Device for the in-flight refueling of an aircraft
Patent Information
- Application Number
- EP2024721704
- Authority / Receiving Office
- EP · EP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-03-24
- Filing Date
- 2024-03-21
- Publication Date
- 2026-02-11
AI Technical Summary
Current in-flight refueling systems face challenges in safely and visibly detecting pipe movements and undulations during refueling, particularly at night or in low visibility conditions, which can lead to pipe damage and emergency landings due to the inability to perceive waves generated by pipe movements.
The integration of a lighting system along the length of the refueling pipe, comprising regularly spaced radiation sources such as LEDs, optical fibers, or piezoelectric strips, which follow pipe movements and undulations, allowing pilots to visually detect and assess wave formation and speed.
Enhances safety by enabling pilots to detect and respond to pipe movements and undulations, reducing the risk of damage and emergency landings, especially in adverse weather conditions or nighttime operations.
Smart Images
Figure FR2024050353_03102024_PF_FP_ABST
Abstract
Description
[0001] DESCRIPTION
[0002] TITLE: IN-FLIGHT REFUELLING DEVICE FOR AN AIRCRAFT
[0003] Technical field of the invention
[0004] The present invention relates to the general field of aeronautics. It relates more particularly to an in-flight refueling device for an aircraft, as well as to an aircraft comprising such an in-flight refueling device.
[0005] Technical background
[0006] The technical background includes in particular documents US-A1- 2005 / 017130, US-A-5,539,624, DE-A1 -10 2016 118302, CN-U-206 719 564, US-A1 -2005 / 145751 and US-A2-2019 / 154173.
[0007] During a flight, it is known to refuel an aircraft in such a way as to transfer at least one fluid, such as fuel, to it.
[0008] This is the case, for example, of an aircraft that cannot or must not land in an area it is flying over. The aircraft must then be refueled in flight. This is particularly the case when the volume of fuel it is carrying reaches a lower threshold value.
[0009] During such refueling, as shown schematically in FIG. 1, a first aircraft 14, also called refueling aircraft 14 or refueling aircraft 14, is equipped with an in-flight refueling device to which a second aircraft 22, also called receiver 22 or aircraft to be refueled 22, is connected.
[0010] The in-flight refueling device comprises a pipe 10, intended for the transfer of fluid, unrolled from the first aircraft to the second aircraft which is located downstream of the first aircraft, in a direction of flight, and which must be refueled.
[0011] The hose 10 may be unwound or deployed from a downstream end of a fuselage 12 of the refueling aircraft 14, as shown in FIG. 1, or from a wing of the refueling aircraft 14.
[0012] Alternatively, the pipe 10 can be deployed from a load, also called a nacelle, installed at the ventral point of an aircraft, in particular a fighter plane, or from a load installed under the wing of an aircraft, in particular a refueling plane or a fighter plane.
[0013] The pipe 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.
[0014] The first connector 18 is configured to provide a fluid connection with a second connector 20, capable of cooperating by complementarity. The second connector 20 is carried, in particular by a pole, by the aircraft to be refueled 22. Such a type of connection is well known to those skilled in the art.
[0015] The first connection 18 comprises, for example, a pressure limiting member 24 and a truncated cone-shaped basket 26. For this purpose, the connection 18 may comprise a valve making it possible to calibrate a pressure at the outlet of the first connection 18 to the limit in force in the environment.
[0016] The truncated cone-shaped basket 26 serves to facilitate the centering and guiding of the second connector 20 inside the first connector 18. For this purpose, the second connector 20 has a pointed shape cooperating with the pressure limiting member 24 of the first connector 18.
[0017] Furthermore, the truncated cone basket 26 has a shape which also makes it easier to center the first connector 18 in the air flow.
[0018] The hose 10 is unwound using a hose deployment system 10 located inside the refueling aircraft 14 or inside the load of the refueling aircraft 14.
[0019] When the refueling aircraft 14 takes off, the hose 10 is wound up. During refueling, the unwinding of the hose 10 is controlled so as to unwind a sufficient length of the hose 10, for example over several tens of meters, in particular a length of between 15 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.
[0020] The hose 10 is relatively flexible and is likely to move and shift when unwound and subjected to disturbances downstream of the first aircraft 14 or to turbulence. In the event that the movements of the hose 10 are too large and uncontrolled, they could come into contact with the refueling aircraft 14 and / or the second aircraft 22.
[0021] When connecting the hose 10 to the second connector 20 of the aircraft to be refueled 22 and when refueling the aircraft to be refueled 22, waves are generated along the hose 10 and result in undulations of the hose.
[0022] The characteristics of such waves are that they are likely to damage the second connection 20, in particular the boom, of the aircraft to be refueled 22.
[0023] Such waves may cause a rupture of the second connection 20 which would require an emergency landing of the aircraft to be refueled 22, following such damage.
[0024] Depending on the flight conditions, the movements and undulations of the pipe 10 may not be perceptible to the pilot of the aircraft to be refueled 22, or are difficult to do so, particularly during a night flight.
[0025] A pipe 10, intended for the transfer of a fluid during refueling, may comprise white annular bands extending around the pipe 10 and visible to the pilot of the aircraft to be refueled 22. Such annular bands allow the pilot to know the length of pipe 10 deployed but do not allow him to visualize a waveform or to assess its propagation speed.
[0026] When detecting movement or undulation of the hose 10, the pilot of the aircraft to be refueled 22 can uncouple the second connector 20 from the hose 10 and extract himself from a risky situation.
[0027] However, when flying at night or in reduced visibility, for example in the presence of fog and / or clouds, the pilot of the aircraft to be refueled 22 is not able to observe the type of movement or undulation with current technology.
[0028] In addition, the truncated basket 26 carried by the pipe 10 can be equipped with a light system intended to facilitate its location by the pilot of the aircraft to be refueled 22. However, when the second connector 20 of the aircraft to be refueled 22 is connected to the pressure limiting member 24, the truncated basket 26 no longer follows the movements and undulations of the pipe 10.
[0029] The aircraft to be refueled 22 may include a lighting beacon. However, such a beacon is generally not powerful enough to illuminate several tens of meters and may lose effectiveness depending on weather conditions.
[0030] The present invention aims to provide a solution to at least some of the problems of the prior art, which is simple, effective and economical.
[0031] Summary of the invention
[0032] The invention relates to an in-flight refueling device, in particular for a refueling aircraft, comprising a pipe intended for transferring a fluid, this pipe comprising:
[0033] - a first end capable of being connected to a fluid source, and
[0034] - a second end equipped with an in-flight refueling connection, The in-flight refueling device further comprises a light system arranged along at least part of the pipe, capable of being connected to an energy source, in particular located on the side of the first end of the pipe, and comprising at least one series of radiation sources distributed along the part of the pipe, in particular the radiation sources are regularly distributed along the part of the pipe.
[0035] The invention thus proposes to equip the pipe with a lighting system, that is to say a system capable of emitting radiation, in particular light. The lighting system is distributed along part of the length of the pipe or over its entire length. When the pipe undergoes movements or undulations, the lighting system follows such movements and undulations. It is then possible to observe such movements with the naked eye, including in dim light or in poor visibility, in particular at night.
[0036] The light system may be connected to a power source that supplies it with the energy needed to emit the radiation. The power source is chosen based on the nature of the light system. The in-flight refueling device according to the invention may also have one or more of the following characteristics, taken alone or in combination with each other:
[0037] - the radiation sources are spaced from each other by a distance of between 20cm and 100cm, preferably between 40cm and 60cm, and for example 50cm;
[0038] - the radiation source is chosen from a light-emitting diode, a light fiber, an optical fiber and / or a piezoelectric strip;
[0039] - the lighting system comprises at least two series of radiation sources, respectively distributed over at least two lines extending along the pipe and angularly spaced from one another or from one another around the pipe;
[0040] - the light system includes two radiation source lines located at 180° from each other around the pipe;
[0041] - the lighting system comprises three lines of radiation sources spaced apart from each other at an angle of between 60° and 120°;
[0042] - the lighting system comprises four lines of radiation sources spaced apart from each other at an angle of between 60° and 90°;
[0043] - the radiation sources are distributed in a straight line along the pipe;
[0044] - the radiation sources are distributed on a line wound helically around the pipe;
[0045] - the light system is fixed on an external periphery of the pipe;
[0046] - the lighting system is integrated into the pipe;
[0047] - the pipe is of the multi-layer type;
[0048] - the pipe comprises at least one metallic layer, one elastomer layer, and one textile layer;
[0049] - the light system is integrated, for example by weaving, into the textile layer; this improves the durability and visibility of the light system; -- the energy source is a light and / or electrical energy source; and / or
[0050] -- the light system is configured to emit radiation in the visible, infrared and / or ultraviolet range.
[0051] The present invention also relates to an assembly comprising an in-flight refueling device as described above, and a source of fluid, such as fuel, capable of being connected to the first end of the pipe. The present invention also relates to an aircraft comprising an in-flight refueling device and / or an assembly as described above.
[0052] Brief description of the figures
[0053] Other characteristics and advantages of the invention will appear during the reading of the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:
[0054] - [Fig.1] Figure 1 is a schematic view of a refueling aircraft equipped with a device for refueling in flight an aircraft to be refueled;
[0055] - [Fig. 2] Figure 2 is a schematic view of an embodiment of an in-flight refueling device according to the invention;
[0056] - [Fig. 3] Figure 3 is a schematic view of another embodiment of an in-flight refueling device according to the invention;
[0057] - [Fig. 4] Figure 4 is another schematic view of the in-flight refueling device of Figure 3 undergoing undulation;
[0058] - [Fig. 5] Figure 5 is a schematic view of an alternative embodiment of an in-flight refueling device according to the invention; and
[0059] - [Fig. 6] Figure 6 is a schematic view of another alternative embodiment of an in-flight refueling device according to the invention.
[0060] Detailed description of the invention
[0061] Figure 2 illustrates an embodiment of an in-flight refueling device 100 according to the invention.
[0062] More specifically, Figure 2 is a perspective view of the embodiment of the in-flight refueling device 100 according to the invention. The in-flight refueling device 100 comprises a pipe 102 configured to allow fluid transfer.
[0063] The hose 102 has a first end 102a configured to be connected to a fluid source 106, and a second end 102b equipped with an in-flight refueling connector 108.
[0064] The pipe 102 has, for example, a length L of around ten meters or several tens of meters, in particular a length of between 10m and 30m.
[0065] The hose 102 is preferably a multi-layer hose comprising, for example, a metal layer, an elastomer layer and a textile layer.
[0066] The fluid source 106 may comprise at least one fluid reservoir and a pump. The fluid is, for example, fuel.
[0067] The in-flight refueling connection 108 is of the type described above in relation to FIG. 1 and comprises, for example, a pressure limiting member 110 and a frustoconical basket 112.
[0068] The pipe 102 may be associated with a deployment system 104 configured to allow deployment of the pipe 102, in particular by winding and unwinding the pipe 102.
[0069] The deployment system 104 of the hose 102 is capable of winding the hose 102 around an axis and unwinding it to a desired length to ensure in-flight refueling. The deployment system 104 is, for example, of the winch type.
[0070] The deployment system 104 may comprise a portion for attachment to a structure of a refueling aircraft 118. Such an attachment portion may be, for example, a fixing flange, not shown in the figures.
[0071] The in-flight refueling device 100 further comprises a radiation system 114, in particular a light system 114, arranged along at least a portion of the pipe 102. The radiation system 114 is capable of being connected to an energy source 116.
[0072] The energy source 116 may be located on the side of the first end 102a of the pipe 102, in particular located in the aircraft. Alternatively, the energy source 116 may be arranged at the in-flight refueling connection 108 or the deployment 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, on the pipe 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 the pipe 102.
[0075] The radiation sources 120 may be regularly distributed along the pipe 102 or a portion of the pipe 102. More particularly, the radiation sources 120 may be regularly spaced from each other by a distance H, in particular between 20cm and 100cm, preferably between 40cm and 60cm, and for example 50cm.
[0076] The radiation source 120 may in particular be chosen from a light-emitting diode, also known by the acronym LED for “Light-Emitting Diode” in English, a light fiber, an optical fiber, and / or a piezoelectric strip.
[0077] The radiation source 120 is configured to emit light in the visible, infrared and / or ultraviolet range.
[0078] In the case of using a light-emitting diode or a light fiber, the radiation source 120 may be connected to the energy source 116 by at least one electrical conductor 122, such as a wire. The electrical conductor 122 is likely to extend along the pipe 102. In such a configuration, the energy source 116 is then a source of electrical energy.
[0079] In the case of using an optical fiber, the optical fiber may extend along the pipe 102. The optical fiber may be connected to the energy source 116. In such a configuration, the energy source 116 is then a light energy source.
[0080] In the case of the use of a piezoelectric strip, under the effect of a deformation of the pipe 102, the piezoelectric strip also deforms and generates a voltage used as an energy source 116. The pipe 102 may, in addition, comprise white annular strips 124, as previously mentioned.
[0081] 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 energy source 116 is located in the refueling aircraft 118. For example, in such a configuration, the energy source 116 may be located next to or on the deployment system 104 of the hose 102.
[0082] The energy source 116 may be an electrical generator, of the dynamoelectric machine type, configured to generate electrical energy during deployment, in particular during unwinding and winding, of the pipe 102.
[0083] The pipe 102 is, for example, wound on a mobile drum rotating around the aforementioned axis, the electric generator comprising, for example, a rotor rotated by the drum.
[0084] Figure 4 is another schematic view of the in-flight refueling device 100 of Figure 3 undergoing undulation. More particularly, Figure 4 illustrates the general principle of the invention.
[0085] During an in-flight refueling, the hose 102 is deployed over several meters. A wave is likely to be generated and propagate along the hose. This may be, for example, following an impact of the in-flight refueling connector 108 on the second connector 20, in particular the boom, of the aircraft to be refueled.
[0086] The wave results in an undulation of the pipe 102 which can have a period P, in particular between 2m and 4m and a maximum amplitude B between 50cm and 150cm.
[0087] The wave may cause a rupture of the second connection 20, in particular of the boom, requiring an emergency landing of the aircraft to be refueled following such damage.
[0088] The presence of the radiation sources 120 at regular intervals allows the pilot of the aircraft to be refueled to visualize a general shape of the pipe 102. Consequently, the pilot of the aircraft to be refueled can therefore visualize the formation of the undulations.
[0089] In the event that the detected undulations are too significant, the pilot of the aircraft to be refueled could then decide to disconnect the second connector 20, in particular the boom, from the aircraft to be refueled from the pipe 102.
[0090] The presence of the radiation sources 120 allows the pilot of the aircraft to be refueled to assess the shape and speed of the wave, including during a night flight, which is particularly advantageous.
[0091] According to one embodiment, the radiation sources 120 are distributed along a line, which may be a rectilinear line parallel to a longitudinal axis A of the pipe 102.
[0092] Figures 5 and 6 are schematic views of alternative embodiments of the in-flight refueling device 100 according to the invention.
[0093] The radiation sources 120 may be distributed in a line wound helically around the pipe 102.
[0094] The light system 114 may comprise two or more series of radiation sources 120, respectively distributed on two or more lines extending along the pipe 102.
[0095] The radiation source lines 120 may be angularly spaced from one another or from each other around the pipe 102.
[0096] In the case where the pipe 102 or the light system 114 comprises two lines L1, L2 of radiation sources 120, the lines L1, L2 could be located at an angle oc of 180° from each other around the pipe, that is to say diametrically opposite with respect to the longitudinal axis A of the pipe 102.
[0097] In the case where the pipe 102 or the light system 114 comprises three lines of radiation sources 120, these lines could be spaced apart from each other by an angle oc of between 60° and 120°.
[0098] In the case where the pipe 102 or the light system 114 comprises four lines of radiation sources 120 spaced from each other by an angle oc of between 60° and 90°.
[0099] The light system 114 can be attached and fixed, for example by gluing, on an external periphery of the pipe 102.
[0100] Alternatively, the lighting system 114 could be integrated into the pipe 102. In the aforementioned case where the pipe 102 is of the multi-layer type, the lighting system 114 could be integrated into a textile layer, for example by weaving. The in-flight refueling device 100 according to the invention can in particular be arranged:
[0101] - inside the refueling aircraft 118;
[0102] - at a downstream end of a fuselage of the refueling aircraft 118;
[0103] - under a wing of the refueling aircraft 118; and / or - in a load, also called a nacelle, installed o at a ventral point of the refueling aircraft 118, and / or o under the wing of the refueling aircraft 118.
[0104] The invention makes it possible to improve the safety of refueling missions, particularly at night, by allowing the pilot of the aircraft to be refueled to be able to carry out an emergency disconnection if he deems it necessary. In the current technique, the pilot of the aircraft to be refueled cannot anticipate the generation of a wave and is totally dependent on the overall behavior of the in-flight refueling device.
Claims
CLAIMS 1. In-flight refueling device (100), in particular for a refueling aircraft, comprising - a pipe (102) intended for transferring a fluid, this pipe (102) comprising a first end (102a) capable of being connected to a fluid source (106), and a second end (102b) equipped with an in-flight refueling connection (108), and - a light system (114), arranged along at least a portion of the pipe (102), capable of being connected to an energy source, and comprising at least one series of radiation sources (120) distributed along the portion of the pipe (102), characterized in that the pipe (102) is of the multilayer type and comprises at least one metal layer, one elastomer layer, and one textile layer, and in that the light system is integrated into the textile layer.
2. In-flight refueling device (100) according to claim 1, wherein the radiation sources (120) are spaced from each other by a distance (H) of between 20cm and 100cm, preferably between 40cm and 60cm, and for example 50cm.
3. In-flight refueling device (100) according to claim 1 or 2, wherein the radiation source (120) is chosen from a light-emitting diode, a light fiber, an optical fiber and / or a piezoelectric strip.
4. In-flight refueling device (100) according to one of the preceding claims, wherein the light system (114) comprises at least two series of radiation sources (120), respectively distributed on at least two lines (L1, L2) extending along the pipe (102) and angularly spaced from one another or from one another around the pipe (102).
5. An in-flight refueling device (100) according to claim 4, wherein the light system (114) comprises two lines of radiation sources (120) located at 180° to each other around the pipe.
6. In-flight refueling device (100) according to claim 4, wherein the light system (114) comprises three lines of radiation sources (120) spaced apart from each other by an angle of between 60° and 120°.
7. In-flight refueling device (100) according to claim 4, wherein the light system (114) comprises four lines of radiation sources (120) spaced apart from each other by an angle of between 60° and 90°.
8. In-flight refueling device (100) according to one of claims 1 to 7, wherein the radiation sources (120) are distributed in a rectilinear line along the pipe (102).
9. In-flight refueling device (100) according to one of claims 1 to 7, wherein the radiation sources (120) are distributed on a line wound helically around the pipe (102).
10. In-flight refueling device (100) according to one of claims 1 to 9, wherein the light system (114) is fixed on an external periphery of the pipe (102).
11. In-flight refueling device (100) according to one of claims 1 to 9, wherein the light system (114) is integrated into the pipe (102).
12. In-flight refueling device (100) according to claim 11, wherein the light system is integrated by weaving into the textile layer.
13. Assembly comprising an in-flight refueling device (100) according to one of the preceding claims, and a source of fluid (106), such as fuel, capable of being connected to the first end of the pipe.
14. Aircraft (14) comprising an in-flight refueling device (100) according to one of claims 1 to 12 and / or an assembly according to claim