Guillotine system, in particular for an in-flight refueling device

Abstract

The invention relates to a guillotine system (114), in particular for an in-flight refueling device (100), comprising - a passage (124) through which a pipe (102) is able to pass, - a blade (126) movable between a first position in which the pipe (102) is able to slide freely through the passage (124), and a second position in which the blade (126) is able to cut the pipe (102), the guillotine system (114) further comprising an actuator (128) of the non-pyrotechnic type configured to contain and / or generate a pressurized fluid released to move the blade (126) from the first position to the second position.

Description

[0001] DESCRIPTION

[0002] TITLE: GUILLOTINE SYSTEM, PARTICULARLY FOR AN IN-FLIGHT REFUELLING DEVICE

[0003] Technical field of the invention

[0004] The present invention relates to the general field of aeronautics. It relates more particularly to a guillotine system, in particular for an in-flight refueling device for an aircraft, as well as an aircraft comprising such an in-flight refueling device.

[0005] Technical background

[0006] The technical background includes in particular documents US-A1 - 2014 / 346279, W0-A1 -02 / 24529, US-A1 -2002 / 074455, US-A1 -2019 / 257710 and EP-A1 -4 032 809.

[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 a refueler 14 or refueling aircraft 14, is equipped with an in-flight refueling device to which a second aircraft 22, also called a 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 can 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. Alternatively, the hose 10 can be deployed from a load, also called a nacelle, installed at the ventral point of an aircraft, in particular a fighter aircraft, or from a load installed under the wing of an aircraft, in particular a refueling aircraft or a fighter aircraft.

[0012] 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.

[0013] 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.

[0014] 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.

[0015] 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.

[0016] Furthermore, the truncated cone basket 26 has a shape which also makes it easier to center the first connector 18 in the air flow.

[0017] 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.

[0018] 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. 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.

[0019] In the event that the movements of the pipe 10 are too large and anarchic, they could come into contact with the refueling aircraft 14 and / or the second aircraft 22.

[0020] Furthermore, when the movements of the hose 10 occur when the second connector 20 of the second aircraft 22 is connected to the first connector 18 of the refueling aircraft 14, it is then necessary for the second aircraft 22 to clear the area subject to disturbances downstream of the first aircraft 14 or to turbulence. As a last resort, it may be considered to cut the hose 10 if it cannot be rewound.

[0021] Furthermore, after refueling, there is a risk that the first connector 18 of the refueling aircraft 14 and the second connector 20 of the second aircraft 22 will not disengage from each other. In this case, the second connector 20 will provide a mechanical fuse function.

[0022] Finally, there is also a risk that the hose deployment system will become blocked and it will no longer be possible to rewind the hose after it has been deployed.

[0023] In such cases, it is necessary to cut the hose to abandon the unwound portion of the hose and prevent it from creating a risk to the refueling aircraft and / or the aircraft to be refueled. For example, the pilot of the refueling aircraft may, for example, decide to cut the hose before landing the refueling aircraft 14.

[0024] It is thus known to associate with the pipe a guillotine system comprising a passage crossed by the pipe and a blade movable between a first position, in which the pipe can slide freely through the passage, and a second position, in which the blade cuts the pipe in order to section it in two.

[0025] Such a guillotine system includes an actuator configured to be activated by a control circuit located, generally, in the cockpit of the refueling aircraft. When the pilot of the refueling aircraft actuates the control circuit, a signal is sent to the actuator which triggers a movement of the blade from the first position to the second position.

[0026] In current technology, the actuator is of the pyrotechnic type, that is, it includes an explosive charge and a detonator that ignites the explosive charge when it receives the aforementioned signal. The ignition of the charge releases significant pressure that moves the blade to cut the pipe.

[0027] This solution is advantageous because the pipe can be cut anywhere along its length. Furthermore, it allows the guillotine system to have a good response time of around a few milliseconds following signal remission.

[0028] Such technology, described for example in document FR-A-1 590 598, however has drawbacks.

[0029] A first disadvantage is linked to the fact that the explosive charge is subject to strict regulations requiring daily disarming. Human intervention is necessary to disarm and rearm the actuator every day, which can lead to handling errors, such as incorrect connections, or forgetting to connect, for example when connecting an electrical harness.

[0030] Another disadvantage is the obsolescence of this type of actuator, which must be replaced regularly due to its relatively short lifespan. Furthermore, the use of this type of actuator may be called into question under new regulations, such as the REACH regulation to secure the manufacture and use of chemical substances in European industry.

[0031] Another disadvantage is that it is not possible to track the status of such an actuator type once mounted in a refueling aircraft.

[0032] An alternative to the hose cutting solution exists and consists of abandoning the entire hose rather than a cut portion of it. For this, the hose deployment system comprises an electromechanical hose decoupling system. However, such an alternative is also not ideal because, in order to decouple the hose, it needs to be fully unwound, and the hose deployment system can become blocked even when the hose is not fully unwound. 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.

[0033] Summary of the invention

[0034] The invention relates to a guillotine system, in particular for an in-flight refueling device, comprising

[0035] - a passage through which a pipe is able to pass,

[0036] - a blade movable between o a first position, in which the pipe is able to slide freely through the passage, and o a second position, in which the blade is able to cut the pipe, in particular in order to cut it in two, and

[0037] - an actuator, in particular capable of being activated by a control circuit, configured to ensure the movement of the blade from the first position to the second position.

[0038] More particularly, the actuator is of the non-pyrotechnic type. The actuator is therefore not subject to the constraints and drawbacks of the prior art.

[0039] Additionally, the actuator is configured to contain and / or generate a pressurized fluid released to move the blade from the first position to the second position.

[0040] The present invention provides several non-pyrotechnic solutions for the actuator.

[0041] In this application, a non-pyrotechnic actuator is to be understood as an actuator without explosion or spark, i.e. one which does not generate an explosion or spark when in use.

[0042] According to a first aspect, the actuator comprises a cartridge, capable of containing a volume of a pressurized gas. Such a pressurized gas is configured to be released, in particular following activation by the control circuit, in order to ensure movement of the blade from the first position to the second position. The invention thus proposes to replace the pyrotechnic guillotine system of the prior art with a pneumatic guillotine system.

[0043] The invention makes it possible to overcome at least some of the drawbacks described above. Firstly, the cartridge containing the pressurized gas is not subject to strict regulations and does not have to be disarmed. It therefore requires less human intervention, or even no particular human intervention. The cartridge containing the pressurized gas has a longer lifespan than an explosive charge. Such a cartridge can, moreover, be instrumented to monitor its condition over time, which was not possible in the prior art.

[0044] According to a second aspect of the invention, the actuator comprises an accumulator, capable of containing a volume of pressurized liquid. Such pressurized liquid is configured to be released in order to ensure movement of the blade from the first position to the second position.

[0045] The invention thus proposes to replace the pyrotechnic guillotine system of the prior art with a hydraulic or hydromechanical guillotine system.

[0046] The invention makes it possible to overcome at least some of the drawbacks described above. Firstly, the accumulator containing the pressurized liquid is not subject to strict regulations and does not have to be disarmed. It therefore requires less human intervention, or even no particular human intervention. The accumulator containing the pressurized liquid has a longer service life than an explosive charge. Such an accumulator can, moreover, be instrumented to monitor its condition over time, which was not possible in the prior art.

[0047] According to a third aspect of the invention, the actuator comprises a container capable of containing chemical reagents, in particular separated from each other and capable of being mixed and / or brought into contact to generate a pressurized gas. Such a pressurized gas is then released to ensure movement of the blade from the first position to the second position. The invention thus proposes to replace the pyrotechnic guillotine system of the prior art with a chemical reaction guillotine system.

[0048] The invention overcomes at least some of the drawbacks described above. First, the container containing the chemical reagents is not subject to strict regulations and does not need to be disarmed. It therefore requires less human intervention, or even no specific human intervention. The container containing the chemical reagents has a longer lifespan than an explosive charge. Such a container can, moreover, be instrumented to monitor its condition over time, which was not possible in the prior art.

[0049] Generally speaking, the invention can provide a gain in terms of the actuator response time. The release of the gas, liquid, or reagents can be done in a reaction time of the order of a millisecond, for example.

[0050] The guillotine system according to the invention may also have one or more of the following characteristics, taken alone or in combination with each other:

[0051] - the pressurized gas is air and / or an inert gas;

[0052] - the cartridge comprises a closed enclosure, capable of containing the pressurized gas, and a port, capable of allowing passage of the pressurized gas;

[0053] -- the actuator comprises, in addition to the pressurized gas, a fuel; this fuel is capable of burning to further increase the pressure of the gas and thus improve the performance of the actuator;

[0054] -- the fuel is associated with an ignition or activation system, preferably connected to said control circuit;

[0055] - the accumulator comprises a first internal cavity, capable of containing the liquid under pressure, and a second internal cavity, capable of containing gas under pressure and / or an elastic return member, such as a spring, in particular the first internal cavity and the second internal cavity being separated from each other by a membrane, in particular mobile and / or deformable;

[0056] - the first internal cavity comprises an outlet port capable of allowing liquid to pass through for the purpose of moving the blade, and an inlet port capable of allowing liquid to pass through for the purpose of loading and / or recharging the accumulator with liquid;

[0057] - the inlet port is connected to a source of pressurized liquid, in particular a hydraulic pump, in particular manually operated;

[0058] - the actuator comprises a container, capable of containing chemical reagents, in particular separated from each other and capable of being mixed and / or brought into contact to generate a pressurized gas and ensure movement of the blade from the first position to the second position;

[0059] - the chemical reagents are in solid form, in particular one of the chemical reagents being in powder form;

[0060] - the or each port is equipped with a valve;

[0061] - the system further comprises a monitoring unit, capable of enabling monitoring of a state of the actuator;

[0062] - the monitoring unit comprises at least one sensor and / or is connected to at least one sensor, the sensor being, for example, a pressure sensor;

[0063] - the guillotine system comprises a body defining the passage;

[0064] - the guillotine system comprises a chamber connected, directly or by a pressurized gas conduit, to the actuator;

[0065] - the blade is carried by a support, in particular a piston, capable of moving in the chamber following the supply of the chamber by the actuator, the movement of the support in the chamber causing the movement of the blade from the first position to the second position;

[0066] - the guillotine system also includes a cutting status sensor, capable of confirming that the pipe is properly cut; this sensor allows the aircraft pilot to confirm the correct cutting status of the pipe; in fact, when the pipe is cut, the aircraft must slow down (as well as for the refueling phase); once the correct cutting status is indicated, the aircraft can accelerate; today, this confirmation is made by a second device which must visually confirm the correct separation of the pipe;

[0067] ■■■■ the cutting status sensor is connected to the monitoring unit;

[0068] - the monitoring unit comprises a computer, capable of emitting an alarm in the event of a fault in the actuator, and in particular a fault in the gas, the pressurized liquid or the reagents, or even capable of receiving signals from the cutting status sensor;

[0069] - the monitoring unit and / or the cutting sensor is capable of issuing an alarm to the pilot.

[0070] The present invention also relates to an in-flight refueling device comprising: a hose, configured to allow a transfer of fluid, this hose comprising a first end intended to be connected to a source of fluid, and a second end equipped with an in-flight refueling connector, a system for deploying the hose, this system being to deploy the hose, in particular to wind and unwind the hose, over a desired length to ensure in-flight refueling, and a guillotine system as described above.

[0071] More specifically, the guillotine system can be carried in whole or in part by the deployment system.

[0072] The present invention also relates to an assembly comprising

[0073] - an in-flight refueling device as described above,

[0074] - a source of fluid, such as fuel, connected to the first end of the pipe, and

[0075] - a control circuit connected to the actuator.

[0076] The present invention also relates to an aircraft comprising a guillotine system, an in-flight refueling device or an assembly as described above.

[0077] Brief description of the figures

[0078] 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:

[0079] - [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;

[0080] - [Fig. 2] Figure 2 is a perspective view of an embodiment of an in-flight refueling device according to the invention; - [Fig. 3] Figure 3 is a schematic view of an embodiment of a guillotine system for an in-flight refueling device according to the invention;

[0081] - [Fig. 4] Figure 4 is a schematic view of an alternative embodiment of a guillotine system for an in-flight refueling device according to the invention; and

[0082] - [Fig. 5] Figure 5 is a schematic view of another alternative embodiment of a guillotine system for an in-flight refueling device according to the invention.

[0083] Detailed description of the invention

[0084] Figures 2 and 3 illustrate an embodiment of an in-flight refueling device 100 according to the invention.

[0085] More specifically, Figure 2 is a perspective view of the embodiment of the in-flight refueling device 100 according to the invention.

[0086] The in-flight refueling device 100 includes a hose 102, configured to allow fluid transfer, and a cutoff system, including a guillotine system 114, configured to allow refueling to be cut off through the hose 102, if needed.

[0087] The in-flight refueling device 100 may also comprise a deployment system 104, configured to allow the deployment of the hose 102, in particular by winding and unwinding the hose 102.

[0088] 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.

[0089] The pipe 102 has, for example, a length of around ten meters or several tens of meters, in particular a length of between 10m and 30m.

[0090] The hose 102 is preferably a multi-layer hose comprising, for example, a metal layer, an elastomer layer and a textile layer.

[0091] The fluid source 106 may comprise at least one fluid reservoir and a pump. The fluid is, for example, fuel. 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.

[0092] The deployment system 104 of the hose 102 is capable of winding the hose 102 around an axis X and unwinding it to a desired length to ensure in-flight refueling. The deployment system 104 is, for example, of the winch type.

[0093] The deployment system 104 may comprise a portion for attachment to a structure of the refueling aircraft 14. Such an attachment portion may be, for example, a fixing flange, not shown in the figures.

[0094] In one embodiment, the fixing flange can be connected to two parallel arms carrying a drum movable around an axis of rotation X. The pipe 102 is able to be wound around the movable drum and unwound from the latter.

[0095] The guillotine system 114 is preferably carried by the deployment system 104.

[0096] In one embodiment, the guillotine system 114 may be attached to a rod connected to the arms carrying the movable drum. In particular, the rod on which the guillotine system 114 is attached may extend parallel to the X axis of rotation of the movable drum.

[0097] Figure 3 is a schematic view of one embodiment of a guillotine system 114 for the in-flight refueling device 100 according to the invention.

[0098] The guillotine system 114 includes a passage 124, through which the hose 102 is adapted to pass. The hose 102 is adapted to slide through the passage 124, during deployment, in particular when the hose 102 is rolled up and unrolled.

[0099] The guillotine system 114 also includes a blade 126, capable of being movable between

[0100] - a first position, in which the pipe 102 can slide freely through the passage 124, and

[0101] - a second position, in which the blade 126 cuts the pipe 102 in order to section it in two. In the particular non-limiting embodiment of FIG. 3, the blade 126 is in the first position, which is a high position in the example shown, and the pipe 102 is located in the lower part.

[0102] When the blade 126 is in the second position, illustrated in dotted lines 126', in FIG. 3, which is in the low position in the example shown, it is therefore at the level of the pipe 102. When the blade 126 moves from the first position to the second position, the blade 126 cuts or slices the pipe 20, in particular over an entire section of the pipe 20.

[0103] The blade 126 is preferably a metal blade.

[0104] The guillotine system 114 further comprises an actuator 128, in particular configured to be activated by a control circuit 130, and intended to ensure the movement of the blade 126 from the first position to the second position.

[0105] According to the invention, the actuator 128 is of the non-pyrotechnic type.

[0106] According to a first aspect of the invention illustrated in FIG. 3, the actuator 128 comprises a cartridge 132, capable of containing a pressurized gas, such as air, in particular compressed air, and / or an inert gas under pressure.

[0107] The cartridge 132 contains a volume of pressurized gas, configured to be released following activation by the control circuit 130. A release of the pressurized gas allows the blade 126 to move from the first position to the second position. The cartridge may further comprise, in addition to the pressurized gas, a fuel to form a hybrid actuator. This fuel is capable of burning to further increase the gas pressure and thus improve the performance of the actuator. The fuel is preferably associated with an ignition or activation system which is controlled for example by the control circuit 130.

[0108] Preferably, the cartridge 132 comprises a closed enclosure 134, capable of containing the pressurized gas. In addition, the cartridge 132 may comprise a port 136, capable of allowing passage of the pressurized gas from the enclosure 134. The port 136 may be equipped with a valve 138. The guillotine system 114 may also comprise a monitoring unit 140, capable of allowing monitoring of a state of the cartridge 132.

[0109] The monitoring unit 140 comprises, for example, at least one sensor 142 and / or is connected to a sensor 142. The sensor 142 is, in particular, a pressure sensor.

[0110] The monitoring unit 140 can be remote, mounted on the cartridge 132, in particular via the port 136, and / or be integrated into the port 136.

[0111] The monitoring unit 140 and / or the sensor(s) 142 may be connected to the port 136, in particular to the valve 138.

[0112] The monitoring unit 140 may further comprise or may be connected to at least one pipe cutting status sensor, this sensor being capable of confirming that the pipe is indeed cut.

[0113] The monitoring unit preferably comprises an on-board computer, capable of issuing an alarm in the event of a fault in the actuator, and in particular a fault in the pressurized gas (such as a leak), and also of receiving signals from the cutting state sensor. The monitoring unit is capable of issuing an alarm to the pilot of the aircraft.

[0114] In the example shown, the guillotine system 114 comprises a body 143, capable of defining the passage 124. The body 143 of the guillotine system 114 comprises a chamber 144 connected, directly or via a pressurized gas conduit 146, to the cartridge 132, in particular to the port 136, in particular to the valve 138.

[0115] The blade 126 is arranged in the passage 124 of the body 143 of the guillotine system 114. Furthermore, the blade 126 may be carried by a support 148, such as a piston. The support 148 is also able to move in the chamber 144, following a supply of the chamber 144 by the cartridge 132.

[0116] The movement of the support 148 in the chamber 144 causes the movement of the blade 126 from the first position to the second position and therefore the cutting of the pipe 102.

[0117] The in-flight refueling device 100 comprising the guillotine system 114 according to the invention can in particular be arranged: - inside the refueling aircraft 14;

[0118] - at a downstream end of a fuselage 12 of the refueling aircraft 14;

[0119] - under a wing of the refueling aircraft 14; and / or

[0120] - in a load, also called a nacelle, installed o at a ventral point of the refueling aircraft 14, and / or o under the wing of the refueling aircraft 14.

[0121] Furthermore, according to the invention, the pressurized gas is likely to be contained in the cartridge 132 under a pressure of at least 100 bars. The pressure of the pressurized gas in the cartridge 132 depends on the material, the composition of the pipe 102, the shape of the blade 126 and / or the force to be applied to at least partially cut the pipe 102.

[0122] Figure 4 is a schematic view of an alternative embodiment of the guillotine system 114 for the in-flight refueling device 100 according to the invention. The guillotine system 114 further comprises an actuator 228, in particular configured to be activated by a control circuit 130, and intended to ensure the movement of the blade 126 from the first position to the second position.

[0123] According to the invention, the actuator 228 is of the non-pyrotechnic type.

[0124] According to a second aspect of the invention illustrated in FIG. 4, the actuator 228 comprises an accumulator 232, capable of containing a volume of pressurized liquid, such as oil or fuel.

[0125] The accumulator 232 contains a volume of pressurized liquid, configured to be released following activation by the control circuit 130. A release of the pressurized liquid allows the movement of the blade 126 from the first position to the second position.

[0126] Preferably, the accumulator 232 comprises a first internal cavity 234a, capable of containing the liquid under pressure, and a second internal cavity 234b, capable of containing gas under pressure and / or an elastic return member, such as a spring.

[0127] The first internal cavity 234a and the second internal cavity 234b may be separated from each other by a membrane 235, in particular a mobile and / or deformable membrane. Preferably, the accumulator 232 comprises a closed enclosure, capable of containing the pressurized liquid, the pressurized gas and / or a return member. In particular, the first internal cavity 234a comprises a closed enclosure, capable of containing the pressurized liquid, and / or the second internal cavity 234b comprises a closed enclosure, capable of containing the pressurized gas.

[0128] In addition, the first internal cavity 234a may comprise an outlet port 236, capable of allowing a passage of liquid for the purpose of moving the blade 126. In addition, the first internal cavity 234a may comprise an inlet port 239, capable of allowing a passage of liquid for the purpose of charging and / or recharging the accumulator 232 with liquid.

[0129] The outlet port 236 is capable of allowing passage of pressurized liquid from the first internal cavity 234a. The outlet port 236 may be equipped with a valve 238.

[0130] The inlet port 239 is connected to a source of pressurized liquid. In particular, the source of pressurized liquid may be a hydraulic pump 240, in particular manually operated, in particular comprising and / or connected to a liquid reservoir.

[0131] A connection between the inlet door 239 and the hydraulic pump 240 can be made by a flexible pipe 241.

[0132] The guillotine system 114 may also comprise a monitoring unit 140, capable of enabling monitoring of a state of the accumulator 232.

[0133] The monitoring unit 140 comprises, for example, at least one sensor 142 and / or is connected to a sensor 142. The sensor 142 is, in particular, a pressure sensor.

[0134] The monitoring unit 140 can be remote, mounted on the accumulator 232, in particular via the port 236, and / or be integrated into the port 236.

[0135] The monitoring unit 140 and / or the sensor(s) 142 may be connected to the port 236, in particular to the valve 238.

[0136] The monitoring unit 140 may further comprise or may be connected to at least one pipe cutting status sensor, this sensor being capable of confirming that the pipe is indeed cut. The monitoring unit preferably comprises an on-board computer, capable of issuing an alarm in the event of a fault in the actuator, and in particular a fault in the pressurized liquid (such as a leak), and also of receiving signals from the cutting status sensor. The monitoring unit is capable of issuing an alarm to the pilot of the aircraft.

[0137] In the example shown, the guillotine system 114 comprises a body 143, capable of defining the passage 124. As mentioned above, the body 143 of the guillotine system 114 may comprise a chamber connected, directly or via a pressurized liquid conduit 146, to the accumulator 232, in particular to the port 236, in particular to its valve 238. The blade 126 is arranged in the passage 124 of the body 143 of the guillotine system 114. Furthermore, the blade 126 may be carried by a support, such as a piston. As mentioned above, the support may also be capable of moving in a chamber, following a supply of the chamber by the accumulator 232.

[0138] The movement of the support in the chamber causes the blade 126 to move from the first position to the second position and thus the pipe 102 to be cut.

[0139] The in-flight refueling device 100 comprising the guillotine system 114 according to the invention can in particular be arranged:

[0140] - inside the refueling aircraft 14;

[0141] - at a downstream end of a fuselage 12 of the refueling aircraft 14;

[0142] - under a wing of the refueling aircraft 14; and / or

[0143] - in a load, also called a nacelle, installed o at a ventral point of the refueling aircraft 14, and / or o under the wing of the refueling aircraft 14.

[0144] Furthermore, according to the invention, the pressurized liquid is likely to be contained in the accumulator 232 under a pressure of at least 100 bars. The pressure of the pressurized liquid in the accumulator 232 depends on the material, the composition of the pipe 102, the shape of the blade 126 and / or the force to be applied to at least partially cut the pipe 102. Figure 5 is a schematic view of another alternative embodiment of the guillotine system 114 for the in-flight refueling device 100 according to the invention.

[0145] The guillotine system 114 further comprises an actuator 328, in particular configured to be activated by a control circuit 130, and intended to ensure the movement of the blade 126 from the first position to the second position.

[0146] According to the invention, the actuator 328 is of the non-pyrotechnic type.

[0147] According to a third aspect of the invention illustrated in FIG. 5, the actuator 328 comprises a container 332, capable of containing chemical reagents 333.

[0148] According to a particular embodiment, the chemical reagents 333 are separated from each other and capable of being mixed and / or brought into contact to generate and release a pressurized gas. A release of the pressurized gas makes it possible to ensure the movement of the blade 126 from the first position to the second position.

[0149] The chemical reagents 333 are, for example, in solid form, one of the chemical reagents 333 being, in particular, in powder form.

[0150] The container 332 contains a volume of chemical reagents 333, configured to, after mixing, generate a pressurized gas capable of being released following activation by the control circuit 130. A release of the pressurized gas makes it possible to ensure the movement of the blade 126 from the first position to the second position.

[0151] Preferably, the container 332 comprises a closed enclosure, capable of containing the pressurized gas. In addition, the container 332 comprises a port 336, capable of allowing passage of the pressurized gas to the outside of the container 332. The port 336 may be equipped with a valve 338.

[0152] The guillotine system 114 may also comprise a monitoring unit 140, capable of enabling monitoring of a state of the container 332. The monitoring unit 140 comprises, for example, at least one sensor 142 and / or is connected to a sensor 142. The sensor 142 is, in particular, a pressure sensor.

[0153] The monitoring unit 140 may be remote, mounted on the container 332, in particular via the port 336, and / or be integrated into the port 336. The monitoring unit 140 and / or the sensor(s) 142 may be connected to the port 336, in particular to its valve 338.

[0154] The monitoring unit 140 may further comprise or may be connected to at least one pipe cutting status sensor, this sensor being capable of confirming that the pipe is indeed cut.

[0155] The monitoring unit preferably comprises an on-board computer, capable of issuing an alarm in the event of a fault in the actuator, and in particular a fault in the reagents, and also of receiving signals from the cutting state sensor. The monitoring unit is capable of issuing an alarm to the pilot of the aircraft.

[0156] In the example shown, the guillotine system 114 comprises a body 143, capable of defining the passage 124. As mentioned above, the body 143 of the guillotine system 114 may comprise a chamber connected, directly or via a pressurized gas conduit, to the container 332, in particular to its port 336, in particular to the valve 338.

[0157] The blade 126 is arranged in the passage 124 of the body 143 of the guillotine system 114. Furthermore, the blade 126 may be carried by a support, such as a piston. As mentioned above, the support may also be able to move in a chamber, following a supply of the chamber by the container 332.

[0158] The movement of the support in the chamber causes the blade 126 to move from the first position to the second position and thus the pipe 102 to be cut.

[0159] The in-flight refueling device 100 comprising the guillotine system 114 according to the invention can in particular be arranged:

[0160] - inside the refueling aircraft 14;

[0161] - at a downstream end of a fuselage 12 of the refueling aircraft 14;

[0162] - under a wing of the refueling aircraft 14; and / or

[0163] - in a load, also called a nacelle, installed o at a ventral point of the refueling aircraft 14, and / or o under the wing of the refueling aircraft 14.

[0164] Furthermore, according to the invention, the pressurized gas is capable of being generated in the container 332 under a pressure of at least 100 bars. The pressure depends on the material, the composition of the pipe 102, the shape of the blade 126 and / or the force to be applied to at least partially cut the pipe 102.

[0165] The advantages of the invention are numerous and for example:

[0166] - a gain in maintenance, because the guillotine system 114 no longer requires verification intervention before each flight and after each return from flight of the refueling aircraft 14. In addition, the cartridge 132 and / or the actuator 128, 228, 328 no longer have a usage time limit;

[0167] - a gain in reliability, because daily assembly and disassembly operations on the 114 guillotine system are eliminated;

[0168] - a gain in availability and flight safety, because the guillotine system 114 can be monitored thanks to the feedback on the status of the pressure inside the cartridge 132 and / or the status of the actuator 128, 228, 328. This eliminates the occurrence of a breakdown, guaranteeing a better availability rate of an essential safety function so that the refueling aircraft 14 can land or land with complete peace of mind in the event of a breakdown of the in-flight refueling device 100;

[0169] - a gain in simplicity of placing on the market because the 114 guillotine system is no longer subject to restrictive regulations; etc.

Claims

CLAIMS 1. Guillotine system (114), in particular for an in-flight refueling device (100), comprising - a passage (124), through which a pipe (102) is able to pass, - a blade (126) movable between o a first position, in which the pipe (102) is able to slide freely through the passage (124), and o a second position, in which the blade (126) is able to cut the pipe (102), in particular in order to cut it in two, and - an actuator (128, 228, 328), configured to ensure the movement of the blade (126) from the first position to the second position, characterized in that said actuator (128, 228, 328) is of the non-pyrotechnic type, configured to contain and / or generate a pressurized fluid released to move the blade (126) from the first position to the second position, and in that the system further comprises a monitoring unit (140), capable of allowing monitoring of a state of the actuator (128, 228, 328).

2. Guillotine system (114) according to claim 1, wherein the actuator (128) comprises a cartridge (132), capable of containing a volume of a pressurized gas, in particular air and / or an inert gas.

3. Guillotine system (114) according to claim 2, wherein the cartridge (132) comprises a closed enclosure (134), capable of containing the pressurized gas, and a port (136), capable of allowing passage of the pressurized gas.

4. Guillotine system (114) according to claim 1, wherein the actuator (228) comprises an accumulator (232), capable of containing a volume of liquid under pressure.

5. System according to claim 4, in which the accumulator (232) comprises a first internal cavity (234a), capable of containing the liquid under pressure, and a second internal cavity (234b), capable of containing gas under pressure and / or an elastic return member, in particular the first internal cavity (234a) and the second internal cavity (234b) being separated from each other by a membrane (235), in particular mobile and / or deformable.

6. System according to claim 5, in which the first internal cavity (234a) comprises an outlet port (236), capable of allowing a passage of liquid for the purpose of moving the blade (126), and / or an inlet port (239), capable of allowing a passage of liquid for the purpose of loading and / or recharging the accumulator (232) with liquid.

7. System according to claim 6, wherein the inlet port (239) is connected to a source of pressurized liquid, in particular a hydraulic pump (240), in particular manually operated.

8. Guillotine system (114) according to claim 1, wherein the actuator (328) comprises a container (332), capable of containing chemical reagents (333), in particular separated from each other and capable of being mixed and / or brought into contact to generate a pressurized gas.

9. A guillotine system (114) according to claim 8, wherein the chemical reagents (333) are in solid form, in particular one of the chemical reagents being in powder form.

10. Guillotine system (114) according to one of the preceding claims, wherein the monitoring unit (140) comprises at least one sensor (142) and / or is connected to at least one sensor (142).

11. Guillotine system (114) according to one of the preceding claims, wherein the guillotine system (114) comprises a chamber (144) connected to the actuator (128, 228, 328).

12. Guillotine system (114) according to the preceding claim, in which the blade (126) is carried by a support (148), capable of moving in the chamber (144) following the supply of the chamber (144) by the actuator (128, 228, 328), the movement of the support (148) in the chamber (144) causing the movement of the blade (126) from the first position to the second position.

13. Guillotine system (114) according to one of the preceding claims, wherein it further comprises a cutting status sensor, capable of confirming that the pipe (102) is indeed cut.

14. In-flight refueling device (100) comprising: - a pipe (102), configured to allow a transfer of fluid, this pipe comprising a first end (102a), intended to be connected to a source of fluid (106), and a second end (102b) equipped with an in-flight refueling connection (108), and - a deployment system (104) for the pipe (102), this system being capable of deploying the pipe (102), in particular of winding and unwinding the pipe (102), over a desired length to ensure in-flight refueling, characterized in that it comprises a guillotine system (114) according to any one of the preceding claims.

15. In-flight refueling device (100) according to the preceding claim, in which the guillotine system (114) is carried in whole or in part by the deployment system (104).

16. Set comprising: - an in-flight refueling device (100) according to claim 14 or 15, - a source of fluid (106), such as fuel, connected to the first end (102a) of the pipe (102), and - a control circuit (130) connected to the actuator (128, 228, 328).

17. Aircraft (14) comprising a guillotine system (114) according to any one of claims 1 to 13, or an in-flight refueling device (100) according to claims 14 or 15 or an assembly according to claim 16.

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