System and method for launching a plurality of drones with guidance rings
The described system addresses the inefficiency of vertical drone storage by using guide rods and interface devices to facilitate easy addition and removal of drones, improving operational flexibility and efficiency in drone deployment.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- NAVAL GRP
- Filing Date
- 2024-12-13
- Publication Date
- 2026-06-19
AI Technical Summary
Existing drone launching systems that store drones vertically in a column do not allow for easy addition or removal of drones without first removing an already installed drone, leading to inefficiencies in managing drone deployments.
A system comprising a chassis, guide rods, interface devices, and a displacement and launching device that facilitate the stacking, guidance, and launching of multiple drones, allowing for easy addition or removal of drones through a guided mechanism.
Enables compact and efficient deployment of multiple drones by allowing easy insertion and removal of drones, enhancing operational flexibility and reducing the need for sequential removal of existing drones.
Smart Images
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Abstract
Description
Title of the invention: System and method for launching a plurality of drones with guidance rings
[0001] DOMAIN
[0002] The present invention relates to the field of drones, more particularly a system for launching a plurality of drones.
[0003] In this document, the term "drone" refers to an Unmanned Aerial Vehicle (UAV), that is, an "air vehicle without a human on board," in other words, a flying machine whose piloting is automatic or remotely controlled. Such drones can have various functions, such as carrying out an observation mission, or serving as a decoy, etc.
[0004] The invention also relates to a naval or land platform, or an aircraft, comprising at least one such system, and also relates to a corresponding launching method. EARLIER ART
[0005] It is known to launch a plurality of drones sequentially. The drones are, for example, stored vertically in a "column" in order to save floor space.
[0006] However, due to this column storage, it is not possible to add or remove a drone between two drones already installed, without first removing at least one of the drones already installed.
[0007] One object of the invention is to remedy all or part of the above disadvantages, by providing a system for launching a plurality of drones that is both compact and allows, more easily, adding a drone to those already installed or removing one of the drones already installed more easily. Summary of the invention
[0008] The invention relates to a system for launching a plurality of drones comprising:
[0009] - a chassis,
[0010] - a guiding device comprising at least two guide rods extending parallel to each other in a guiding direction,
[0011] - a plurality of interface devices intended to be fixed respectively on the drones and adapted to be stacked according to the guidance direction so as to form a stack defining respective locations for the drones, each of the interface devices comprising at least two interface zones adapted to cooperate by mechanical contact with the two guidance rods respectively of in order to guide each of the interface devices along the two guide rods into a storage area defined by the system,
[0012] - a displacement device adapted to move the stack in the direction of guidance relative to the chassis and intended to move one of the drones and one of the interface devices from the storage area to an admission area defined by the system, and
[0013] - a launching device intended to support one of the interface devices and one of the drones located in the admission zone and to move said one of the interface devices and said one of the drones to a launch zone defined by the system, the launch device being intended to allow said one of the drones to take off from the launch zone, and then to successively take charge of the other interface devices and drones, each of the interface devices comprising:
[0014] - at least two guide rings adapted to surround respectively the two guide rods around the guidance direction to form the two interface zones, and
[0015] - a body intended to be attached to one of the drones, the body comprising at least two fastening elements adapted to be fixed respectively onto the two guide rings while the two guide rings have already been mounted respectively onto the two guide rods.
[0016] According to other advantageous aspects of the invention, the system comprises one or more of the following features, taken individually or in all technically possible combinations:
[0017] - each of the fastening members includes an elastically deformable part and defining a housing, the elastically deformable part being adapted to be snapped respectively onto one of the two guide rings, the elastically deformable part being received in the housing after snapping;
[0018] - the two guide rings are cylindrical and the elastically deformable part includes a cylindrical surface that at least partially delimits the housing;
[0019] - each of the two guide rings of at least one of the interface devices includes two movable half-rings between a mounted configuration, in which the two half-rings are fixed one on top of the other around one of the two guide rods, and a disassembled configuration, the passage from the disassembled configuration to the mounted configuration allowing the two guide rings of said at least one of the interface devices respectively to be mounted on the two guide rods between two other interface devices in the direction of guidance, the two interface areas of each of the two other interface devices cooperating by mechanical contact with the two guide rods;
[0020] - the two guide rings comprise mechanical bearings forming the two interface zones;
[0021] - the two guide rings are self-lubricated, or solid-lubricated;
[0022] - the guiding device further comprises a platform mounted on the chassis of in a removable manner, the two guide rods being fixed on the platform and extending between the platform and the launching device in the direction of guidance, the two guide rods being mounted adjustablely on the platform between a plurality of configurations corresponding to a plurality of spacings between the two guide rods;
[0023] - the body comprises: two ends opposite each other in the direction of guidance and extending in a first transverse direction orthogonal to the direction of guidance; at least one pin projecting from one of the two ends in the direction of guidance, the pin having a stem and a distal tip relative to said one of the two ends, the distal tip being wider than the stem radially relative to the direction of guidance; at least one through-housing defined by the other of the two ends, and adapted to receive, in the direction of guidance, the pin of a neighboring interface device belonging to the plurality of interface devices, the tip of the pin of the neighboring interface device being adapted to protrude from the through-housing in the direction of guidance;and at least one slot defined by the other of the two ends, and adapted to allow passage of the rod of the pin of the neighboring interface device from the through housing to the launch zone along a second transverse direction orthogonal to the guidance direction and to the first transverse direction. ;
[0024] The invention also relates to a naval or land platform, or an aircraft, comprising at least one system as described above.
[0025] The invention also relates to a method for launching a plurality of drones comprising the following steps:
[0026] - obtaining a system or platform as described above, and of a plurality of drones, the body of each interface device being fixed to one of the drones respectively,
[0027] - assembly of the two guide rings of each of the interface devices respectively on the two guide rods, the two guide rings surrounding the two guide rods respectively around the direction of guidance and forming the two interface zones,
[0028] - fixing the two fixing members of each of the interface devices respectively on the two guide rings, while the two guide rings have already been mounted respectively on the two guide rods, the interface devices being stacked according to the guidance direction so as to form a stack defining respective locations for the drones,
[0029] - cooperation of the two interface zones of each of the interface devices by mechanical contact with the two guide rods, and guidance of each of the interface devices along the two guide rods in the storage area,
[0030] - displacement, by the displacement device, of the stack in the direction of guidance relative to the chassis, and movement of one of the drones and one of the interface devices from the storage area to the admission area,
[0031] - taking charge, by the launching device, of one of the interface devices and of one of the drones located in the admission area and movement of said one of the interface devices and said one of the drones to the launch area, and takeoff of said one of the drones from the launch area, and
[0032] - successive handling of the other interface devices and drones by the launch device. Brief description of the drawings
[0033] The invention will become clearer upon reading the following description, given solely by way of non-limiting example, and made with reference to the accompanying drawings, in which:
[0034] [Fig-1] [Fig.1] is a schematic, side view of a launch system of a plurality of drones according to the invention, just after the takeoff of one of the drones, the trolley being in the launch position,
[0035] [Fig.2] [Fig.2] is a schematic, top view of the system shown on the [Fig.l],
[0036] [Fig.3] [Fig.3] is a schematic, side view of the system shown on the Figures 1 and 2, with the trolley in the admission position, a new drone having just been pushed into the admission zone by the displacement device,
[0037] [Fig.4] [Fig.4] is a schematic, partial, front view of the system shown Figures 1 to 3 show, in particular, the guidance system and an electrical circuit intended to power the drones in the storage area,
[0038] [Fig. 5] [Fig. 5] is a schematic, perspective view of the body of one of the interface devices of the system shown in Figures 1 to 4, exhibiting certain characteristics of the interface devices, the general shape of the body of the interface devices being better represented in [Fig. 18],
[0039] [Fig.6] [Fig.6] is a view analogous to that of [Fig.3], the trolley having taken charge of one of the drones and being moved from the take-off position to the launch position shown in [Fig.1],
[0040] [Fig.7] [Fig.7] is a view analogous to that of [Fig.6], the trolley being in the process of return from the pick-up position to the admission position, after one of the drones has taken off,
[0041] [Fig-8] [Fig.8] is a view analogous to that of [Fig.7], the trolley being moved from the launch position to the admission position, after one of the malfunctioning drones has failed to take off, the anti-return device being about to release this malfunctioning drone from the trolley,
[0042] [Fig.9] [Fig.9] is a view analogous to that of [Fig.8], the chariot having pursued Its trajectory had passed the takeoff position, and the malfunctioning drone was falling outside the launch system.
[0043] [Fig. 10] [Fig. 10] is a schematic, partial, side view of a launch system constituting a variant of the launch system shown in Figures 1 to 3 and 5 to 9, in which the system is equipped with a safety device, the trolley being in the admission position and one of the drones having just arrived in the admission zone (as in [Fig. 3]),
[0044] [Fig.11] [Fig.11] is a view analogous to that of [Fig.10], the trolley being in the process of moving from the admission position to the handling position and having just actuated the locking device to move the locking piece from the holding position to the raised position,
[0045] [Fig.12] [Fig.12] is a view analogous to that of [Fig.11], the trolley having taken charge of the drone located in the admission zone and being moved from the take-off position to the launch position, the securing part being moved from the raised position, shown in [Fig. 11], to the lowered position,
[0046] [Fig.13] [Fig.13] is a view analogous to that of [Fig.12], the locking piece being in the lowered position, and advantageously locked in this position by the locking device,
[0047] [Fig.14] [Fig.14] is a view analogous to that of [Fig.13], the drone having taken off (or having been cleared by the anti-return device), the trolley being in the process of returning from the handling position to the admission position and actuating the securing device to allow the securing part to rise from the lowered position to the holding position, the securing part accompanying the movement of a new drone from the storage area to the admission area,
[0048] [Fig.15] [Fig.15] is a view analogous to that of [Fig.10], representing a variant of the launch system, adapted for launching fixed-wing drones,
[0049] [Fig.16] [Fig.16] is a view analogous to that of [Fig.10], representing a variant of the launching system, equipped with wheels and adapted to be moved manually,
[0050] [Fig.17] [Fig.16] is a view analogous to that of [Fig.1], partially showing a naval platform equipped with a vertical missile launcher comprising a system analogous to that shown in Figures 1 to 3 and 5 to 9, and
[0051] [Fig. 18] [Fig. 18] is a view similar to that of [Fig. 5], showing the body and guide rings of one of the interface devices, certain features of the interface devices not being shown on [Fig. 18] and visible on [Fig. 5], in particular the possible retaining pins. DETAILED DESCRIPTION System for launching a plurality of drones
[0052] With reference to figures 1 to 9 and 18, a system 10 according to the invention is described.
[0053] The system 10 is adapted to launch a plurality of drones 12, in the sense specified below. above.
[0054] In the example, the drones 12 are rotary-wing, and have for example four propellers 14 ([Fig.2]).
[0055] According to a variant which will be described later, the drones 12 are for example fixed-wing.
[0056] The system 10 comprises a chassis 16, and a guide device 18 extending in a guide direction Z, for example substantially vertical.
[0057] The system 10 comprises a plurality of interface devices 20 fixed respectively to the drones 12 and adapted to be stacked along the guidance direction Z so as to form a stack 22 defining respective locations for the drones. This makes it possible to rotate the propellers 14 of the drones 12 without the drones touching each other.
[0058] The interface devices 20 are represented schematically in Figures 1 to 17, in the form of a frame cooperating directly with the guidance system, and more realistically in [Fig. 18], which will be described below. Some features of the interface devices 20 are shown in Figures 1 to 17, while other features are shown in [Fig. 18].
[0059] The system 10 includes a displacement device 24 adapted to move the stack 22 (arrow Fl, [Fig.3]) in the guidance direction Z relative to the chassis 16 and intended to move one of the drones 12 and one of the interface devices 20 from a storage area 26 defined by the system 10 to an admission area 28 ([Fig.3]) also defined by the system.
[0060] Advantageously, the system 10 includes a securing device 30 ([Fig. 10]) adapted to guide and hold said one of the interface devices 20 moved from the storage area 26 to the admission area 28 by the moving device 24.
[0061] The system 10 includes a launch device 32 adapted to support one of the interface devices 20 and one of the drones 12 located in the admission zone 28 (arrow F2, [Fig.6]) and to move said one of the interface devices and said one of the drones to a launch zone 34 (Figures 1 and 7) defined by the system 10, the launch device 32 being adapted to allow a take-off (arrow F3, [Fig.7]) of the drone from the launch zone 34, and then to successively take charge of the other interface devices 20 and drones 12.
[0062] The system 10 advantageously includes an anti-return device 36 adapted to allow the launch of one of the drones 12 and to release one of the drones from the launch device 32 if the drone is faulty.
[0063] The system 10 advantageously includes an electrical circuit 38 ([Fig.4]), and for example an electrical power source 40 electrically connected to the electrical circuit and intended to electrically power the drones 12 in the storage area 26.
[0064] Alternatively, the electrical power source 40 is external to the system 10. In other words, the system 10 is then adapted to be connected to an external electrical source. Chassis
[0065] The chassis 16 forms, for example, an envelope surrounding at least partially the storage area 26 and the intake area 28.
[0066] In an alternative (not shown), the chassis 16 is a load-bearing structure with gaps (like a framework).
[0067] The chassis 16 advantageously defines an exit 42 ([Fig.l]) located between the admission zone 28 and the launch zone 34 and allowing the passage of drones supported by the launch device 32.
[0068] Under this outlet 42, the chassis 16 advantageously defines an inclined plane 44 whose function will be described below. Guidance device
[0069] The guide device 18 comprises two guide rods 18A, 18B (figures 4 and 18) extending parallel to each other in the guidance direction Z.
[0070] According to an unrepresented variant, the guide device 18 comprises more than two guide rods.
[0071] The guiding device 18 includes for example a plate 46 ([Fig.l]) mounted or placed on the chassis 16 in a removable manner.
[0072] The two guide rods 18A, 18B are advantageously fixed on the platform 46 and extend between the platform and the launching device 32 in the guidance direction Z.
[0073] Each of the two guide rods 18A, 18B has a distal end 48 (figures 3 and 4) relative to the platform, the distal end 48 being for example located between the storage area 26 and the intake area 28.
[0074] Advantageously, each of the two guide rods 18A, 18B comprises at least one electrically conductive part 50A, 50B extending along the guidance direction Z into the storage area 26. According to a particular embodiment, each of the two guide rods 18A, 18B is made of an electrically conductive material.
[0075] Advantageously, the two guide rods 18A, 18B are mounted adjustablely on the plate 46 between a plurality of configurations corresponding to a plurality of spacings E ([Fig.4]) between the two guide rods along a first transverse direction X perpendicular to the guidance direction Z.
[0076] For example, each of the two guide rods 18A, 18B is mounted on an oblong hole (not shown) defined by the plate 46, advantageously by means of a washer (not shown) fixed on each of the guide rods and a nut (not shown) screwed onto each of the guide rods.
[0077] The two guide rods 18A, 18B are advantageously cylindrical (with a circular base).
[0078] The electrically conductive part 50A, 50B includes, for example, graphite.
[0079] According to variants not shown, the electrically conductive part 50A, 50B of each of the two guide rods 18A, 18B comprises an adhesive tape 52 comprising copper, or a metallic layer 54 obtained by vapor phase deposition.
[0080] The plate 46 is advantageously electrically insulating.
[0081] For the purposes of this document, "electrically conductive" means, for example, a material whose electrical resistivity at 300 K is, for example, less than or equal to 105 Qm
[0082] The term "electrically insulating" means a material whose electrical resistivity at 300 K is, for example, greater than or equal to 105 Qm Displacement device
[0083] The displacement device 24 includes for example a movable platform 56 ([Fig.l]) mounted on the guide device 18 movable in translation along the guide direction Z.
[0084] The platform 56 is advantageously located under the stack 22.
[0085] The plate 56 is movable for example under the effect of a counterweight, a jack or at least a spring (not shown). Interface devices
[0086] The interface devices 20 are, for example, dedicated to a specific type of drone. In this case, to launch different types of drones, different types of interface devices are used, the rest of the launch system 10 advantageously remaining unchanged.
[0087] According to an unrepresented variant, the interface devices 20 are modifiable, particularly in their dimensions, so as to be able to adapt to different types of drones.
[0088] In the example, each of the interface devices 20 has at least two interface zones 20A, 20B (Figures 5 and 18) adapted to cooperate by mechanical contact, two by two, with the two guide rods 18A, 18B respectively so as to guide each of the interface devices 20 along the two guide rods in the storage zone 26.
[0089] In the example, each of the interface devices 20 comprises only the two interface zones 20A, 20B.
[0090] As seen in [Fig. 18], the interface device 20 comprises two guide rings 164A, 164B adapted to surround respectively the two guide rods 18A, 18B around the Z guide direction and to form the two interface areas 20A, 20B.
[0091] According to variants not shown, the interface device 20 comprises more than two guide rings forming more than two interface zones.
[0092] Advantageously, other guide rings (not shown) are pre-mounted on the two guide rods 18A, 18B, in order to provide locations for additional drones.
[0093] The interface device 20 comprises a body 166 fixed on one of the drones 12.
[0094] In the example, the body 166 is reported on each of the drones 12. For example, the drones 12 are stuck in locations defined by the body 166.
[0095] According to an unrepresented variant, body 166 is part of one of drones 12.
[0096] The body 166 has two fixing members 168A, 168B adapted to be fixed respectively on the two guide rings 164A, 164B while the two guide rings have already been mounted respectively on the two guide rods 18A, 18B.
[0097] Advantageously, each of the fastening members 164A, 164B comprises an elastically deformable portion 170 defining a housing 172, the elastically deformable portion being adapted to be snapped onto one of the two guide rings 164A, 164B respectively, the latter being received in the housing 172 after snapping. The elastically deformable portion 170 includes, for example, a cylindrical surface 174 delimiting at least part of the housing 172.
[0098] The two guide rings 164A, 164B are, for example, cylindrical.
[0099] According to a particular embodiment, each of the two guide rings 164A, 164B comprises two movable half-rings 175, 176 between a mounted configuration ([Fig. 18]), in which the two half-rings are fixed one on top of the other around one of the two guide rods 18A, 18B, and a disassembled configuration. This allows for easy addition or removal of guide rings.
[0100] The transition from the disassembled configuration to the assembled configuration allows the two guide rings 164A, 164B of the interface device 20 to be mounted respectively on the two guide rods 18A, 18B between two other interface devices 20 (represented in figures 10 to 14 for example) according to the guidance direction Z, the two interface zones 20A, 20B of each of the two other interface devices 20 cooperating by mechanical contact with the two guide rods 18A, 18B.
[0101] The two guide rings 164A, 164B include, for example, mechanical bearings 178 forming the two interface zones 20A, 20B.
[0102] As an alternative or in addition, the two guide rings 164A, 164B are self-lubricated, or with solid lubrication.
[0103] As can be seen in [Fig.5] (on which the guide rings are not shown), the body 166 comprises, for example, two ends 58, 60 opposite each other in the guidance direction Z and extending in the first transverse direction X. For example, the body 166 comprises four uprights 62, 64, 66, 68 connecting the two ends together in the guidance direction Z.
[0104] Advantageously, the interface device 20 located in the admission zone 28 and another of the interface devices 20 neighbouring in the stack 22 define between them a passage 70 (figures 4 and 5) in a second transverse direction Y orthogonal to the guidance direction Z and to the first transverse direction X. The same is advantageously true for any two of the consecutive interface devices 20 in the stack 22. Possible holding pawn(s)
[0105] Advantageously, the body 166 of the interface devices 20 comprises two pins 72A, 72B projecting from one of the two ends 58, 60 in the Z-direction, and two through-holes 74A, 74B defined by the other of the two ends 58, 60, and adapted to receive, in the Z-direction, the two pins 72A, 72B of the body 166 of a neighboring interface device 20. The body 166 has two slots 76A, 76B defined by the other of the two ends 58, 60,
[0106] In an alternative (not shown), the body 166 comprises a single pin 72A and defines a single housing 74A and a single corresponding slot 76A.
[0107] Each of the pins 72A, 72B comprises, for example, a stem 78 and an end piece 80 distal to the end 60 from which they protrude, the end piece 80 being wider than the stem 78 radially with respect to the guidance direction Z.
[0108] The tip 80 of the pins 72A, 72B of the neighboring interface device 20 is adapted to protrude through housings 74A, 74B in the guidance direction Z.
[0109] The two slots 76A, 76B are adapted to allow passage of the rod 78 of the pins of the neighbouring interface device from the through housings 74A, 74B to the launch zone 34 along the second transverse direction Y. Launch device
[0110] The launching device 32 advantageously comprises a carriage 82, and at least one actuator 84.
[0111] The actuator 84 is adapted to iteratively move the carriage 82 relative to the chassis 16, advantageously in translation along the second transverse direction Y.
[0112] The actuator 84 is adapted to move the carriage 82:
[0113] - from an admission position ([Fig.3]), in which the carriage 82 allows a interface devices 20 and one of the drones 12 to move from the storage area 26 to the admission area 28 under the action of the movement device 24,
[0114] - towards a pick-up position ([Fig.4], or by shifting the carriage 82 towards the left on [Fig.3]), in which the trolley is intended to support said one of the interface devices 20 and / or the corresponding drone 12 located in the admission zone 28,
[0115] - then to a launch position (Figures 1 and 2), intended to allow takeoff of drone 12 corresponding from launch zone 34,
[0116] - then again (arrow F4 on [Fig.8]) towards the pick-up position, and then back to the intake position.
[0117] The trolley 82 is adapted to move said one of the interface devices 20 and / or the corresponding drone 12 from the admission zone 28 to the launch zone 34 when the trolley moves from the admission position to the launch position, and to oppose the passage of another of the interface devices 20 from the storage zone 26 to the admission zone 28 when the trolley is in the pick-up position and when the trolley is in the launch position.
[0118] The actuator 84 includes, for example, a pneumatic cylinder.
[0119] The carriage 82 advantageously comprises a platform 86 and a stop 88.
[0120] The plate 86 extends, for example, perpendicularly to the Z guide direction and is adapted to enter the passage 70 described above, without moving said one of the interface devices 20, when the trolley 82 moves from the admission position to the support position.
[0121] The stop 88 is adapted to push said one of the interface devices 20 and / or the corresponding drone 12 when the trolley 82 moves from the pick-up position to the launch position. Possible non-return device
[0122] The non-return device 36 is adapted to permit (not oppose) a passage ([Fig.6]) of said one of the interface devices 20 from the admission zone 28 to the launch zone 34.
[0123] The anti-return device 36 is advantageously adapted to prevent one of the interface devices 20 from moving back in the opposite direction ([Fig. 8]) from the launch zone 34 to the admission zone 28, in the event that the corresponding drone 12 has not taken off. The anti-return device 36 is then adapted to disengage one of the interface devices 20 from the trolley 82 when the trolley is moved from the launch position to the admission position, the system 10 being adapted so that one of the interface devices 20 then falls (arrow F5 in [Fig. 9]) from the trolley 82 outside of the system 10.
[0124] In the example, the inclined plane 44 formed by the chassis 16 is advantageously adapted to guide the falling drone 12.
[0125] The anti-return device 36 includes for example a support 90 mounted on the chassis, a part 92 movablely mounted on the support 90 between a rest position (figures 7 and 8 for example) and a retracted position relative to the support ([Fig.6]), and a first return member 94 adapted to return the part 92 from the retracted position to the rest position.
[0126] In the rest position ([Fig.8]), said one of the interface devices 20, more precisely its body 166, is intended to butt against a first surface 96 of the part 92, during the possible reverse passage from the launch zone 34 to the admission zone 28.
[0127] The retracted position ([Fig.6]) is occupied when the carriage 82 moves from the admission position 28 to the launch position 34 and pushes on a second surface 98 of the part 92 forming for example an inclined plane. Possible security measures
[0128] The security device 30 is optional and can be seen in particular in figures 10 to 14.
[0129] The securing device 30 includes, for example, a securing piece 100 mounted movably in translation relative to the chassis 16 in the guidance direction Z, a second return member 102 to return the securing piece in the guidance direction Z towards the stack 22, and a control system 104 adapted to mechanically control the securing piece and to be actuated by the carriage 82.
[0130] The securing piece 100 is advantageously adapted to cooperate with one of the interface devices 20 moved from the storage area 26 to the admission area 28 by the displacement device 24, said one of the interface devices being compressed between the securing piece 100 and another of the interface devices 20 when said one of the interface devices passes from the storage area 26 to the admission area 28.
[0131] The securing piece 100 forms, for example, a gantry partially surrounding the second transverse direction Y.
[0132] The securing piece 100 includes for example two centering pins 106 (only one of which is visible) intended to cooperate with said one of the interface devices 20, for example with the interface areas 20A, 20B.
[0133] As an alternative (not shown), the securing piece 100 has only one centering pin.
[0134] The securing piece 100 forms in the example a cam 108 extending in the guidance direction Z and in relief in the first transverse direction X.
[0135] The control system 104 is advantageously adapted to move (arrow F6, [Fig. 11]) the locking piece 100 relative to the chassis 16 from a holding position ([Fig. 10]), occupied when said one of the interface devices 20 is in the admission zone 28 and in which the locking piece 100 prevents said one of the interface devices from tilting relative to the chassis 16, to a raised position ([Fig. 11]), occupied when the carriage 82 leaves the support position towards the launch position, and in which the locking piece 100 no longer cooperates with said one of the interface devices 20.
[0136] The control system 104 is advantageously adapted to allow the safety piece 100 to descend (arrow F7, [Fig. 12]) from the raised position ([Fig. 11]) to a lowered position ([Fig. 13]) under the action of the second return element 102 when the carriage 82 moves from the pick-up position to the launch position. In the lowered position, the safety piece 100 is adapted to cooperate with another of the interface devices 20 located in the storage area 26.
[0137] The control system 104 is advantageously adapted to lock the safety piece 100 in the lowered position ([Fig. 13]) when the carriage 82 is in the launching position (or close to it), and to allow the safety piece to rise (arrow F8, [Fig. 14]) from the lowered position to the holding position under the action of the displacement device 24, when the carriage 82 moves from the receiving position to the receiving position. It is therefore understood that the upward action of the displacement device 24 is then stronger than the downward action of the second return element 102.
[0138] In the example, the control system 104 includes a crank 110 rotatably mounted on the frame 16 and adapted to act on the cam 108, a crankshaft 112 rotatably mounted on the frame and adapted to be actuated by the carriage 82, a torsion spring 114 adapted to apply a restoring torque on the crankshaft, and a connecting rod 116 for transmission between the crank 110 and the crankshaft 112. Power supply for drones
[0139] The electrical circuit 38 ([Fig.4]) is electrically connected to the electrically conductive part 50A, 50B of each of the two guide rods 18A, 18B.
[0140] Each of the interface zones 20A, 20B (Figures 5 and 18) includes at least one electrically conductive surface layer (not shown) adapted to be respectively in electrical contact with the electrically conductive part 50A, 50B of one of the two guide rods 18A, 18B.
[0141] The surface layer of each of the four interface zones 20A, 20B is electrically connected to one of the drones 12.
[0142] For example, each of the interface devices 20 has an electrical interface socket 120 electrically connected to the surface layer of the interface areas 20A, 20B, the electrical socket 120 being electrically connected to one of the drones 12. System operation
[0143] The operation of the system 10 is derived from its structure and will now be described in such a way as to illustrate a method according to the invention.
[0144] The interface devices 20 are fixed respectively on the drones 12 and stacked along the guidance direction Z so as to form the stack 22 defining the respective locations for the drones.
[0145] The interface zones 20A, 20B of each of the interface devices 20 cooperate by mechanical contact with the two guide rods 18A, 18B, so as to guide each of the interface devices along the two guide rods into the storage zone 26.
[0146] The carriage 82 is for example initially in the admission position ([Fig.3]).
[0147] The displacement device 24 moves (arrow Fl) the stack 22 in the guidance direction Z relative to the chassis 16, and moves one of the drones and one of the interface devices from the storage area to the admission area ([Fig. 3]). In the example, the platform 56 pushes the stack 22 upwards in the guidance direction Z, the interface devices 20 being guided by the two guide rods 18A, 18B in the storage area 26. The trolley 82 does not impede the arrival of one of the interface devices 20 and one of the drones 12 in the admission area 28.
[0148] In the inlet zone 28, said one of the interface devices 20 is free with respect to the guide device 18. In the example, the four interface zones 20A, 20B no longer cooperate with the two guide rods 18A, 18B, which are interrupted before the inlet zone 28.
[0149] The actuator 84 moves the carriage 82 relative to the chassis 16 from the admission position to the support position. In the support position ([Fig. 4]), the carriage 82 supports one of the interface devices 20 and / or the drone 12 corresponding located in the admission zone 28 and opposes the passage of another of the interface devices 20 from the storage zone 26 to the admission zone 28. In the example, the platform 86 enters the passage 70 ([Fig.4]) and the stop 88 pushes said one of the interface devices 20 and / or the corresponding drone 12.
[0150] The trolley 82 is moved by the actuator 84 from the receiving position to the launching position, in order to move (arrow F2) one of the interface devices 20 and / or the corresponding drone 12 from the receiving area 28 to the launching area 34 ([Fig. 6]). The trolley 82 prevents the passage of another of the interface devices 20 from the storage area 26 to the receiving area 28 when the trolley is in the launching position.
[0151] Advantageously, the non-return device 36 allows said one of the interface devices 20 to move from the admission zone 28 to the launch zone 34. In the example, the part 92 is in the retracted position, because the part is, for example, pushed upwards by said one of the interface devices 20 in the guidance direction Z.
[0152] The corresponding drone 12, if functional, takes off (arrow F3) from the launch area 34 ([Fig.7]).
[0153] The actuator 84 moves (arrow F4) the trolley 82 from the launch position to the take-up position, and then again to the admission position to admit a new drone 12 into the admission area 28.
[0154] The aforementioned movements of the trolley 82 are repeated several times to allow the flight of the plurality of drones 12 (or the ejection of any defective drones).
[0155] A possible reverse movement of said one of the interface devices 20 from the launch zone 34 to the admission zone 28 is advantageously prevented by the non-return device 36 if the corresponding drone 12 has not taken off ([Fig. 8]). In the example, the part 92 is in the rest position and said one of the interface devices 20 abuts against the first surface 96.
[0156] The anti-return device 36 then disengages one of the interface devices 20 from the carriage 82 when the carriage moves from the launch position to the admission position. One of the interface devices 20, and the corresponding drone 12, then fall from the carriage 82 out of the system (arrow F5, [Fig. 9]). Advantageously, the inclined plane 44 facilitates the removal of the malfunctioning drone.
[0157] Optional retaining pins 72A, 72B (Figures 4 and 5) hold one of the interface devices 20 in position when it enters the intake zone 28, by cooperation with another of the interface devices 20 located below. When the carriage 82 leaves the intake position, the pins 72A, 72B of the interface device 20 located above exit the through slots 74A, 74B of the interface device 20 located below by passing through the slots 76A, 76B. How the security system works
[0158] The locking piece 100 is initially in the holding position ([Fig. 10]), said one of the interface devices 20 having just arrived in the intake zone 28 from the storage zone 26. The locking piece 100 prevents said one of the interface devices 20 from tilting relative to the chassis 16. The crank 110 is in contact with the cam 108.
[0159] As shown in [Fig. 11], the carriage 82 moves from the intake position to the intake position and actuates the control system 104, which moves (arrow F6) the locking piece 100 from the holding position ([Fig. 10]) to the raised position ([Fig. 11]). More specifically, the stop 88 rotates the crankshaft 112, which causes the crank 110 to rotate via the connecting rod 116. The rotation of the crank 110 raises the cam 108.
[0160] In the raised position, the securing piece 100 no longer cooperates with said one of the interface devices 20 and the carriage 82 takes charge of said one of the interface devices 20.
[0161] Then the carriage 82 moves to the launching position. The control system 104 allows the safety piece 100 to descend (arrow F7, [Fig. 12]) from the raised position ([Fig. 11]) to the lowered position ([Fig. 13]) under the action of the second return member 102. More precisely, the crankshaft 112 is released and returns to its initial position under the action of the torsion spring 114. The crank 110 rotates and allows the safety piece 100 to descend.
[0162] In the lowered position, the securing piece 100 cooperates with another of the interface devices 20 still located in the storage area 26.
[0163] The control system 104 locks the locking piece 100 in the lowered position ([Fig. 13]), particularly when the carriage 82 is in the launch position. The control system 104 returns, for example, to its initial position under the action of the torsion spring 114, and the crank 110 locks the locking piece 100 in its lowered position.
[0164] When the carriage 82 moves from the receiving position to the receiving position, the control system allows the locking piece 100 to rise (arrow F8, [Fig. 14]) from the lowered position to the holding position under the action of the displacement device 24, which pushes the stack 22. More specifically, the stop 88 rotates the crankshaft 112 beyond its initial position, causing the crank 110 to rotate and thus release the locking piece 100 from the lowered position. The locking piece 100 can then rise.
[0165] When the carriage 82 returns to the admission position and the locking piece 100 is in the holding position, the control system 104 returns to its initial position and the crank 110 is again in contact with the cam ([Fig. 10]). Electrical operation
[0166] The electrical source 40 ([Fig.4]) sends a current into the electrically conductive part 50A of one 18A of the two guide rods, and receives this current from the other 50B. The current passes through the surface layer 118 ([Fig.5]) of each of the interface zones 20A, 20B, and through the electrical interface socket 120, which makes it possible to power each of the drones 12 in the storage zone 26. System integration into a platform
[0167] The system 10 is intended to be integrated into a larger installation, such as a naval or land-based platform 150 ([Fig. 17]), or an aircraft.
[0168] System 10 can, for example, be integrated:
[0169] - in a missile launch facility ([Fig. 17]), for example in a free pit 152. Integration is advantageously done from above without requiring any particular adaptation of the pit;
[0170] - in a site defence installation;
[0171] - in a shelter or shipping container for ground-based defensive use,
[0172] - in a logistics carrier or maritime barge to protect a wind farm floating, or on a support vessel such as a force supply ship;
[0173] - on the rear or roof of an armored vehicle;
[0174] - at the rear of a cargo vehicle or a flatbed truck;
[0175] - in a frigate, corvette or unmanned surface vehicle (USV) deck;
[0176] - on the roof of a speedboat;
[0177] - in an air carrier in view of a drop;
[0178] - in a helicopter or unmanned aerial vehicle, advantageously for deployment implemented by the lower part of the aircraft.
[0179] These implementations, except the first one mentioned, are purely illustrative and are not shown in the figures. Other variations of the system
[0180] In these variants, system 10 is analogous to those shown in Figures 1 to 14. Similar elements bear the same numerical references and will not be described again. Only the differences or specific features will be described in detail below.
[0181] With reference to [Fig.15], a system 10 adapted for launching fixed-wing drones 12 is described.
[0182] The chassis 16 is advantageously inclined. More precisely, the second transverse direction Y forms an acute angle α with a horizontal plane H.
[0183] The chassis 16 advantageously forms a launching ramp 154.
[0184] The launch device 32 is adapted to give each of the launched drones 12 a predefined initial velocity.
[0185] With reference to [Fig. 16], a portable system 10 is described. The chassis 16 is equipped with wheels 158 and handles 160 enabling a user (not shown) to move the system 10, for example on a deck 162 of a naval platform 150.
[0186] With reference to [Fig. 17], a system 10 integrated into a missile launch installation, for example integrated into a naval platform 150, is again described. The installation includes, for example, several silos or pits, one of which 152 is occupied by the system 10. Benefits
[0187] Thanks to the features described above, the system 10 allows for the launch of multiple drones 12 while remaining compact, and also allows for the easy addition of a drone to the 12 already installed or the removal of one of the 12 already installed drones. Indeed, these operations do not require the removal of any other drones already installed.
Claims
1. Demands System (10) for launching a plurality of drones (12), comprising: - a chassis (16), - a guiding device (18) comprising at least two guide rods (18A, 18B) extending parallel to each other in a guiding direction (Z), - a plurality of interface devices (20) intended to be fixed respectively on the drones (12) and adapted to be stacked along the guidance direction (Z) so as to form a stack (22) defining respective locations for the drones (12), each of the interface devices (20) comprising at least two interface zones (20A, 20B) adapted to cooperate by mechanical contact with the two guidance rods (18A, 18B) respectively so as to guide each of the interface devices (20) along the two guidance rods (18A, 18B) in a storage zone (26) defined by the system (10), - a displacement device (24) adapted to move the stack (22) in the guidance direction (Z) relative to the chassis (16) and intended to move one of the drones (12) and one of the interface devices (20) from the storage area (26) to an admission area (28) defined by the system (10), and - a launch device (32) intended to take charge of one of the interface devices (20) and one of the drones (12) located in the admission zone (28) and to move said one of the interface devices (20) and said one of the drones (12) to a launch zone (34) defined by the system (10), the launch device (32) being intended to allow said one of the drones (12) to take off from the launch zone (34), and then to successively take charge of the other interface devices (20) and drones (12), each of the interface devices (20) comprising: - at least two guide rings (164A, 164B) adapted to respectively surround the two guide rods (18A, 18B) around the guidance direction (Z) and to form the two interface zones (20A, 20B), and - a body (166) intended to be fixed to one of the drones (12), the body (166) comprising at least two fixing members (168A, 168B) adapted to be fixed respectively on the two guide rings (164A, 164B) while the two guide rings (164A, 164B) have already been mounted respectively on the two guide rods (18A, 18B).
2. System (10) according to claim 1, wherein each of the fastening members (168A, 168B) comprises an elastically deformable part (170) defining a housing (172), the elastically deformable part (170) being adapted to be snapped respectively onto one of the two guide rings (164A, 164B), the elastically deformable part (170) being received in the housing (172) after snapping.
3. System (10) according to claim 2, wherein the two guide rings (164A, 164B) are cylindrical and the elastically deformable part (170) has a cylindrical surface (174) delimiting at least in part the housing (172).
4. A system (10) according to any one of claims 1 to 3, wherein each of the two guide rings (164A, 164B) of at least one of the interface devices (20) comprises two half-rings (175, 176) movable between a mounted configuration, in which the two half-rings (175, 176) are fixed one on top of the other around one of the two guide rods (18A, 18B), and a disassembled configuration, the transition from the disassembled configuration to the mounted configuration enabling the two guide rings (164A, 164B) of said at least one of the interface devices (20) to be mounted respectively on the two guide rods (18A, 18B) between two other interface devices (20) along the guidance direction (Z), the two interface zones (20A, 20B) of each of the two other interface devices (20) cooperating by mechanical contact with the two guide rods (18A, 18B).
5. System (10) according to any one of claims 1 to 4, wherein the two guide rings (164A, 164B) comprise mechanical bearings (178) forming the two interface zones (20A, 20B).
6. System (10) according to any one of claims 1 to 5, wherein the two guide rings (164A, 164B) are self-lubricated, or solid-lubricated.
7. System (10) any one of claims 1 to 6, wherein the guiding device (18) further comprises a plate (46) mounted on the chassis (16) in a removable manner, the two guide rods (18A, 18B) being fixed on the platform (46) and extending between the platform (46) and the launching device (32) in the guidance direction (Z), the two guide rods (18A, 18B) being mounted adjustablely on the platform (46) between a plurality of configurations corresponding to a plurality of spacings (E) between the two guide rods (18A, 18B).
8. A system (10) according to any one of claims 1 to 7, wherein the body (166) comprises: - two ends (58, 60) opposite each other in the guidance direction (Z) and extending in a first transverse direction (X) orthogonal to the guidance direction (Z), - at least one pin (72A) projecting from one of the two ends (58, 60) in the guidance direction (Z), the pin (72A) having a stem (78) and an end piece (80) distal to said one of the two ends (58, 60), the distal end piece (80) being wider than the stem (78) radially with respect to the guidance direction (Z), - at least one through-hole (74A) defined by the other of the two ends (58, 60), and adapted to receive, in the guidance direction (Z), the pin (72A) of a neighboring interface device belonging to the plurality of interface devices (20),the tip (80) of the pin (72A) of the neighboring interface device being adapted to protrude from the through housing (74A) in the guidance direction (Z), and - at least one slot (76A) defined by the other of the two ends (58, 60), and adapted to allow passage of the rod (78) of the pin (72A) of the neighboring interface device from the through housing (74A) to the launch zone (34) along a second transverse direction (Y) orthogonal to the guidance direction (Z) and to the first transverse direction (X).
9. Naval or land-based platform (150), or aircraft, comprising at least one system (10) according to any one of claims 1 to Q
10. O. A method for launching a plurality of drones (12), comprising the following steps: - obtaining a system (10) according to any one of claims 1 to 8 or a platform (150) according to claim 9, and a plurality of drones (12), the body (166) of each of the interface devices (20) being respectively fixed to one of the drones (12), - mounting the two guide rings (164A, 164B) of each of the interface devices (20) respectively onto the two guide rods (18A, 18B), the two guide rings surrounding the two guide rods around the guidance direction (Z) and forming the two interface zones (20A, 20B), - fixing the two fixing members (168A, 168B) of each of the interface devices (20) respectively onto the two guide rings (164A, 164B) while the two guide rings (164A, 164B) have already been mounted respectively onto the two guide rods (18A, 18B), the interface devices (20) being stacked along the guidance direction (Z) so as to form a stack (22) defining respective locations for the drones (12), - cooperation of the two interface zones (20A, 20B) of each of the interface devices (20) by mechanical contact with the two guide rods (18A, 18B),and guiding each of the interface devices (20) along the two guide rods (18A, 18B) in the storage area (26), - movement, by the movement device (24), of the stack (22) in the guidance direction (Z) relative to the chassis (16), and movement of one of the drones (12) and one of the interface devices (20) from the storage area (26) to the admission area (28), - taking charge, by the launch device (32), of one of the interface devices (20) and one of the drones (12) located in the admission zone (28) and moving said one of the interface devices (20) and said one of the drones (12) to the launch zone (34), and taking flight of said one of the drones (12) from the launch zone (34), and - successive taking charge of the other of the interface devices (20) and the drones (12) by the launch device (32).