A reciprocating ejection type unmanned aerial vehicle carrier and its use method

Abstract

The present invention provides a reciprocating ejection type UAV carrier vehicle, which includes a vehicle body, a launching platform, a sliding block, a first sliding rail, a fixed pulley, a locking mechanism, a winding mechanism, a feeding device, a locking mechanism, etc. The vehicle body has the advantage that, in the process of the vehicle body moving back and forth, the kinetic energy of the vehicle body itself can be used to provide elastic potential energy for a torsion reel to eject the UAV, thereby eliminating the need for the additional installation of an expensive ejection power device, and two UAVs can be launched in one reciprocating cycle, thereby improving the launching efficiency.

Description

Technical Field

[0001] The present invention belongs to the field of vehicle-mounted unmanned aerial vehicles, and in particular relates to a reciprocating ejection type unmanned aerial vehicle carrier vehicle and a use method thereof. Background Art

[0002] Existing drone carriers often have their own ejection devices for launching drones. However, for a carrier, setting up an ejection device requires an additional power device to provide power for launching drones, such as a steam power device or an electromagnetic power device, which is extremely costly, heavy, and takes up a lot of space, restricting the modification or manufacture of drone carriers. At the same time, if the ground conditions on which the car is located are not flat, it will affect the ejection of the drone and the accuracy of the process from the drone being loaded into the car body to the ejection device.

[0003] Therefore, there is a need for a drone carrier vehicle that can utilize the vehicle's own kinetic energy to launch a drone without the need for an additional launch power device, has a simple structure, high launch efficiency, and can adapt to rugged terrain to launch and load drones. Summary of the invention

[0004] The purpose of the present invention is to provide a drone carrier vehicle which can utilize the vehicle's own kinetic energy to launch a drone without the need for an additional launch power device, has a simple structure, high launch efficiency, and can adapt to rugged terrain to launch and load drones.

[0005] In order to solve the technical problems existing in the prior art, the present invention adopts the following technical solutions: a reciprocating catapult type UAV carrier, characterized in that: it includes a vehicle body, a top of which is provided with an arc-shaped groove; a launching platform, a bottom surface of which is a cylindrical surface and slidingly cooperates with the arc-shaped groove, and a top surface of which is an inclined surface with a lower front and a higher rear, two first slide rails for the UAV and the slider to slide are arranged side by side on the inclined surface, and a fixed pulley is connected to each of the left and right sides of the inclined surface; a locking mechanism cooperating with the slider is arranged between the two first slide rails; two winding mechanisms are respectively located on both sides of the vehicle body and fixed to the ground, one end of two pull ropes are wound on the winding mechanism, and the other end is connected to one side of the slider; a feeding device, used to lift the UAV to the rear end of the first slide rail so that it slides down to the slider under the influence of gravity; a locking mechanism is used to limit the relative movement between the vehicle body and the launching platform.

[0006] As a further solution of the present invention: the winding mechanism includes a torsion reel, a base and a first lifting rod, the base is fixed to the ground, the torsion reel is fixed to the base through the first lifting rod, one end of the pull rope is wound on the torsion reel, and the other end is connected to one side of the slider.

[0007] As a further solution of the present invention: the locking mechanism includes a base, a torsion spring and a rotating rod, the base is fixed between the two first sliding rails, the rotating rod is inclined toward the front of the vehicle and is hinged to the base through the torsion spring; two first grooves cooperating with the first sliding rails are provided under the sliding block, a second groove is provided between the two first grooves, and a locking rod cooperating with the rotating rod is fixed to the lower end of the second groove.

[0008] As a further solution of the present invention: a limiting block is fixed at the front end of the first slide rail; and a tension sensor is installed on the pull rope.

[0009] As a further solution of the present invention: multiple layers of second slide rails for placing the drone are arranged in the vehicle body, and the electric push plate is installed on the front part of the vehicle body through a second lifting rod.

[0010] As a further solution of the present invention: the loading device is arranged at the rear part of the vehicle body, and includes a third lifting rod, a fixed plate, a vertical rod, a spring, a rotating plate and a third slide rail, the third slide rail is fixed to the rotating plate, the rotating plate is connected to the upper end of the fixed plate through the spring and the vertical rod, the fixed plate is installed at the rear end of the vehicle body through the third lifting rod, wherein the spring is installed in front of the vertical rod, and the upper end of the vertical rod is hinged to the rotating plate through a ball joint seat; the rear end of the first slide rail is provided with a first inclined surface, and the front end of the third slide rail is provided with a second inclined surface matching the first inclined surface.

[0011] As a further solution of the present invention: a plurality of pin holes are circumferentially provided at the front end of the launch platform; the locking mechanism comprises a fixing seat fixed to the front end of the vehicle body, and a telescopic rod installed on the fixing seat cooperates with the pin holes.

[0012] As a further solution of the present invention: in the initial position, the fixed pulley is located directly above the torsion reel, at this time the slider and the drone are located at the lowest point of the first slide rail and the rotating rod hooks the locking rod, and the first lifting rod is used to adjust the height of the torsion reel so that the tension of the pull ropes on both sides is equal, and then the vehicle body reciprocates in front and behind the winding mechanism, and when the vehicle body moves forward or backward, the pull rope is driven to generate tension to rotate the torsion reel, and at the same time the rotating rod is flipped by the thrust of the locking rod until the rotating rod is disengaged from the locking rod, and the restoring force of the torsion reel drives the pull rope and the slider to launch the drone, and then the telescopic rod is inserted into the pin hole and the loading device loads a new drone, and the vehicle body moves in the opposite direction and launches a new drone on the other side of the initial position, thereby launching two drones in one reciprocating cycle.

[0013] Beneficial effects of the present invention:

[0014] 1. In the process of the vehicle body moving back and forth, the present invention uses the kinetic energy of the vehicle body itself to provide elastic potential energy for the torsion reel to catapult the UAV, thereby eliminating the need to install an additional expensive catapult power device.

[0015] 2. The present invention enables the vehicle body to reciprocate in the front and rear directions of the winding mechanism. Since the vehicle body can pull the torque reel to the limit and launch the drone when it moves forward to the farthest end in the front and moves backward to the farthest end in the rear, the vehicle body can launch two drones in one reciprocating cycle of forward and backward movement, thereby improving the launch efficiency.

[0016] 3. The locking mechanism provided in the present invention can automatically make the rotating rod hook the locking rod of the slider to complete the locking when the slider is at the lowest point in the initial position, so as to subsequently pull the torque reel to complete the energy storage; the advantage of the vehicle body moving back and forth is that the vehicle body must pass through the initial position in the process of moving from one end to the other end to complete the locking. During the operation, there is no need to deliberately find the initial position and stop the locking slider, thereby improving the operating efficiency.

[0017] 4. The present invention arranges the cylindrical bottom surface of the launch platform and the arc-shaped groove of the vehicle body to slide together, so as to ensure that when the ground is uneven and the vehicle body rolls, the launch platform can be automatically leveled under the influence of gravity, thereby preventing the tension of the pull ropes on both sides from being unequal and increasing the friction between the slider and the first slide rail.

[0018] 5. The present invention provides a first lifting rod for adjusting the height of the torsion reel on the uneven ground at the initial position until the tension of the pull ropes on both sides is the same, ensuring that the left and right torsion reels are located in the same horizontal plane.

[0019] 6. The present invention provides a loading device to load the UAV onto the first slide rail from the rear of the vehicle. By providing a spring, a vertical rod and a ball joint seat, and cooperating with the first inclined surface of the first slide rail and the second inclined surface of the third slide rail, two effects can be achieved when the third slide rail lifts and impacts the first slide rail: 1. The third slide rail is constrained by the first inclined surface to tilt and flip, and the spring is compressed, so that the UAV is thrown from the third slide rail into the first slide rail; 2. When the car is on an uneven road surface, the launch platform deflects relative to the vehicle body due to the automatic leveling function to generate a roll angle, so that the first slide rail deflects left and right relative to the third slide rail. The ball joint seat cooperates with the spring to enable the third slide rail to adaptively rotate left and right after contacting the first inclined surface, so that the third slide rail is aligned with the first slide rail.

[0020] 7. The telescopic rod of the locking device provided in the present invention cooperates with the pin hole, so that when the third slide rail impacts the first slide rail during the loading process of the loading device, the launching platform is prevented from being deflected left and right by the impact, thereby ensuring the loading stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1It is a schematic diagram of the overall structure of a reciprocating catapult type UAV carrier.

[0022] Figure 2 It is a schematic diagram of the partial structure of a reciprocating catapult type UAV carrier vehicle.

[0023] Figure 3 This is a schematic diagram of the internal structure of a reciprocating catapult type UAV carrier.

[0024] Figure 4 The present invention is a schematic diagram of a reciprocating ejection type UAV carrier vehicle loading device with a first slide rail for loading UAVs.

[0025] Figure 5 The present invention is a schematic diagram of a reciprocating ejection type UAV carrier vehicle with an electric push plate as a loading device for loading UAVs.

[0026] Figure 6a It is a schematic diagram of a reciprocating catapult type UAV carrier in an initial position.

[0027] Figure 6b It is a schematic diagram of a reciprocating ejection type UAV carrier moving to a forward ejection position.

[0028] Figure 6c It is a schematic diagram of a reciprocating ejection type UAV carrier launching a UAV at the front ejection position.

[0029] Figure 6d It is a schematic diagram of a reciprocating ejection type UAV carrier moving to the rear ejection position.

[0030] Figure 6e It is a schematic diagram of a reciprocating ejection type UAV carrier vehicle ejecting a UAV at the rear ejection position. DETAILED DESCRIPTION

[0031] The present invention will be described in detail below in conjunction with the accompanying drawings:

[0032] See attached Figure 1A reciprocating ejection type UAV carrier comprises a vehicle body 1, the top of which is provided with an arc-shaped groove; a launch platform 2, the bottom surface of which is a cylindrical surface and slides with the arc-shaped groove, the cylindrical axis corresponding to the arc-shaped groove surface is located above the center of gravity of the launch platform 2, and when the vehicle body 1 rolls due to uneven road surface, the launch platform 2 can automatically rotate to a horizontal position along the arc-shaped groove under the action of gravity, the top surface of the launch platform 2 is an inclined surface with a low front and a high rear, and two parallel first slide rails 4 for the UAV 3 and the slider 6 to slide are arranged side by side on the inclined surface, and the left and right sides of the inclined surface are A fixed pulley 5 is connected to each side; a locking mechanism cooperating with a slider 6 is arranged between the two first slide rails 4; two winding mechanisms are respectively located on both sides of the vehicle body 1 and fixed to the ground, one end of the two pull ropes 7 is wound in the winding mechanism, and the other end is connected to one side of the slider 6; a loading device is used to lift the UAV 3 to the rear end of the first slide rail 4, and then make the UAV 3 slide down to the slider 6 under the influence of gravity to complete the loading; a locking mechanism is used to limit the relative movement between the vehicle body 1 and the launching platform 2 to ensure the stability of the launching platform 2 during the loading process of the UAV 3.

[0033] The winding mechanism includes a torsion reel 8, a base 9 and a first lifting rod 10. The base 9 is fixed to the ground. The torsion reel 8 is fixed to the base 9 through the first lifting rod 10. One end of the pull rope 7 is wound on the torsion reel 8, and the other end is connected to one side of the slider 6. The torsion reel 8 will generate a restoring torque after being subjected to the torque brought by the pull rope 7.

[0034] See attached Figure 2 The locking mechanism includes a base 111, a torsion spring 112 and a rotating rod 113. The base 111 is fixed between the two first slide rails 4. The rotating rod 113 is hinged on the base 111 through the torsion spring 112, and the rotating rod 113 is tilted toward the front of the vehicle when in the balanced position; two first grooves 61 cooperating with the first slide rails 4 are provided below the slider 6, a second groove 62 is provided between the two first grooves 61, and a locking rod 63 cooperating with the rotating rod 113 is fixed at the lower end of the second groove 62; when the locking rod 63 moves forward with the slider 6 and passes through the rotating rod 113, the rotating rod 113 is forced to flip downward so that the locking rod 63 passes through, and when the locking rod 63 moves backward with the slider 6 and passes through the rotating rod 113, the rotating rod 113 hooks the locking rod 63 to prevent it from passing, until the pulling force of the pull rope 7 on the slider 6 is large enough, the rotating rod 113 is pushed to flip upward so that the locking rod 63 passes through.

[0035] A limit block 41 is fixed at the front end of the first slide rail 4 to limit the slider 6 ; a tension sensor is installed on the pull rope 7 so as to monitor the tension of the pull rope 7 .

[0036] See attached Figure 3, a plurality of layers of second slide rails 14 for placing the drone 3 are arranged in the vehicle body 1, and an electric push plate 16 is installed at the front of the vehicle body 1 through a second lifting rod 15. The feeding device is arranged at the rear of the vehicle body 1, and includes a third lifting rod 17, a fixed plate 18, a vertical rod 19, a spring 20, a rotating plate 21 and a third slide rail 22, the third slide rail 22 is fixed on the rotating plate 21, the rotating plate 21 is connected to the upper end of the fixed plate 18 through a spring 20 and the vertical rod 19, and the fixed plate 18 is installed at the rear end of the vehicle body 1 through the third lifting rod 17, wherein the spring 20 is installed in front of the vertical rod 19, the upper end of the vertical rod 19 is hinged to the rotating plate 21 through a ball joint seat, and the lower end of the vertical rod 19 is fixedly connected to the fixed plate 18; a first inclined surface is provided at the rear end of the first slide rail 4, and a second inclined surface matching the first inclined surface is provided at the front end of the third slide rail 22.

[0037] See attached Figure 4 , 5 , the electric push plate 16 pushes the drones 3 on the second slide rail 14 onto the third slide rail 22 in sequence. When the drones 3 on a certain layer are used up, the second lifting rod 15 adjusts the height of the electric push plate 16 to the second slide rail 14 of another layer, and the third lifting rod 17 also moves the third slide rail 22 to the second slide rail 14 of that layer to receive the drones 3. When it is necessary to load the drone 3 onto the first slide rail 4, the third lifting rod 17 pushes the third slide rail 22 to rise rapidly until the first inclined surface at the rear end of the first slide rail 4 collides with the second inclined surface at the front end of the third slide rail 22, and the first inclined surface exerts downward pressure on the second inclined surface, thereby compressing the spring 20, and the third slide rail 22 turns and tilts downward around the ball joint seat at the upper end of the vertical rod 19, and the rapid turning of the third slide rail 22 also throws the drone 3 above it to the first slide rail 4, and then the drone 3 slides down along the first slide rail 4 to the slider 6 under gravity to complete the loading.

[0038] See attached Figure 1 The front end of the launch platform 2 is provided with a plurality of pin holes 131 along the circumferential direction; the locking mechanism includes a fixing seat 12 fixed to the front end of the vehicle body 1, and a telescopic rod 13 mounted on the fixing seat 12 cooperates with the pin holes 131. The telescopic rod retracts into the fixing seat 12 during the movement of the vehicle body 1. When the loading device loads the first slide rail 4 with the drone 3, the telescopic rod 13 extends and inserts into the pin hole 131, thereby preventing the launch platform 2 from moving relative to the vehicle body 1, so that the launch platform 2 remains stable during the loading process.

[0039] The method of use of the present invention is as follows: Figure 6aAs shown, after the vehicle body 1 is driven to the launch site, the two bases 9 are fixed to the ground on both sides of the vehicle body 1, and the vehicle body 1 is adjusted to the initial position. At the initial position, the two fixed pulleys 5 are located directly above the two torque reels 8. At this time, the slider 6 and the drone 3 are located at the lowest point of the first slide rail 4 and the rotating rod 113 hooks the locking rod 63. The first lifting rod 10 is used to adjust the height of the torque reel 8 to the same horizontal line, and the tension of the pull ropes 7 on both sides is equal. At this time, the installation work is completed; Figure 6b As shown, the vehicle body 1 then moves forward. When the vehicle body 1 moves forward or backward, it can drive the pull rope 7 to generate tension to rotate the torsion reel 8. At the same time, the rotating rod 113 is pushed by the locking rod 63 and gradually turns over; Figure 6c As shown, until the vehicle body 1 moves forward to the farthest front end, the rotating rod 113 completely flips over and disengages from the locking rod 63, at which time the torsion reel 8 generates a restoring torque to reel in the pull rope 7, driving the slider 6 to launch the drone 3, and then the telescopic rod 13 is inserted into the pin hole 131 and the loading device is loaded with a new drone 3, and then the vehicle body 1 moves backward through the initial position and the rotating rod 113 automatically hooks the locking rod 63 again; Figure 6d , 6e As shown, the vehicle body 1 continues to retreat to the farthest rear end to launch a new UAV 3, and then the vehicle body 1 continues to move forward to start the next reciprocating cycle. Thus, the vehicle of the present invention launches two UAVs 3 in one reciprocating cycle.

[0040] The above examples are only used to illustrate the present invention, wherein the directions, structures, materials and connection methods of the components may be changed. Any equivalent transformations and improvements based on the technology of the present invention should not be excluded from the protection scope of the present invention.

Claims

1. A reciprocating ejection type UAV carrier, characterized in that: The invention comprises a vehicle body (1) having an arc-shaped groove on the top; a launching platform (2) having a cylindrical bottom surface and slidingly cooperating with the arc-shaped groove, and a top surface being an inclined surface with a lower front and a higher rear, wherein two first slide rails (4) for sliding of a drone (3) and a slider (6) are arranged side by side on the inclined surface, and a fixed pulley (5) is connected to each of the left and right sides of the inclined surface; a locking mechanism cooperating with the slider (6) is arranged between the two first slide rails (4); two winding mechanisms respectively located on both sides of the vehicle body (1) and fixed to the ground, one end of two pull ropes (7) being wound on the winding mechanism and the other end being connected to one side of the slider (6); and a feeding device for lifting the drone (3) to the rear end of the first slide rail (4) so ​​that the drone (3) can be launched. It slides down to the slider (6) under the influence of gravity; a locking mechanism is used to limit the relative movement between the vehicle body (1) and the launch platform (2); the winding mechanism comprises a torsion reel (8), a base (9) and a first lifting rod (10), the base (9) is fixed to the ground, the torsion reel (8) is fixed to the base (9) through the first lifting rod (10), one end of the pull rope (7) is wound on the torsion reel (8), and the other end is connected to one side of the slider (6); the locking mechanism comprises a base (111), a torsion spring (112) and a rotating rod (113), the base (111) is fixed between the two first slide rails (4), and the rotating rod (113) is inclined toward the front direction of the vehicle and is rotated by the torsion spring (112). 112) is hinged on the base (111); two first grooves (61) cooperating with the first slide rail (4) are provided below the slider (6), a second groove (62) is provided between the two first grooves (61), a locking rod (63) cooperating with the rotating rod (113) is fixed at the lower end of the second groove (62); a limit block (41) is fixed at the front end of the first slide rail (4); a tension sensor is installed on the pull rope (7); multiple layers of second slide rails (14) for placing the drone (3) are provided in the vehicle body (1), and an electric push plate (16) is installed on the front part of the vehicle body (1) through a second lifting rod (15); the feeding device is arranged at the rear part of the vehicle body (1), and includes a third lifting rod (15) and a second lifting rod (16). A lowering rod (17), a fixed plate (18), a vertical rod (19), a spring (20), a rotating plate (21) and a third slide rail (22), wherein the third slide rail (22) is fixed on the rotating plate (21), the rotating plate (21) is connected to the upper end of the fixed plate (18) through the spring (20) and the vertical rod (19), the fixed plate (18) is installed on the rear end of the vehicle body (1) through the third lifting rod (17), wherein the spring (20) is installed in front of the vertical rod (19), and the upper end of the vertical rod (19) is hinged to the rotating plate (21) through a ball joint seat; the rear end of the first slide rail (4) is provided with a first inclined surface, and the front end of the third slide rail (22) is provided with a second inclined surface matching the first inclined surface.

2. The reciprocating ejection type UAV carrier according to claim 1, characterized in that: The front end of the launch platform (2) is provided with a plurality of pin holes (131) along the circumferential direction; the locking mechanism comprises a fixing seat (12) fixed to the front end of the vehicle body (1), and a telescopic rod (13) mounted on the fixing seat (12) cooperates with the pin holes (131).

3. A method for using a reciprocating ejection type UAV carrier, characterized in that: A catapult-type UAV carrier vehicle comprising the method of claim 2, wherein the fixed pulley (5) is located directly above the torque reel (8) in the initial position, the slider (6) and the UAV (3) are located at the lowest point of the first slide rail (4) and the rotating rod (113) hooks the locking rod (63), and the height of the torque reel (8) is adjusted using the first lifting rod (10) to make the tension of the pull ropes (7) on both sides equal, and then the vehicle body (1) reciprocates in front of and behind the winding mechanism, and when the vehicle body (1) moves forward or backward, the pull rope (7) is driven to generate tension to make the vehicle body (1) move forward or backward. The torsion reel (8) rotates, and at the same time, the rotating rod (113) is overturned by the thrust of the locking rod (63), until the rotating rod (113) is separated from the locking rod (63), and the restoring force of the torsion reel (8) drives the pull rope (7) and the slider (6) to eject the drone (3), after which the telescopic rod (13) is inserted into the pin hole (131) and the loading device loads a new drone (3), and the vehicle body (1) moves in the opposite direction and launches a new drone (3) on the other side of the initial position, thereby launching two drones (3) in one reciprocating cycle.

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