A rotating ejection type UAV carrier

Abstract

The present invention relates to a rotary ejection type UAV carrier vehicle, comprising a vehicle body, a shaft rod being fixed on the top of the vehicle body; a lifting plate, a through hole being opened on the vehicle body and a sleeve being fixed on the top, the shaft rod being slidably matched with the through hole and the sleeve; the lifting plate being connected to the top of the vehicle body through a spring; the inner ring of an upper ball bearing being fixed to the upper end of the shaft rod, and the inner ring of a lower ball bearing being fixed to the sleeve; two groups of folding frames, each group of folding frames comprising a long rod and a short rod, a launcher and a fixture capable of installing a UAV being fixed on the upper end of the long rod of one group of folding frames, a counterweight being fixed on the upper end of the long rod of the other group of folding frames, and a lifting assembly, thereby realizing the function of the carrier vehicle to perform rotary ejection on the UAV.

Description

Technical Field

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

[0002] Existing unmanned aircraft carriers often have built-in ejection devices for launching drones. However, most of the existing ejection devices are linear ejection devices, and rotary ejection ejection devices are rarely used, such as the patent document with publication number CN202175200U. The reasons are: 1. The rotary ejection ejection device requires a high-power rotating motor to provide rotational kinetic energy, but it is difficult for drone carriers to carry high-power rotating motors; 2. A large amount of energy is wasted on the kinetic energy of the counterweight of the rotary ejection ejection device, and the kinetic energy obtained by the drone itself accounts for a small proportion, resulting in low energy utilization; 3. When the rotation speed is sufficient, there is a lack of a simple and reliable way to eject the drone and make the drone detach from the ejection device; 4. Since the movement direction of the drone changes repeatedly during the rotation process, it is difficult to set the launch direction of the drone; 5. There is a lack of a simple and effective method to move the drone from the vehicle body to the rotary ejection ejection device.

[0003] Therefore, there is a need for a rotary ejection type UAV carrier which can utilize the vehicle's own kinetic energy to increase the UAV launch speed, has high energy utilization, can set the launch direction of the UAV, and is convenient for loading the UAV onto a ejection device. Summary of the invention

[0004] The purpose of the present invention is to provide a rotary ejection type UAV carrier vehicle which can utilize the vehicle's own kinetic energy to increase the UAV launch speed, has high energy utilization, can set the launch direction of the UAV and is convenient for loading the UAV onto a ejection device.

[0005] In order to solve the technical problems existing in the prior art, the present invention adopts the following technical solutions: a rotary ejection type UAV carrier, characterized in that it includes a vehicle body, a shaft rod is fixed on the top of the vehicle body; a lifting plate, a through hole is opened on the vehicle body and a sleeve is fixed on the top, the shaft rod is slidably matched with the through hole and the sleeve; the lifting plate is connected to the top of the vehicle body through a spring; the inner ring of the upper ball bearing is fixed to the upper end of the shaft rod, and the inner ring of the lower ball bearing is fixed to the sleeve; two groups of folding frames, each group of the folding frames includes a long rod and a short rod, the upper end of the short rod is hinged to the outer ring of the upper ball bearing, the lower end is hinged to the middle part of the long rod, the lower end of the long rod is hinged to the outer ring of the lower ball bearing, the upper end of the long rod of one group of folding frames is fixed with a launcher and a fixture capable of installing a UAV, and the upper end of the long rod of the other group of folding frames is fixed with a counterweight; a lifting assembly fixed to the road surface is used to drive the lifting plate to rise and fall when the vehicle body moves.

[0006] As a further solution of the present invention: it includes a plurality of guide shafts fixed on the top of the vehicle body, and the guide shafts are slidably matched with the guide holes opened on the lifting plate.

[0007] As a further solution of the present invention: it includes a first rotating motor fixed on the lifting plate, and a gear is fixed on the output end of the first rotating motor; an outer gear ring is arranged on the outer ring of the lower ball bearing, and the gear is meshed with the outer gear ring.

[0008] As a further solution of the present invention: the lifting assembly includes a base, an electric telescopic rod and a guide rope, the four bases are respectively fixed to the ground at the right front, right rear, left front and left rear of the vehicle body, and each of the bases is fixed with an electric telescopic rod; a guide wheel is installed on each of the left and right sides of the lifting plate, and a guide rope is provided on each of the left and right sides of the vehicle body, and the two guide ropes are respectively matched with the two guide wheels; the two ends of the guide rope on the right side are respectively connected to the output ends of the electric telescopic rod corresponding to the base at the right front and right rear, and the two ends of the guide rope on the left side are respectively connected to the output ends of the electric telescopic rod corresponding to the base at the left front and left rear.

[0009] As a further solution of the present invention: the drone includes a fuselage and a matching part, the matching part is composed of a vertical plate and a horizontal plate, the upper end of the vertical plate is connected to the fuselage, and the lower end is connected to the front end of the horizontal plate, and the horizontal plate is arranged along the length direction of the fuselage.

[0010] As a further solution of the present invention: the fixer is a hollow tube, the inner wall of the hollow tube is slidably matched with the horizontal plate, and a horizontal slit is opened through the hollow tube on the side close to the shaft rod; the launcher includes a rotating plate and a fixed column, the lower end of the fixed column is connected to the long rod, and the upper end is hinged to the middle part of the rotating plate; one end of the rotating plate passes through the horizontal slit and can move laterally inside the hollow tube; a second rotating motor is fixed to the top of the shaft rod, and its output end is connected to a blocking block via a connecting rod.

[0011] As a further solution of the present invention: a placement plate for storing the drone is fixed in the vehicle body, and the placement plate is penetrated along the length direction with a sliding slot that slidably cooperates with the matching part; a cylinder is arranged at one end of the placement plate, and a push plate is fixed to the output end of the cylinder; the other end of the placement plate is adjacent to the carrier plate, and the end of the carrier plate close to the placement plate is an inlet end with a moving slot, the moving slot is connected to the sliding slot, and the moving slot is slidably cooperated with the matching part, and the other end of the carrier plate is a closed end; an electric lifting rod is fixed in the vehicle body, and the lower part of the inlet end of the carrier plate is connected to the output end of the electric lifting rod through a third rotating motor.

[0012] The present invention provides a folding frame to drive the UAV to rotate around the shaft. When the folding frame is retracted, the rotation radius of the UAV decreases. According to the principle of conservation of angular momentum, the angular velocity and linear velocity of the UAV's circular motion will be increased, thereby increasing the initial launch velocity of the UAV.

[0013] The present invention uses a simple structure in which a guide rope fixed at both ends cooperates with a guide wheel, so that when the vehicle body moves forward, the guide wheel drives the lifting plate to move in an elliptical trajectory to lower the lifting plate, thereby driving the folding frame to contract and thereby increasing the linear speed of the UAV movement. This process of the lifting component essentially achieves the effect of converting the forward kinetic energy of the vehicle body into the kinetic energy of the UAV movement, so that the vehicle's own driving power device can also participate in the process of providing the initial velocity for the UAV, thereby reducing the power requirement for the first rotating motor.

[0014] The present invention uses a hollow tube and a matching part to fix the drone on the folding frame, and uses a rotating plate to cooperate with a blocking block, so that when the folding frame is retracted to a certain extent, one end of the rotating plate collides with the blocking block, so that the other end of the rotating plate pushes the drone out of the hollow tube and launches it; this process can realize the launch of the drone through a simple mechanical structure; at the same time, in this process, the folding frame and the counterweight block slow down and the drone accelerates, which essentially realizes the transfer of kinetic energy from the folding frame and the counterweight block to the drone, reducing the energy wasted on the counterweight block.

[0015] In the present invention, since the UAV detaches from the hollow tube and is launched after the rotating plate collides with the blocking block, the position of the blocking block can directly determine the launch position and launch direction of the UAV. By setting a second rotating motor to control the position of the blocking block, the launch position and launch direction of the UAV can be controlled and adjusted, thereby enabling the UAV to be launched in multiple directions.

[0016] After the carrier plate of the present invention receives the UAV from the placement plate, the placement plate is rotated at high speed by the third rotating motor, so that the UAV performs a circular motion and slides along the moving gap to the closed end under the action of centrifugal force, thereby positioning the UAV at the closed end, making it easier for the folding frame to accurately transfer the UAV from the carrier plate to the hollow tube during the rotation process. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of a rotating ejection type UAV carrier.

[0018] Figure 2 It is a partial structural schematic diagram of a rotary ejection type UAV carrier.

[0019] Figure 3 It is a schematic diagram of the internal structure of a rotating ejection type UAV carrier.

[0020] Figure 4It is a side view of the internal structure of a rotary ejection type UAV carrier.

[0021] Figure 5a It is a schematic diagram of the initial state of a rotating ejection type UAV carrier.

[0022] Figure 5b It is a schematic diagram of a rotating ejection type UAV carrier vehicle's carrier plate lifting a UAV.

[0023] Figure 5c It is a schematic diagram of a rotary ejection type drone carrier transferring a drone from a carrier plate to a hollow tube.

[0024] Figure 5d It is a schematic diagram of a folding frame of a rotating ejection type UAV carrier driving the UAV to rotate.

[0025] Figure 5e It is a schematic diagram of a rotating ejection type UAV carrier vehicle in which the body moves to drive the folding frame to retract and eject the UAV. DETAILED DESCRIPTION

[0026] The present invention will be described in detail below in conjunction with the accompanying drawings:

[0027] See attached Figure 1 , Figure 5a A rotary ejection type UAV carrier comprises a vehicle body 1, on the top of which a shaft rod 2 is fixed; a lifting plate 3, which is provided with a through hole and on which a sleeve 4 is fixed, through which the shaft rod 2 passes and slides with the sleeve 4; the lifting plate 3 is connected to the top of the vehicle body 1 through a spring 35; the inner ring of the upper ball bearing 51 is fixed to the upper end of the shaft rod 2, and the inner ring of the lower ball bearing 52 is fixed to the sleeve 4; two sets of folding frames, each set of folding frames comprises a long rod 61 and a short rod 62, the upper end of the short rod 62 is hinged to the outer ring of the upper ball bearing 51, and the lower end is hinged to the middle part of the long rod 61, and the lower end of the long rod 61 is hinged to the outer ring of the lower ball bearing 52, A transmitter and a fixture for mounting the UAV 7 are fixed to the upper end of the long rod 61 of one group of folding frames, and a counterweight 9 is fixed to the upper end of the long rod 61 of the other group of folding frames for maintaining balance during rotation; a first rotating motor 32 is fixed to the lifting plate 3, a gear 33 is fixed to the output end of the first rotating motor 32, an outer gear ring is provided on the outer ring of the lower ball bearing 52, the gear 33 is meshed with the outer gear ring, so that the first rotating motor 32 can drive the outer ring of the lower ball bearing 52 to rotate, and then drive the two groups of folding frames and the UAV 7 to rotate around the shaft 2; it also includes a lifting component fixed to the road surface, which is used to drive the lifting plate 3 to rise and fall when the vehicle body 1 moves.

[0028] A plurality of guide shafts 31 are fixed on the top of the vehicle body 1 , and the guide shafts 31 are slidably matched with guide holes provided on the lifting plate 3 , so as to guide the lifting movement of the lifting plate 3 .

[0029] When the lifting plate 3 descends along the shaft 2, the lower ball bearing 52 is driven to descend and the distance between the lower ball bearing 52 and the upper ball bearing 51 increases, thereby driving the folding frame to retract inward. During this process, the distance between the drone 7 and the shaft 2 decreases, thereby reducing the radius of the circular motion of the drone 7 around the shaft 2.

[0030] The lifting assembly includes a base 10, an electric telescopic rod 11 and a guide rope 12. The four bases 10 are respectively fixed to the ground at the right front, right rear, left front and left rear of the vehicle body 1, and an electric telescopic rod 11 is fixed to each base 10; a guide wheel 34 is installed on the left and right sides of the lifting plate 3, and a guide rope 12 is provided on the left and right sides of the vehicle body 1, and the two guide ropes 12 are respectively slidably matched with the two guide wheels 34; the two ends of the right guide rope 12 are respectively connected to the output ends of the electric telescopic rod 11 corresponding to the right front and right rear bases 10, and the two ends of the left guide rope 12 are respectively connected to the output ends of the electric telescopic rod 11 corresponding to the left front and left rear bases 10; the spacing between the two guide wheels 34 is equal to the spacing between the two front electric telescopic rods 11 and the spacing between the two rear electric telescopic rods 11. As shown in the attached figure Figure 5e As shown, when the vehicle body 1 moves forward and backward, the guide wheel 34 rolls along the guide rope 12. From the definition of an ellipse, it can be seen that the motion trajectory of the guide wheel 34 is an ellipse with the output ends of the front and rear electric telescopic rods 11 as the focus. When the vehicle body 1 moves forward from the midpoint between the front and rear bases 10, the guide wheel 34 will drive the lifting plate 3 to descend.

[0031] As attached Figure 2 As shown, the drone 7 includes a fuselage 71 and a matching portion 72. The matching portion 72 is composed of a vertical plate and a horizontal plate. The upper end of the vertical plate is connected to the fuselage 71, and the lower end is connected to the front end of the horizontal plate. The horizontal plate is arranged along the length direction of the fuselage 71; the matching portion 72 is made of elastic material.

[0032] The fixer is a hollow tube 8, the inner wall of which is in sliding cooperation with the horizontal plate, so that the horizontal plate of the drone 7 can be inserted into the hollow tube 8, and a horizontal slit 83 is provided through the hollow tube 8 on the side close to the shaft 2; the launcher comprises a rotating plate 81 and a fixing column 82, the lower end of the fixing column 82 is fixedly connected to the long rod 61, and the upper end is hinged to the middle part of the rotating plate 81; one end of the rotating plate 81 passes through the horizontal slit 83 and can move laterally inside the hollow tube 8, and when the horizontal plate of the drone 7 is inserted into the hollow tube 8, one end of the rotating plate 81 contacts the rear end of the horizontal plate of the drone 7; a second rotating motor 85 is fixed to the top of the shaft 2, and its output end A blocking block 84 is connected via a connecting rod 86; when the lifting plate 3 is in the initial position, the end of the rotating plate 81 close to the shaft rod 2 is far away from the blocking block 84, so that the rotating plate 81 will not collide with the blocking block 84 during the rotation around the shaft rod 2. However, when the lifting plate 3 descends and the folding frame contracts, the distance between the rotating plate 81 and the shaft rod 2 gradually decreases until the end of the rotating plate 81 close to the shaft rod 2 collides with the blocking block. At this time, the rotating plate 81 rotates relative to the fixed column 82, so that the end of the rotating plate 81 in contact with the horizontal plate moves along the horizontal seam 83 to push the horizontal plate out of the hollow tube 8, thereby completing the ejection of the drone 7.

[0033] As attached Figure 3 , 4 As shown, a placement plate 14 for storing a plurality of drones 7 is fixed in the vehicle body 1, and a sliding slit 141 is provided along the length direction of the placement plate 14 to slide with the matching portion 72 of the drone 7; a cylinder 17 is provided at one end of the placement plate 14, and a push plate 18 is fixed at the output end of the cylinder 17 to push the drone 7 along the sliding slit 141; the other end of the placement plate 14 is adjacent to the carrier plate 13, and the end of the carrier plate 13 close to the placement plate 14 is an inlet end 131 with a moving slit 132, the moving slit 132 is butted with the sliding slit 141, and the moving slit 132 is slidably matched with the matching portion 72, and the other end of the carrier plate 13 away from the placement plate 14 is a closed end 133; an electric lifting rod 15 is fixed in the vehicle body 1, and the lower part of the inlet end 131 of the carrier plate 13 is connected to the output end of the electric lifting rod 15 through a third rotating motor 16, and the third rotating motor 16 is located on one side of the moving slit 132.

[0034] The method of use of the present invention is as follows: Figure 5a As shown, after the vehicle body 1 is driven to the specified launch site, the cylinder 17 is started to push the UAV 7 from the placement plate 14 to the inlet end 131 of the carrier plate 13, and at the same time, the four bases 10 are respectively fixed to the ground at the right front, right rear, left front and left rear of the vehicle body 1, and the four electric telescopic rods 11 are started so that their output ends are located on the same horizontal plane to avoid adverse effects caused by uneven ground. The initial position of the guide wheel 34 is located above the midpoint between the front and rear bases 10, and the second rotating motor 85 is started to move the blocking block 84 to the desired position; as shown in the attached figure Figure 5b As shown, the electric lifting rod 15 drives the carrier plate 13 to rise until the matching portion 72 of the UAV 7 and the hollow tube 8 are at the same height. At this time, the third rotating motor 16 is started and drives the carrier plate 13 to rotate at high speed around the vertical axis, so that the UAV 7 moves along the moving gap 132 to the closed end 133 under the action of centrifugal force; as shown in the attached figure Figure 5c As shown, the third rotating motor 16 then stops rotating, and the horizontal plate of the drone 7 is arranged tangentially along the moving track of the hollow tube 8, and then the first rotating motor 32 is started to drive the folding frame and the hollow tube 8 to make a circular motion around the shaft 2. When the hollow tube 8 passes through the horizontal plate of the drone 7, the hollow tube 8 covers the horizontal plate and drives the drone 7 to leave the carrier plate 13 along the moving gap 132, thereby completing the loading of the drone 7; as shown in the attached Figure 5d As shown, the electric lifting rod 15 drives the carrier plate 13 to descend, the third rotating motor 16 drives the carrier plate 13 to reset, and the first rotating motor 32 is adjusted to the maximum output power to drive the drone 7 and the folding frame to rotate rapidly around the shaft 2. At this time, the rotating plate 81 is far away from the blocking block 84, so the rotating plate 81 will not hit the blocking block 84 during the circular motion around the shaft 2; as shown in the attached Figure 5e As shown, the vehicle body 1 then moves forward, during which the guide wheel 34 is acted upon by the guide rope 12 to move in an elliptical trajectory. Since the initial position of the guide wheel 34 is located at the highest point of the elliptical trajectory, the guide wheel 34 descends along the elliptical trajectory as the vehicle body 1 moves forward, and the lifting plate 3 descends along with the guide wheel 34 and compresses the spring 35 below. At this time, the lower ball bearing 52 descends with the lifting plate and the distance between the lower ball bearing 52 and the upper ball bearing 51 increases, thereby driving the folding frame to retract inward. During this process, the distance between the drone 7 and the shaft 2 decreases, thereby reducing the radius of the circular motion of the drone 7 around the shaft 2. Based on the principle of conservation of angular momentum, when the angular momentum remains unchanged, the linear velocity of a particle performing circular motion is inversely proportional to its motion radius. Therefore, the linear velocity of the drone 7 increases as its circular motion radius decreases. In this process, the first acceleration of the UAV 7 is achieved. From the perspective of energy transfer, the kinetic energy of the acceleration of the UAV 7 comes from the work done by the lifting plate 3 moving downward when the vehicle body 1 moves forward; during the inward contraction of the folding frame, the radius of the circular motion of the rotating plate 81 becomes smaller and smaller, until the end of the rotating plate 81 close to the shaft 2 collides with the blocking block 84, at which time the rotating plate 81 rotates around the fixed column so that the end of the rotating plate 81 located in the hollow tube 8 moves along the transverse seam and pushes the UAV 7 out of the hollow tube 8, thereby completing the ejection of the UAV 7; in the process of the rotating plate 81 pushing the UAV 7, the UAV 7 accelerates for the second time while the folding frame and the counterweight 9 decelerate. From the perspective of energy transfer, the kinetic energy of the folding frame and the counterweight 9 is transferred to the UAV 7 during this process. The present invention realizes the two accelerations of the UAV 7 during the rotating ejection process, greatly improving the initial launch velocity of the UAV 7.

[0035] 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 rotating ejection type UAV carrier, characterized in that: The invention comprises a vehicle body (1) having a shaft (2) fixed on the top thereof; a lifting plate (3) having a through hole and a sleeve (4) fixed on the top thereof, wherein the shaft (2) is slidably matched with the through hole and the sleeve (4); the lifting plate (3) is connected to the top of the vehicle body (1) via a spring (35); the inner ring of an upper ball bearing (51) is fixed to the upper end of the shaft (2), and the inner ring of a lower ball bearing (52) is fixed to the sleeve (4); two sets of folding frames, each set of the folding frames comprising a long rod (61) and a short rod (62), the upper end of the short rod (62) being connected to the upper ball bearing (51) and the inner ring of a lower ball bearing (52) being fixed to the sleeve (4); and The outer ring of the ball bearing (51) is hinged, and the lower end is hinged to the middle part of the long rod (61); the lower end of the long rod (61) is hinged to the outer ring of the lower ball bearing (52); the upper end of the long rod (61) of one group of folding frames is fixed with a transmitter and a fixture capable of mounting a drone (7); the upper end of the long rod (61) of another group of folding frames is fixed with a counterweight (9); a lifting assembly fixed to the road surface is used to drive the lifting plate (3) to rise and fall when the vehicle body (1) moves; it includes a plurality of guide shafts (31) fixed to the top of the vehicle body (1); the guide shafts (31) are connected to the upper end of the long rods (61) of the folding frames; The lifting plate (3) is provided with a guide hole for sliding engagement with the lifting plate (3); the lifting plate (3) comprises a first rotating motor (32) fixed on the lifting plate (3), the output end of which is fixed with a gear (33); an outer gear ring is provided on the outer ring of the lower ball bearing (52), and the gear (33) meshes with the outer gear ring; the lifting assembly comprises a base (10), an electric telescopic rod (11) and a guide rope (12); four bases (10) are respectively fixed to the ground at the right front, right rear, left front and left rear of the vehicle body (1), and each base (10) is fixed with a An electric telescopic rod (11); a guide wheel (34) is installed on each of the left and right sides of the lifting plate (3); a guide rope (12) is installed on each of the left and right sides of the vehicle body (1); the two guide ropes (12) are respectively matched with the two guide wheels (34); the two ends of the guide rope (12) on the right side are respectively connected to the output ends of the electric telescopic rod (11) corresponding to the right front and right rear bases (10); the two ends of the guide rope (12) on the left side are respectively connected to the output ends of the electric telescopic rod (11) corresponding to the left front and left rear bases (10).

2. The rotary projectile type UAV carrier according to claim 1, characterized in that: The drone (7) comprises a fuselage (71) and a matching portion (72), wherein the matching portion (72) is composed of a vertical plate and a horizontal plate, wherein the upper end of the vertical plate is connected to the fuselage (71), and the lower end is connected to the front end of the horizontal plate, and the horizontal plate is arranged along the length direction of the fuselage (71).

3. The rotary projectile type UAV carrier according to claim 2, characterized in that: The fixer is a hollow tube (8), the inner wall of the hollow tube (8) is slidably matched with the transverse plate, and a transverse slit (83) is formed through the hollow tube (8) on a side close to the shaft (2); the launcher comprises a rotating plate (81) and a fixing column (82), the lower end of the fixing column (82) is connected to the long rod (61), and the upper end is hinged to the middle part of the rotating plate (81); one end of the rotating plate (81) passes through the transverse slit (83) and can move laterally inside the hollow tube (8); a second rotating motor (85) is fixed to the top end of the shaft (2), and the output end of the second rotating motor (85) is connected to a blocking block (84) via a connecting rod (86).

4. The rotary projectile type UAV carrier according to claim 3, characterized in that: A placement plate (14) for storing the drone (7) is fixed in the vehicle body (1); a sliding slit (141) is provided through the placement plate (14) along the length direction and is slidably matched with the matching portion (72); a cylinder (17) is provided at one end of the placement plate (14); a push plate (18) is fixed at the output end of the cylinder (17); the other end of the placement plate (14) is adjacent to the carrier plate (13); the carrier plate (13) is close to one end of the placement plate (14). The inlet end (131) is provided with a moving slit (132), the moving slit (132) is butted against the sliding slit (141), and the moving slit (132) is slidably matched with the matching portion (72), and the other end of the carrier plate (13) is a closed end (133); an electric lifting rod (15) is fixed in the vehicle body (1), and the lower part of the inlet end (131) of the carrier plate (13) is connected to the output end of the electric lifting rod (15) via a third rotating motor (16).

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