[0087] The wave in the pipe 102 takes the form of a wave, which can have a period P between 2m and 4m and a maximum amplitude B between 50cm and 150cm.

[0088] Waves could cause the second connector 20 (especially the boom) to break, making an emergency landing necessary for an aircraft that needs refueling after such damage.

[0089] The presence of radiation sources 120 at regular intervals allows the pilot of an aircraft awaiting refueling to see the general shape of pipe 102. As a result, the pilot of the aircraft awaiting refueling may see the formation of waves.

[0090] If the detected fluctuations are too large, the pilot of the aircraft awaiting refueling may decide to disconnect the second connector 20 (specifically the boom) of the aircraft awaiting refueling from the pipe 102.

[0091] The presence of radiation source 120 allows pilots of aircraft awaiting refueling to understand the shape and speed of the waves, even during nighttime flights, which is particularly advantageous.

[0092] In one embodiment, the radiation source 120 is distributed along a line, which may be a straight line parallel to the longitudinal axis A of the pipe 102.

[0093] Figure 5and Figure 6 This is a schematic diagram of an alternative embodiment of the in-flight refueling device 100 according to the present invention.

[0094] The radiation source 120 can be distributed in the line spirally wound around the pipe 102.

[0095] The lighting system 114 may include two or more series of radiation sources 120, which are distributed in two or more lines extending along the conduit 102.

[0096] The lines of radiation source 120 may be spaced apart at an angle to each other or spaced apart at an angle around pipe 102.

[0097] In the case where the duct 102 or the lighting system 114 includes two lines L1, L2 of the radiation source 120, the lines L1, L2 can be positioned around the duct at an angle α of 180° to each other, that is, they are diametrically opposite each other relative to the longitudinal axis A of the duct 102.

[0098] In the case where the duct 102 or the lighting system 114 includes three lines of radiation source 120, these lines can be spaced apart at an angle α between 60° and 120°.

[0099] In the case where the duct 102 or the lighting system 114 includes four lines of radiation source 120, these four lines are spaced apart from each other at an angle α between 60° and 90°.

[0100] The lighting system 114 can be installed and attached to the outer periphery of the pipe 102, for example, by gluing.

[0101] Alternatively, the lighting system 114 can be integrated into the conduit 102. In the case described above, where the conduit 102 is of a multi-layered type, the lighting system 114 can be integrated into the fabric layer, for example, by weaving.

[0102] The in-flight refueling device 100 according to the present invention can be specifically arranged as follows:

[0103] -Inside refueling aircraft 118;

[0104] - At the downstream end of the fuselage of the refueling aircraft 118;

[0105] - Below the wing of refueling aircraft 118; and / or

[0106] -In the carrier, also known as the cabin, the carrier is installed

[0107] ○ At the belly point of refueling aircraft 118; and / or

[0108] ○ Below the wing of the refueling aircraft 118.

[0109] This invention improves the safety of refueling missions (especially nighttime refueling missions) by enabling the pilot of an aircraft awaiting refueling to perform an emergency disconnection when deemed necessary. With current technology, the pilot of an aircraft awaiting refueling may not anticipate wave generation and relies entirely on the overall behavior of the refueling system during flight.

Claims

1. An in-flight refueling device (100), particularly for refueling aircraft, comprising: - A conduit (102) configured to transport fluid includes a first end (102a) adapted for connection to a fluid source (106) and a second end (102b) equipped with an in-flight refueling connector (108), and A lighting system (114) arranged along at least a portion of the conduit (102), the lighting system being connectable to an energy source, and comprising at least a series of radiation sources (120) distributed along a portion of the conduit (102). The feature is that the pipe (102) is of a multi-layer type and includes at least one metal layer, an elastomer layer and a fabric layer, and the lighting system is integrated into the fabric layer.

2. The in-flight refueling device (100) according to claim 1, wherein, The radiation sources (120) are spaced apart by a distance (H) between 20 cm and 100 cm, preferably between 40 cm and 60 cm, for example, 50 cm.

3. The in-flight refueling device (100) according to claim 1 or 2, wherein, The radiation source (120) is selected from light-emitting diodes, light-emitting fibers, optical fibers and / or piezoelectric strips.

4. The in-flight refueling device (100) according to any one of the preceding claims, wherein, The lighting system (114) includes at least two series of radiation sources (120), which are distributed on at least two lines (L1, L2) extending along the conduit (102) and spaced apart from each other at an angle around the conduit (102).

5. The in-flight refueling device (100) according to claim 4, wherein, The lighting system (114) includes two lines of a radiation source (120) positioned 180° apart from each other around the conduit.

6. The in-flight refueling device (100) according to claim 4, wherein, The lighting system (114) includes three lines of radiation source (120) spaced apart from each other at an angle between 60° and 120°.

7. The in-flight refueling device (100) according to claim 4, wherein, The lighting system (114) includes four lines of a radiation source (120), the four lines being spaced apart at an angle between 60° and 90°.

8. The in-flight refueling device (100) according to any one of claims 1 to 7, wherein, The radiation source (120) is distributed in a straight line along the pipe (102).

9. The in-flight refueling device (100) according to any one of claims 1 to 7, wherein, The radiation sources (120) are distributed on a line spirally wound around the pipe (102).

10. The in-flight refueling device (100) according to any one of claims 1 to 9, wherein, The lighting system (114) is attached to the outer periphery of the pipe (102).

11. The in-flight refueling device (100) according to any one of claims 1 to 9, wherein, The lighting system (114) is integrated into the conduit (102).

12. The in-flight refueling device (100) according to claim 11, wherein, The lighting system is integrated into the fabric layer by weaving.

13. An assembly comprising a fluid source (106) and an in-flight refueling device (100) according to any one of the preceding claims, wherein the fluid is, for example, fuel, and the fluid source is connectable to the first end of the conduit.

14. An aircraft (14) comprising an in-flight refueling device (100) according to any one of claims 1 to 12 and / or the components according to claim 13.

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