Marine unmanned aerial vehicle launcher

Abstract

The invention relates to the technical field of unmanned aerial vehicle launchers, in particular to a marine unmanned aerial vehicle launcher. The marine unmanned aerial vehicle launcher comprises a supporting frame, a bottom bracket, a telescopic piece, an angle adjusting assembly, a lifting frame, a front supporting assembly and a rear supporting assembly. The two ends of the telescopic pieces are rotationally connected with the supporting frame and the bottom bracket correspondingly, and the multiple telescopic pieces are arranged at intervals; the angle adjusting assembly is arranged on the bottom bracket and is in transmission connection with the lifting frame; the front supporting assembly and the rear supporting assembly are arranged on the lifting frame at intervals in the length direction of the lifting frame, and the front supporting assembly and the rear supporting assembly are both used for being connected with the unmanned aerial vehicle. The front supporting assembly locks or releases the lug rods through the lock catches, so that the levelness of the bottom bracket can be adjusted by adjusting the lengths of the multiple telescopic pieces, it is guaranteed that the levelness of the bottom bracket is within the set range, and therefore the launching accuracy of the unmanned aerial vehicle is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) launching devices, and in particular to a marine-type UAV launching rack. Background Art

[0002] The launch methods of drones can be divided into: taxiing takeoff, catapult takeoff, rocket-assisted launch, hand-thrown launch, aerial delivery and vertical takeoff. Among them, during rocket-assisted launch, the kinetic energy of the drone's takeoff comes from the energy generated by the combustion of fuel in the rocket booster. The advantages of rocket-assisted launch are that the entire launch device occupies a relatively small area, the cost is low, it is less affected by the outside world, and it can be deployed at a faster speed.

[0003] The existing Chinese patent CN107176310B discloses "a UAV launcher, including a base frame, a front support assembly, and a rear support assembly. The front support assembly is arranged at the front end of the base frame to support the front of the UAV, and the rear support assembly is arranged at the rear end of the base frame to support the tail of the UAV. The rear support assembly includes a rear support column, a U-shaped support, and a self-locking spring. The rear support column is fixed to the base frame, and the two ends of the U-shaped support are hinged to the rear support column. The self-locking spring connects the base frame and the U-shaped support. The U-shaped support is subjected to the elastic force of the self-locking spring. A placement rack matching the UAV tail beam is also provided on the U-shaped support. A U-shaped groove is provided at the top of the placement rack, and the UAV tail beam can be placed in the U-shaped groove." When the launcher is installed on a ship, the hull shakes due to waves during the voyage of the ship, which easily causes the launcher to shake and become unstable, resulting in poor stability of the UAV. Summary of the invention

[0004] The purpose of the present invention is to provide a marine UAV launcher, so as to solve the technical problem in the prior art that when the launcher is installed on a ship, the waves cause the hull to shake during the voyage of the ship, which easily causes the launcher to shake unstably, resulting in poor stability of the UAV.

[0005] The present invention provides a marine-type UAV launching frame, comprising: a supporting frame, a bottom bracket, a telescopic member, an angle adjustment assembly, a lifting frame, a front supporting assembly and a rear supporting assembly; the two ends of the telescopic member are rotatably connected to the supporting frame and the bottom bracket respectively, the number of the telescopic members is multiple, and the multiple telescopic members are arranged at intervals; the angle adjustment assembly is arranged on the bottom bracket, and the angle adjustment assembly is transmission-connected to the lifting frame; along the length direction of the lifting frame, the front supporting assembly and the rear supporting assembly are arranged at intervals on the lifting frame, and the front supporting assembly and the rear supporting assembly are both used to connect with the UAV; the front supporting assembly comprises a front supporting frame, a pull rod and a lock; the front supporting frame is provided with a locking groove for placing the ear rod of the UAV, the lock is rotatably arranged on the front supporting frame, the pull rod is connected to the lock, and the pull rod can move along the length direction of the front supporting frame so that the lock locks or releases the ear rod.

[0006] Furthermore, the telescopic member is a buffer electric cylinder; the number of the telescopic members is six, the six telescopic members are arranged at intervals along the same annular direction, and two adjacent telescopic members are arranged at an acute angle.

[0007] Furthermore, every two of the six telescopic members form a group, and the three groups are respectively located at three corners of a triangle, the two telescopic members in the same group form a "V" shape, and the adjacent two telescopic members in two adjacent groups form an inverted "V" shape.

[0008] Furthermore, when the front support assembly is connected to the drone, the length direction of the front support frame intersects with the length direction of the lifting frame, and the front support frame is rotatably connected to the lifting frame; the front support assembly also includes a first elastic member, which is connected between the front support frame and the lifting frame, and the first elastic member can drive the front support frame to rotate toward the lifting frame.

[0009] Furthermore, the front support assembly also includes an automatic release support block and a locking lever; the automatic release support block is arranged on the lifting frame, and a support surface is formed on the automatic release support block, one end of the locking lever is a contact end, and the other end of the locking lever is a connecting end, and the weight of the contact end is greater than the weight of the connecting end; the middle part of the locking lever is rotatably connected to the front support frame, the connecting end can contact and disengage from the support surface, and the connecting end is rotatably connected to the pull rod; when the contact end contacts the support surface, the lock locks the ear rod, and when the contact end disengages from the support surface, the lock releases the ear rod.

[0010] Furthermore, the contact surface is arranged in an inclined surface, and the automatic release support block is arranged to slide along the length direction of the lifting frame; and / or the pull rod is a telescopic structure so as to be able to be telescopic in the length direction of the front support frame.

[0011] Furthermore, the front support assembly also includes a safety pin, which is connected between the lifting frame and the front support frame to lock the position of the front support frame when supporting the drone.

[0012] Furthermore, the front support frame is rotatably connected to the front end wall of the lifting frame; the front support assembly also includes a base, the base is fixed to the front end of the lifting frame, the base is provided with a slide rail, and the automatic release support block is slidably arranged along the slide rail; the base is provided with a first hole, the front support frame is provided with a second hole, and the safety pin is inserted into the first hole and the second hole.

[0013] Furthermore, the angle adjustment assembly includes a rotating drive member, a transmission member, a steering plate and a pitch drive member; the plane where the steering plate is located intersects with the vertical; the rotating drive member is arranged on the base bracket, and the rotating drive member is connected to the steering plate through the transmission member to drive the steering plate to rotate; one end of the lifting frame is rotatably connected to the steering plate, one end of the pitch drive member is rotatably connected to the steering plate, and the other end of the pitch drive member is rotatably connected to the lifting frame.

[0014] Further, the pitch driving member is a pitch motor; and / or, the rotation driving member is a motor, and the transmission member includes a driving gear and a driven gear meshing with the driving gear; the driving gear and the driving gear are both rotatably arranged on the upper surface of the bottom bracket, and the lower surface of the steering plate is fixedly connected to the driven gear.

[0015] Furthermore, the rear support assembly includes a rear support frame, a limit block and a support tail plate; the limit block is provided with a limit groove extending along the length direction of the lifting frame, the support tail plate is slidably arranged in the limit groove, and the support tail plate is used to be fixed on the UAV; and / or the sea-use UAV launch frame also includes a supporting assembly, and the supporting assembly includes a tail tube bracket, a rotating frame, a support plate, a gear rod, a second elastic member, a retractable supporting rod, an adjusting screw and a limit rod; the tail tube bracket is fixed on the lifting frame, the rotating frame is rotatably connected to the tail tube bracket, the support plate is fixed on the rotating frame, and the gear rod is slidably arranged on the tail tube in a direction facing the rotating frame On the bracket, the second elastic member is connected between the tail tube bracket and the rotating frame to press the rotating frame against the gear rod; the support plate is used to support the rocket; the retractable supporting rod is connected between the rotating frame and the support plate; the tail tube bracket includes side plates arranged opposite to each other, and the rotating frame is rotatably connected between the two side plates, each of the side plates is provided with a strip hole, and the two ends of the gear rod are respectively slid into the two strip holes, and the wall of the side plate in the length direction of the strip hole is provided with a through hole, and the adjusting screw passes through the through hole and abuts against the gear rod; the limit rod is arranged on the tail tube bracket, and is located on the side of the rotating frame away from the gear rod.

[0016] The marine UAV launcher provided by the present invention has at least the following beneficial effects:

[0017] The overall length of the telescopic parts is adjustable. The telescopic parts are connected between the support frame and the bottom bracket. By adjusting the length of multiple telescopic parts, the horizontality of the bottom bracket can be adjusted to ensure that the horizontality of the bottom bracket is within the set range, thereby ensuring the stability of the bottom bracket and improving the stability of the UAV. The accuracy of the horizontality of the bottom bracket is guaranteed, and the stability of the UAV is guaranteed. On this basis, the lifting frame is adjusted to the required angle through the angle adjustment component so that the UAV reaches the set launch angle. The accuracy of the launch angle is improved, so that the accuracy of the UAV taking off according to the set trajectory is guaranteed.

[0018] The telescopic parts adopt buffer electric cylinders, which can be adjusted reliably and can also play a role in buffering and shock absorption. The vibration of the hull can be reduced by the buffer electric cylinders, which increases the stability of the marine UAV launcher.

[0019] When the front support frame is in a supporting state, the first elastic member has energy stored and has the ability to drive the front support frame to rotate in a direction close to the lifting frame. When the drone is launched, the front support frame can rotate (rotate along the launch direction of the drone, which can be understood as the front support frame rotating forward close to the lifting frame) during the process of the ear rod disengaging from the locking groove, so that the ear rod can be more smoothly disengaged from the locking groove to ensure the smooth launch of the drone. The provision of the first elastic member can reduce or even avoid the thrust of the ear rod on the front support frame, thereby reducing or even avoiding the power consumption of the drone. When the ear rod is disengaged from the locking groove and the front support frame loses its constraint, the first elastic member can also push the front support frame to rotate downward (in the direction close to the lifting frame) to move away from the drone, further avoiding affecting the movement of the drone.

[0020] The locking degree of the lock can be adjusted, and it can be adjusted according to the specific launch situation, which can also improve the stability of the drone.

[0021] The rotation drive member can drive the steering plate to rotate in the horizontal direction (also understood as in the XY plane) through the transmission member, thereby driving the lifting frame to rotate, and then driving the drone to rotate, thereby adjusting the angle of the drone in the horizontal direction. The pitch drive member works to drive one end of the lifting frame to lift vertically (also understood as the Z axis), so that an angle is formed between the lifting frame and the steering plate, thereby adjusting the launch angle of the drone. The drone launch angle provided in this embodiment can not only adjust the pitch angle, but also adjust the angle of the drone in the plane, so that the launch accuracy of the drone can be higher.

[0022] During the launch of the drone, the tail support plate can slide along the limit groove, and the limit groove limits the movement of the tail support plate, so that the movement of the tail support plate is stable, thereby making the launch of the drone stable. The rear support assembly in this embodiment can not only support the tail of the drone before launch to ensure the stability of the drone, but also limit the movement of the drone when the drone is launched, thereby improving the movement stability of the drone.

[0023] Setting up a supporting assembly can support the rocket, thereby increasing the stability of the UAV before launch.

[0024] It should be understood that both the foregoing general description and the following specific embodiments are for the purpose of example and illustration and do not necessarily limit the present disclosure. The accompanying drawings, which are incorporated into and constitute a part of the specification, illustrate the subject matter of the present disclosure. At the same time, the specification and the drawings are used to explain the principles of the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 This is a schematic structural diagram of a marine-type UAV launcher according to an embodiment of the present invention;

[0027] Figure 2 for Figure 1 The schematic diagram of the structure of the front support assembly in the launcher of the marine type UAV is shown;

[0028] Figure 3 for Figure 1 A schematic diagram of the partial structure of the front support assembly in the marine UAV launcher shown;

[0029] Figure 4 for Figure 1 An enlarged view of point A in the launcher of the marine-type UAV is shown;

[0030] Figure 5 for Figure 1 The schematic diagram of the structure of the supporting assembly in the marine UAV launcher is shown.

[0031] icon:

[0032] 1- Support frame;

[0033] 2- bottom bracket;

[0034] 3- telescopic parts;

[0035] 4-angle adjustment component; 401-rotation drive member; 402-driving gear; 403-driven gear; 404-pitch drive member; 405-steering plate;

[0036] 5-Lifting frame;

[0037] 6-front support assembly; 601-front support frame; 602-pull rod; 603-locking buckle; 604-locking groove; 605-first elastic member; 606-automatic release support block; 607-locking lever; 608-safety pin; 609-base; 6061-support surface; 6071-contact end; 6072-connecting end; 6091-slide rail;

[0038] 7-rear support assembly; 701-rear support frame; 702-limiting block; 703-support tail plate;

[0039] 8-supporting assembly; 801-tail pipe bracket; 802-rotating frame; 803-supporting plate; 804-gear lever; 805-second elastic member; 806-retractable supporting rod; 807-adjusting screw; 808-strip hole; 809-limiting rod;

[0040] 9-UAV; 901-ear pole;

[0041] 10-Rocket. DETAILED DESCRIPTION

[0042] The technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0043] The components of the embodiments of the present invention generally described and shown in the drawings herein may be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention.

[0044] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in the field without making any creative work shall fall within the scope of protection of the present invention.

[0045] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0046] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] In addition, the terms "horizontal", "vertical", "overhanging" and the like do not mean that the components are required to be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0048] It should be noted that the marine UAV launcher provided by the present invention is not limited to use in marine ships, but can also be used in other scenarios (for example: vehicles, airplanes, etc.).

[0049] like Figures 1 to 5 As shown, the present invention provides a marine-type UAV launcher, comprising: a support frame 1, a bottom bracket 2, a telescopic member 3, an angle adjustment assembly 4, a lifting frame 5, a front support assembly 6 and a rear support assembly 7; the two ends of the telescopic member 3 are rotatably connected to the support frame 1 and the bottom bracket 2 respectively, the number of the telescopic members 3 is multiple, and the multiple telescopic members 3 are arranged at intervals; the angle adjustment assembly 4 is arranged on the bottom bracket 2, and the angle adjustment assembly 4 is transmission-connected to the lifting frame 5; along the length direction of the lifting frame 5, the front support assembly 6 and the rear support assembly 7 The front support assembly 6 and the rear support assembly 7 are arranged at intervals on the lifting frame 5, and are both used to connect with the drone 9; the front support assembly 6 includes a front support frame 601, a pull rod 602 and a lock 603; the front support frame 601 is provided with a locking groove 604 for placing the ear rod 901 of the drone 9, the lock 603 is rotatably arranged on the front support frame 601, the pull rod 602 is connected to the lock 603, and the pull rod 602 can move along the length direction of the front support frame 601 so that the lock 603 locks or releases the ear rod 901.

[0050] In this embodiment, the support frame 1 is used to be fixed on the support surface 6061 (for example, the ground, the surface of a platform or the surface of a ship, etc.), and the front support assembly 6 and the rear support assembly 7 are respectively connected to the drone 9, so as to support the drone 9. The overall length of the telescopic member 3 is adjustable, and the telescopic member 3 is connected between the support frame 1 and the bottom bracket 2, and the telescopic member 3 is rotatably connected to the lifting frame 5 and the support plate, respectively. By adjusting the length of multiple telescopic members 3, the horizontality of the bottom bracket 2 can be adjusted to ensure that the horizontality of the bottom bracket 2 is within the set range, thereby ensuring the stability of the bottom bracket 2 and improving the stability of the drone 9. The accuracy of the horizontality of the bottom bracket 2 is guaranteed, and the stability of the drone 9 is guaranteed. On this basis, the lifting frame 5 is adjusted to the required angle through the angle adjustment assembly 4 so that the drone 9 reaches the set launch angle, and the accuracy of the launch angle of the drone 9 is improved, so that the accuracy of the drone 9 taking off according to the set trajectory is guaranteed.

[0051] Especially for marine-type UAV launchers used at sea, the shaking of the ship under the action of waves will cause the marine-type UAV launcher to shake, so the horizontality of the plane where the launch point of the UAV 9 is located is difficult to ensure, affecting the accuracy of the launch of the UAV 9. The marine-type UAV launcher provided in this embodiment can adjust the horizontality of the bottom bracket 2, so that the accuracy of the angle adjustment of the lifting frame 5 arranged thereon can still be guaranteed, thereby ensuring the accuracy of the launch angle of the UAV 9.

[0052] In addition, when the ear rod 901 is located in the locking groove 604, the lock buckle 603 can be driven by the pull rod 602 to move into the locking groove 604, thereby locking the ear rod 901 in the locking groove 604 to prevent the ear rod 901 from being separated from the locking groove 604. When the launch angle adjustment of the drone 9 is completed and the drone 9 is ready, the lock buckle 603 can move out of the locking groove 604 to release the ear rod 901, so that the ear rod 901 can be separated from the locking groove 604 to avoid affecting the movement of the drone 9. The lock buckle 603 can lock the ear rod 901, which can prevent external factors (such as wind or waves, etc.) from causing the sea-type drone launcher to shake and cause the earless rod 901 to be separated from the locking groove 604, thereby preventing the drone 9 from shifting or falling off, thereby ensuring the stability of the drone 9 and ensuring the accuracy of the drone 9 launch from another aspect.

[0053] Optionally, when the UAV 9 is installed on the marine UAV launcher, the UAV 9 is generally parallel to the lifting frame 5 (the plane where the center of the UAV 9 is located is parallel to the plane where the center of the lifting frame 5 is located, or it can be understood that the length direction of the UAV 9 is parallel to the length direction of the lifting frame 5). With this arrangement, the lifting angle of the lifting frame 5 is the launch angle of the UAV 9, and no further conversion is required, which facilitates control.

[0054] The marine type UAV launcher can include a level detection element (e.g., a detector or a sensor, etc.), and the level detection element can be fixed on the support surface 6061 or other external structures, or can be fixed on the support frame 1. The level detection element detects the level of the bottom bracket 2. The telescopic member 3 adopts an electrically controlled telescopic member 3, and the marine type UAV launcher can be provided with a control system, and the level detection element and the telescopic member 3 are both connected to the control system for communication, and the level detection element can transmit the detected information to the control system. After being processed by the control system, if the level is within the set level range, the telescopic member 3 does not need to work, and if the level is not within the set level range, the telescopic member 3 works until the level detection element detects that the bottom bracket 2 is within the set level range. Of course, the level detection element and the telescopic member 3 can also be connected to the back-end terminal for communication, and are uniformly controlled by the back-end terminal, for example, the control cabin on the ship.

[0055] Among them, the support frame 1 can be a frame structure, a block structure, a plate structure, or a combination of a frame structure and a block structure, a combination of a block structure and a plate structure, a combination of a frame structure and a plate structure, or a combination of a frame structure, a block structure, and a plate structure.

[0056] The bottom bracket 2 may be a frame structure or a block structure, and the optional bottom bracket 2 may be a bottom bracket plate 803 for easy assembly.

[0057] The telescopic member 3 may have various structural forms, for example, an electric telescopic rod, a motor screw mechanism, etc.

[0058] like Figures 1 to 3 As shown, on the basis of the above embodiment, further, when the front support assembly 6 is connected to the UAV 9, the length direction of the front support frame 601 intersects with the length direction of the lifting frame 5 (preferably, the front support frame 601 is perpendicular to the lifting frame 5, so that the front support frame 601 is arranged to support the UAV 9 more stably, and is also convenient for fixing and assembling), and the front support frame 601 is rotatably connected to the lifting frame 5; the front support assembly 6 also includes a first elastic member 605, which is connected between the front support frame 601 and the lifting frame 5, and the first elastic member 605 can drive the front support frame 601 to rotate toward the direction close to the lifting frame 5.

[0059] In this embodiment, when the front support frame 601 is in the supporting state, the first elastic member 605 reserves energy and has the ability to drive the front support frame 601 to rotate in the direction close to the lifting frame 5. When the drone 9 is launched, the front support frame 601 can rotate (rotate along the launch direction of the drone 9, which can be understood as the front support frame 601 rotating forward close to the lifting frame 5) during the process of the ear rod 901 disengaging from the locking groove 604, so that the ear rod 901 can be more smoothly disengaged from the locking groove 604, ensuring the smooth launch of the drone 9. The provision of the first elastic member 605 can reduce or even avoid the thrust of the ear rod 901 on the front support frame 601, thereby reducing or even avoiding the power consumption of the drone 9. When the ear rod 901 is disengaged from the locking groove 604 and the front support frame 601 loses its constraint, the first elastic member 605 can also push the front support frame 601 to rotate downward (close to the lifting frame 5) to move away from the drone 9, further avoiding affecting the movement of the drone 9.

[0060] A stopper may be provided in a direction away from the launch direction of the drone 9 (i.e., away from the front end of the lifting frame 5) to prevent the front support frame 601 from rotating backward in the supporting state, and the first elastic member 605 may push the front support frame 601 to rotate forward. The front support frame 601 may be directly provided on the front end wall of the lifting frame 5, and the end wall of the lifting frame 5 may form a stopper.

[0061] Among them, the first elastic member 605 can be a spring (tension spring or compression spring), and the spring is directly connected between the lifting frame 5 and the front support frame 601. Optionally, the first elastic member 605 is a torsion spring, and the rotation connection between the front support frame 601 and the lifting frame 5 is realized by a rotating shaft. The torsion spring is sleeved outside the rotating shaft. It can be understood that the two ends of the torsion spring are respectively connected to the lifting frame 5 and the front support frame 601. The use of a torsion spring can save the space occupied by the first elastic member 605.

[0062] On the basis of the above-mentioned embodiment, there may be various structural ways to realize that the lock 603 can lock and release the ear rod 901, for example: the front support assembly 6 also includes a main handle motor, a handle and a push rod, the push rod is provided with a protrusion, and the front support frame 601 is provided with a mounting hole. The handle motor drives the handle to rotate, and the handle passes through the mounting hole to be connected with the push rod to drive the push rod to rotate, thereby driving the protrusion to rotate so as to abut against the pull rod 602 to lift the pull rod 602. In this embodiment, the handle motor drives the handle to rotate in one direction (e.g., clockwise), the handle drives the push rod to rotate, the push rod drives the projection to rotate, the projection is separated from the pull rod 602, the pull rod 602 falls, and the lock 603 rotates into the locking groove 604, thereby locking the ear rod 901; the handle motor drives the handle to rotate in the reverse direction (e.g., counterclockwise), the handle drives the push rod to rotate, the push rod drives the projection to rotate, when the projection abuts against the pull rod 602, the pull rod 602 is immediately lifted, and the pull rod 602 can be set to drive the lock 603 to rotate in a direction away from the locking groove 604 when it is lifted, thereby releasing the ear rod 901. The lock 603 can lock the ear rod 901 when the drone 9 is parked or before launching, and when the drone 9 is ready to launch, the handle motor drives the handle to work, thereby realizing that the lock 603 releases the ear rod 901.

[0063] Among them, the turning handle is passed through the mounting hole to be connected with the push rod, so as to drive the push rod to rotate, thereby driving the protrusion to rotate so as to abut against the pull rod 602 to lift the pull rod 602. There can be various structural forms, for example: the pull rod 602 includes an outer tube and an inner tube, the inner tube can move up and down relative to the outer tube in the height length direction of the front support frame 601, the push rod is rotatably connected to the outer tube, the inner tube is connected to the lock buckle 603, the protrusion is located inside the outer tube, the protrusion can abut against the bottom of the inner tube, and the protrusion can push the inner tube to rise under the drive of the push rod. When the protrusion is separated from the inner tube, the inner tube descends; or, a connecting groove is provided at the bottom of the pull rod 602, and a sliding hole extending along the height length direction of the front support frame 601 is correspondingly provided on the side wall of the connecting groove, and the two ends of the top rod are respectively rotatably set in the two sliding holes, and the protrusion is located in the connecting groove and can abut against the bottom of the connecting groove. When the protrusion abuts against the bottom of the connecting groove, the pull rod 602 is pushed up, and when the protrusion is separated from the bottom of the connecting groove, the pull rod 602 descends. In this process, the top rod can move relatively along the sliding hole. Of course, other structures can also be used to achieve this, which will not be repeated here.

[0064] As an optional solution, the telescopic part 3 adopts a buffer electric cylinder, which has reliable adjustment and can also play a role in buffering and shock absorption. The vibration of the hull can be reduced by the buffer electric cylinder, thereby increasing the stability of the marine UAV launcher.

[0065] The number of telescopic members 3 can be set as required.

[0066] As an optional solution, the number of telescopic parts 3 is six, and the six telescopic parts 3 are arranged at intervals along the same annular direction (the annular shape is not a circular ring in the narrow sense, and can also be an elliptical ring, a quadrilateral ring, a triangular ring, etc.), and the two adjacent telescopic parts 3 are arranged at an acute angle (for example: 30°, 40°, 50°, 60°, 75° or 80°, etc.). In this way, the horizontality of the bottom bracket 2 can be better adjusted, and the bottom bracket 2 can be supported more stably, so that the support of the drone 9 is more stable.

[0067] More preferably, every two of the six telescopic parts 3 form a group, and the three groups of telescopic parts 3 can be respectively located at the three corners of the triangle, the telescopic parts 3 in the same group form a "V" shape, and the two adjacent telescopic parts 3 in two adjacent groups form an inverted "V" shape (for example, the first group is adjacent to the second group, and the telescopic parts 3 in the first group close to the second group form an inverted "V" shape with the telescopic parts 3 in the second group close to the first group). Such an arrangement can further improve the stability of the support for the drone 9.

[0068] As an alternative, Figure 2 and Figure 3 As shown, the front support assembly 6 also includes an automatic release support block 606 and a locking lever 607; the automatic release support block 606 is arranged on the lifting frame 5, and a support surface 6061 is formed on the automatic release support block 606, one end of the locking lever 607 is a contact end 6071, and the other end of the locking lever 607 is a connecting end 6072, and the weight of the contact end 6071 is greater than the weight of the connecting end 6072 (it can also be understood that the locking lever 607 is a heavy hammer structure); the middle part of the locking lever 607 is rotatably connected to the front support frame 601, and the connecting end 6072 can contact and disengage from the support surface 6061, and the connecting end 6072 is rotatably connected to the pull rod 602; when the contact end 6071 contacts the support surface 6061, the lock 603 locks the ear rod 901, and when the contact end 6071 disengages from the support surface 6061, the lock 603 releases the ear rod 901.

[0069] In this embodiment, the middle part of the locking lever 607 is rotatably connected to the front support frame 601, and the contact end 6071 of the locking lever 607 rises, and the connecting end 6072 of the locking lever 607 falls, so that the pull rod 602 falls, and the lock 603 locks the ear rod 901. When the contact end 6071 of the locking lever 607 falls, the connecting end 6072 of the locking lever 607 rises, so that the pull rod 602 rises, and the lock 603 releases the ear rod 901. When the front support frame 601 is in a supporting state, the contact end 6071 contacts the supporting surface 6061, and the support block 606 is automatically released to lift the contact end 6071, so that the connecting end 6072 falls, and the lock 603 locks the ear rod 901. When the drone 9 is launched, the ear rod 901 gradually disengages from the locking groove 604, and the front support rod gradually rotates forward and downward, then the contact end 6071 disengages from the support surface 6061, and the weight of the contact end 6071 is greater than the weight of the connection end 6072, then the contact end 6071 automatically falls, and the connection end 6072 automatically rises, so that the lock 603 automatically opens and releases the ear rod 901, avoiding affecting the launch of the drone 9. In this embodiment, the automatic locking of the ear rod 901 and the automatic release of the ear rod 901 by the lock 603 can be achieved through a mechanical mechanism, that is, the automatic closing and opening of the locking groove 604 by the lock 603, avoiding the use of control structures such as motors, on the one hand, making the structure of the front support assembly 6 simple and low in cost, on the other hand, avoiding vibration caused by the control structure when working, further ensuring the stability of the marine drone launcher and the stability of the drone 9.

[0070] As an alternative, Figure 3 As shown, the contact surface is arranged in an inclined surface, and the automatic release support block 606 is arranged to slide along the length direction of the lifting frame 5, so that the contact end 6071 can contact with the support surface 6061 at different positions, thereby achieving the lifting of the contact end 6071 to different heights, thereby achieving different degrees of falling of the pull rod 602, and then achieving the adjustment of the locking degree of the lock 603. For example: the automatic release support block 606 can move and adjust the position along the length direction of the lifting frame 5. When the front support frame 601 is in the supporting state, when the automatic release support block 606 moves toward the direction close to the locking lever 607, the contact surface contacts the higher position of the inclined surface, and the connection end 6072 drops a lot, the rotation amount of the locking buckle 603 into the locking groove 604 is large, and the locking degree of the locking buckle 603 is greater. Conversely, the locking degree of the locking buckle 603 can be reduced. This embodiment can adjust the locking degree of the locking buckle 603 through the sliding setting of the automatic release support block 606, so that it can be adjusted according to the specific launch situation, and the stability of the drone 9 can be improved.

[0071] The contact end 6071 is preferably arranged in an arc shape to facilitate the movement of the contact end 6071 along the support surface 6061 .

[0072] As an alternative, Figure 3 As shown, the pull rod 602 is a telescopic structure so as to be able to extend and retract in the length direction of the front support frame 601. The length of the pull rod 602 can determine the amount of the lock buckle 603 in the steering lock groove 604. When the length of the pull rod 602 is longer, the lock buckle 603 can be locked to a greater degree. When the length of the pull rod 602 is shorter, the lock buckle 603 can be locked to a lesser degree. That is, by making the length of the pull rod 602 retractable, the locking degree of the lock buckle 603 can be adjusted, and it can be adjusted according to the specific launch situation, which can further improve the stability of the drone 9.

[0073] Among them, the pull rod 602 can include a fixed tube and a sliding tube. The sliding tube slides along the fixed tube. Along the length direction of the sliding tube, a plurality of holes are provided on the sliding tube. The fixed tube is provided with spring balls, and the spring balls can be inserted into the corresponding holes. Optionally, the threaded telescopic structure (for example, the pull rod 602 is a double-headed stud structure) has a simple structure and can also achieve a wider range of length adjustment.

[0074] Only the automatic release support block 606 can be set to slide along the length direction of the lifting frame 5 to adjust the locking degree of the lock; only the pull rod 602 can be set as a telescopic structure to adjust the locking degree of the lock; and the automatic release support block 606 can be set to slide along the length direction of the lifting frame 5, and the pull rod 602 can be set as a telescopic structure to adjust the locking degree of the lock.

[0075] like Figure 2 and Figure 3 As shown, based on the above embodiment, further, the front support assembly 6 also includes a safety pin 608, and the safety pin 608 is connected between the lifting frame 5 and the front support frame 601 to lock the position of the front support frame 601 when supporting the drone 9.

[0076] In this embodiment, when the UAV 9 needs to be parked or does not need to be launched temporarily, the safety pin 608 can be connected between the lifting frame 5 and the front support frame 601 to fix the current position of the front support frame 601, thereby further improving the stability of the UAV 9.

[0077] As an alternative, Figure 2 and Figure 3 As shown, the front support frame 601 is rotatably connected to the front end wall of the lifting frame 5; the front support assembly 6 also includes a base 609, which is fixed to the front end of the lifting frame 5, and a slide rail 6091 is provided on the base 609, and the automatic release support block 606 is slidably set along the slide rail 6091; a first hole is provided on the base 609, and a second hole is provided on the front support frame 601, and a safety pin 608 is inserted into the first hole and the second hole.

[0078] Among them, the slide rail 6091 can be a slide groove, and the bottom of the automatic release support block 606 is directly slid into the slide groove; or the slide rail 6091 is a protrusion, and a corresponding slide groove is set at the bottom of the automatic release support block 606.

[0079] Optionally, the front support frame 601 may be symmetrically arranged on the left and right sides of the lifting frame 5, and correspondingly, the associated structures on the front support frame 601 are also symmetrically arranged, so that the support for the drone 9 is more stable.

[0080] The front support frame 601 can be a frame structure, a block structure, a plate structure, or a combination of a frame structure and a block structure, a combination of a block structure and a plate structure, a combination of a frame structure and a plate structure, or a combination of a frame structure, a block structure, and a plate structure.

[0081] like Figure 1 As shown, on the basis of the above embodiment, further, the angle adjustment component 4 includes a rotating drive member 401, a transmission member, a steering plate 405 and a pitch drive member 404; the plane where the steering plate 405 is located intersects with the vertical direction (preferably the steering plate 405 is perpendicular to the vertical direction. It should be noted that the vertical direction is generally vertical but not absolute, and errors are allowed to exist for the convenience of setting); the rotating drive member 401 is arranged on the bottom bracket 2, and the rotating drive member 401 is connected to the steering plate 405 through the transmission member to drive the steering plate 405 to rotate; one end of the lifting frame 5 is rotatably connected to the steering plate 405, one end of the pitch drive member 404 is rotatably connected to the steering plate 405, and the other end of the pitch drive member 404 is rotatably connected to the lifting frame 5.

[0082] In this embodiment, the rotating driving member 401 can drive the steering plate 405 to rotate in the horizontal direction (also understood as on the XY plane) through the transmission member, thereby driving the lifting frame 5 to rotate, and then driving the UAV 9 to rotate, and then adjusting the angle of the UAV 9 in the horizontal direction. The pitch driving member 404 (which can be an electric telescopic rod, a cylinder or an oil cylinder, etc.) works to drive one end of the lifting frame 5 to lift vertically (also understood as the Z axis), so that an angle is formed between the lifting frame 5 and the steering plate 405, thereby adjusting the launch angle of the UAV 9. The marine UAV launcher provided in this embodiment can not only adjust the pitch angle, but also adjust the angle of the UAV 9 in the plane, so that the launch accuracy of the UAV 9 can be higher.

[0083] Optionally, the steering plate 405 is parallel to the bottom bracket 2 to facilitate adjustment of the launch angle.

[0084] The pitch driving member 404 may be a cylinder, preferably an electric cylinder for easy control.

[0085] The rotating driving member 401 may be a rotary cylinder. Optionally, the rotating driving member 401 is a motor (more preferably a reduction motor).

[0086] The transmission member preferably includes a driving gear 402 and a driven gear 403 meshing with the driving gear 402; the driving gear 402 and the driving gear 403 are both rotatably arranged on the upper surface of the bottom bracket 2, and the lower surface of the steering plate 405 is fixedly connected to the driven gear 403 (the connection between the bottom bracket 2, the driven gear 403 and the steering plate 405 can be achieved through a slewing support), and the transmission is transmitted through the gear set, with precise control and smooth transmission. Preferably, the steering plate 405 is coaxially arranged with the driving gear 402.

[0087] like Figure 1 and Figure 4 As shown, based on the above embodiment, the rear support assembly 7 further includes a rear support frame 701, a limit block 702 and a support tail plate 703; the limit block 702 is provided with a limit groove extending along the length direction of the lifting frame 5, and the support tail plate 703 is slidably arranged in the limit groove, and the support tail plate 703 is used to be fixed on the drone 9.

[0088] In this embodiment, during the launch of the drone 9, the support tail plate 703 can slide along the limiting groove, and the limiting groove limits the movement of the support tail plate 703, so that the movement of the support tail plate 703 is stable, thereby making the launch of the drone 9 stable. The rear support assembly 7 in this embodiment can not only support the tail of the drone 9 before launching to ensure the stability of the drone 9, but also limit the movement of the drone 9 when the drone 9 is launched to improve the stability of the movement of the drone 9.

[0089] like Figure 1 , Figure 4 and Figure 5 As shown, on the basis of the above-mentioned embodiment, further, the marine-type UAV launcher also includes a supporting assembly 8, the supporting assembly 8 includes a tail tube bracket 801, a rotating frame 802, a support plate 803, a gear lever 804 and a second elastic member 805; the tail tube bracket 801 is fixed on the lifting frame 5, the rotating frame 802 is rotatably connected to the tail tube bracket 801, the support plate 803 is fixed on the rotating frame 802, the baffle is slidably arranged on the tail tube bracket 801 in a direction facing the rotating frame 802 (that is, the movement of the gear lever 804 can drive the rotating frame 802 to rotate), and the second elastic member 805 is connected between the tail tube bracket 801 and the rotating frame 802 to press the rotating frame against the gear lever 804; the support plate 803 is used to support the rocket 10.

[0090] In this embodiment, the supporting assembly 8 can support the rocket 10, thereby increasing the stability of the support for the UAV 9 before launching. The gear lever 804 can be moved to drive the rotating frame 802 to rotate, thereby driving the supporting plate 803 to rotate to a position that fits the rocket 10, thereby improving the stability of the support for the rocket 10, and further improving the stability of the support for the UAV 9. No matter which position the rotating frame 802 rotates to, the second elastic member 805 can always press the rotating frame 802 against the gear lever 804 to fix the current position of the rotating frame 802.

[0091] The second elastic member 805 may be a spring (tension spring or compression spring), which is directly connected between the rotating frame 802 and the tail pipe bracket 801. Optionally, the second elastic member 805 is a torsion spring, the rotating frame 802 is rotatably connected to the tail pipe bracket 801 via a connecting shaft, and the torsion spring is sleeved on the connecting shaft. It can be understood that the two ends of the torsion spring are respectively connected to the rotating frame 802 and the tail pipe bracket 801, and the torsion spring occupies less space.

[0092] Optionally, the support plate 803 is arranged in an arc shape so as to better fit the rocket 10 and support the rocket 10. A baffle is arranged at the rear of the support plate 803 to limit the tail end of the rocket 10.

[0093] like Figure 1 , Figure 4 and Figure 5 As shown, based on the above embodiment, the supporting assembly 8 further includes: a retractable supporting rod 806 (the retractable supporting rod 806 can optionally be a retractable rod with a double-headed stud structure), the retractable supporting rod 806 is connected between the rotating frame 802 and the support plate 803, and the height of the support plate 803 can be adjusted through the retractable supporting rod 806 to better fit the rocket 10.

[0094] like Figure 1 , Figure 3 and Figure 4 As shown, on the basis of the above embodiment, further, the supporting assembly 8 also includes an adjusting screw 807, the tail pipe bracket 801 includes relatively arranged side plates, the rotating frame 802 is rotatably connected between the two side plates, each side plate is provided with a strip hole 808, the two ends of the shift rod 804 are respectively slid into the two strip holes 808, and the wall of the side plate in the length direction of the strip hole 808 is provided with a through hole, and the adjusting screw 807 passes through the through hole and abuts against the shift rod 804.

[0095] In this embodiment, the position of the shift rod 804 is adjusted by rotating the adjusting screw 807, thereby adjusting the angle of the rotating frame 802, which is convenient for operation.

[0096] Furthermore, a limiting rod 809 may be provided on the tail pipe bracket 801 , and the limiting rod 809 is located on a side of the rotating frame 802 away from the shift rod 804 , so as to limit the rotation of the rotating frame 802 on the side where the limiting rod 809 is located.

[0097] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention is described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments can still be modified, or some or all of the technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention. In the description provided herein, a large number of specific details are described. However, it can be understood that the embodiments of the present invention can be practiced without these specific details. In some examples, well-known methods, structures and techniques are not shown in detail so as not to obscure the understanding of this description. In addition, those skilled in the art can understand that although some embodiments described herein include certain features included in other embodiments but not other features, the combination of features of different embodiments means being within the scope of the present invention and forming different embodiments.

Claims

1. A marine-type UAV launcher, characterized in that: include: Support frame, bottom bracket, telescopic member, angle adjustment assembly, lifting frame, front support assembly and rear support assembly; The two ends of the telescopic member are rotatably connected to the support frame and the bottom bracket respectively, and the number of the telescopic members is multiple, and the multiple telescopic members are arranged at intervals; The angle adjustment component is arranged on the bottom bracket, and the angle adjustment component is transmission-connected with the lifting frame; Along the length direction of the lifting frame, the front support assembly and the rear support assembly are arranged on the lifting frame at intervals, and the front support assembly and the rear support assembly are both used to connect with the drone; The front support assembly includes a front support frame, a pull rod and a lock; the front support frame is provided with a locking groove for placing the ear rod of the drone, the lock is rotatably set on the front support frame, the pull rod is connected to the lock, and the pull rod can move along the length direction of the front support frame so that the lock locks or releases the ear rod.

2. The marine-use UAV launcher according to claim 1 is characterized in that: The telescopic member is a buffer electric cylinder; The number of the telescopic parts is six, and each two of the six telescopic parts form a group. The three groups are respectively located at the three corners of the triangle. The two telescopic parts in the same group form a "V" shape, and the adjacent two telescopic parts in two adjacent groups form an inverted "V" shape.

3. The marine-use UAV launcher according to claim 1 or 2, characterized in that: When the front support assembly is connected to the drone, the length direction of the front support frame intersects with the length direction of the lifting frame, and the front support frame is rotatably connected to the lifting frame; The front support assembly also includes a first elastic member, which is connected between the front support frame and the lifting frame. The first elastic member can drive the front support frame to rotate towards the lifting frame.

4. The marine-use UAV launcher according to claim 3 is characterized in that: The front support assembly further comprises an automatic release support block and a locking lever; the automatic release support block is arranged on the lifting frame, a support surface is formed on the automatic release support block, one end of the locking lever is a contact end, the other end of the locking lever is a connecting end, and the weight of the contact end is greater than the weight of the connecting end; The middle part of the locking lever is rotatably connected to the front support frame, the connecting end can contact and disengage from the support surface, and the connecting end is rotatably connected to the pull rod; when the contact end contacts the support surface, the locking catch locks the ear rod, and when the contact end disengages from the support surface, the locking catch releases the ear rod.

5. The marine-use UAV launcher according to claim 4 is characterized in that: The contact surface is arranged in an inclined surface, and the automatic release support block is arranged to slide along the length direction of the lifting frame; And / or, the pull rod is a telescopic structure so as to be able to be telescopic in the length direction of the front support frame.

6. The marine-use UAV launcher according to claim 4 is characterized in that: The front support assembly also includes a safety pin, which is connected between the lifting frame and the front support frame to lock the position of the front support frame when supporting the drone.

7. The marine-use UAV launcher according to claim 6 is characterized in that: The front support frame is rotatably connected to the front end wall of the lifting frame; The front support assembly also includes a base, which is fixed to the front end of the lifting frame, and a slide rail is provided on the base, and the automatic release support block is slidably arranged along the slide rail; The base is provided with a first hole, the front support frame is provided with a second hole, and the safety pin is inserted into the first hole and the second hole.

8. The marine-use UAV launcher according to claim 1, characterized in that: The angle adjustment assembly includes a rotation drive member, a transmission member, a steering plate and a pitch drive member; the plane where the steering plate is located intersects with the vertical direction; The rotating driving member is arranged on the bottom bracket, and the rotating driving member is connected to the steering plate through the transmission member to drive the steering plate to rotate. One end of the lifting frame is rotatably connected to the steering plate, one end of the pitch driving member is rotatably connected to the steering plate, and the other end of the pitch driving member is rotatably connected to the lifting frame.

9. The marine-use UAV launcher according to claim 8, characterized in that: The pitch driving member is a pitch motor; And / or, the rotating driving member is a motor, and the transmission member includes a driving gear and a driven gear meshing with the driving gear; the driving gear and the driving gear are both rotatably arranged on the upper surface of the bottom bracket, and the lower surface of the steering plate is fixedly connected to the driven gear.

10. The marine-use UAV launcher according to claim 1, characterized in that: The rear support assembly includes a rear support frame, a limit block and a support tail plate; the limit block is provided with a limit groove extending along the length direction of the lifting frame, the support tail plate is slidably arranged in the limit groove, and the support tail plate is used to be fixed on the UAV; And / or, the marine-type UAV launcher further comprises a supporting assembly, wherein the supporting assembly comprises a tail tube bracket, a rotating frame, a supporting plate, a shift rod, a second elastic member, a retractable supporting rod, an adjusting screw and a limiting rod; The tail pipe bracket is fixed on the lifting frame, the rotating frame is rotatably connected to the tail pipe bracket, the support plate is fixed on the rotating frame, the shift lever is slidably arranged on the tail pipe bracket in a direction facing the rotating frame, and the second elastic member is connected between the tail pipe bracket and the rotating frame to press the rotating frame against the shift lever; The support plate is used to support the rocket; The retractable supporting rod is connected between the rotating frame and the supporting plate; The tail pipe bracket comprises side plates arranged opposite to each other, the rotating frame is rotatably connected between the two side plates, each of the side plates is provided with a strip hole, the two ends of the gear lever are respectively slidably arranged in the two strip holes, the wall of the side plate in the length direction of the strip hole is provided with a through hole, the adjusting screw passes through the through hole and abuts against the gear lever; The limiting rod is arranged on the tail pipe bracket and is located on a side of the rotating frame away from the shift rod.

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