CN202175200U - Rotary throwing device for unmanned aerial vehicle - Google Patents

Abstract

A rotary projectile device used for unmanned aerial vehicles, two motors are fixed on the column of the projectile frame. The two motor gears are respectively mounted on the output shafts of the two motors. The gear disc is sleeved on the two motor gears, and the inner teeth of the gear disc mesh with the two motor gears. The counterweight bar and the interlocking cross bar are located above the gear plate, and the symmetrical jacket is sleeved on the support bar and fastened by two fasteners. The counterweight is mounted on the counterweight bar and is able to slide along the counterweight bar. One end of the movable swing arm is hinged with the end of the interlocking cross bar through a connecting piece; the other end of the movable swing arm is hinged with a UAV grasping and releasing latch. The utility model controls the rotation speed of the motor of the rotary ejection device to control the launch speed of the small and medium-sized UAV between 0m/s and 50m/s, which can effectively reduce the overload during the take-off process of the small and medium-sized UAV, and prolong the life of the unmanned drone. It has the characteristics of low production cost, small footprint, convenient operation and can be used in vehicles and ships.

Description

A rotary projectile device for drones

technical field

The invention belongs to the technical field of aviation machinery

Background technique

my country's traditional UAV launch methods can be divided into rocket-assisted launch, hydraulic ejection, air pressure ejection, and ground roll-off. Large-scale UAVs usually take off by ground sliding, while small and medium-sized UAVs usually use catapult take-off, which is extremely expensive and requires extremely high safety measures. Regardless of the ejection take-off method, the UAV must be accelerated to a launch speed for safe take-off by converting the energy stored in the energy storage device into mechanical energy. Traditional hydraulic ejection systems and pneumatic ejection systems are often tens of meters or even tens of meters long, occupy a large area, and are difficult to deploy and withdraw. The thrust line control and adjustment requirements of the rocket booster system are complex and cannot be reused. When the rocket falls off, it is easy to interfere with the rear-mounted power device, and it involves the storage and use of pyrotechnics, which is expensive and has sound, light, smoke and other signals when launching. , easy to expose the target.

Contents of the invention

Aiming at the shortcomings of the traditional unmanned aerial vehicle launch system, such as high manufacturing cost, large occupied area, complicated operation and easy exposure, the present invention proposes a rotary projectile device for unmanned aerial vehicles.

The invention comprises a projecting frame column, a driving mechanism and a rotating mechanism; the driving mechanism includes two motors, two motor gears and a gear plate; the two motors are fixed on the projecting frame column; the two motor gears are respectively mounted on the output of the two motors. on the shaft; the gear plate is set on the two motor gears, and the inner teeth of the gear plate mesh with the two motor gears; the rotating mechanism includes a counterweight bar, a counterweight, two fasteners, a linkage bar, and a connecting piece , the movable swing arm and the UAV grabbing and releasing the mortise lock; the counterweight bar and the linkage bar are located above the gear plate, and the symmetrical jacket is on the support bar and fastened by two fasteners; the counterweight It is installed on the counterweight bar and can slide along the counterweight bar; one end of the movable swing arm is hinged with the end of the linkage cross bar through a connecting piece; the other end of the movable swing arm is hinged with a UAV grasping and releasing latch.

The projectile frame column includes a tripod, a support rod, a motor fixing ear, and a positioning plate; the tripod is an adjustable mechanism and is fixed on one end of the support rod; the positioning plate is set on the support rod and is located above the motor fixing ear.

The two fasteners are located above the counterweight bar and the linkage cross bar, and the sleeve is clamped on the circumference of the support bar; one end of the counterweight bar is a semicircular fixed sleeve, and the inner diameter of the fixed sleeve is the same as the outer diameter of the support bar. The same; one end of the interlocking cross bar is also a semicircular fixed sleeve, the inner diameter of which is the same as the outer diameter of the support rod; the other end of the interlocking cross bar has a hinge hole; the interlocking cross bar is located on the positioning plate The upper surface of the upper surface is symmetrically distributed on the circumference of the support bar with the counterweight bar, and is clamped on the positioning plate through the fixed sleeve at one end of the interlocking cross bar. The two fasteners are semi-circular sleeves, and there are radially protruding connecting lugs on the circumference of each fastener.

The UAV grab and release mortise lock includes a mortise lock connection end, a bolt, a fixed shaft, a lock and a tension spring; the UAV grasp and release mortise lock is connected to the movable rocker arm through the mortise lock connection end, and the lower end is fixed by the fixed shaft There is a lock, and the lock can rotate around the fixed shaft; the upper end of the lock has a latch, and the lower end has a tension spring; the two sides of the lock are completely symmetrical, and one of the upper middle is equal to the radius of the fixed shaft The small hole, the lower end of the lock buckle is an outward slope, and the upper end is an inward slope; the side of the latch is a triangle that matches the upper end of the lock buckle, and can move up and down.

The invention lowers the height of the UAV's grasping and releasing mortise lock by controlling the tripod, and inserts the UAV's grasping and releasing mortise lock into a special slot on the UAV to realize the grasping of the UAV, and raises the tripod To the predetermined height, adjust the quality of the counterweight and the position of the counterweight on the support rod according to the quality and take-off speed of the projected UAV, and fix the tripod and the support rod, thus completing the pre-launch of the UAV. Install. Start the motor to drive the gear plate and the movable rocker arm to rotate, and at the same time start the power device of the drone to accelerate the rotation of the drone and the rocker arm at the same time. Since the movable rocker arm and the linkage crossbar are hinged, as the rotation speed increases, Larger, the radius of rotation of the UAV around the support rod is also increasing. This design can effectively reduce the angular velocity of the linkage crossbar when the UAV reaches the take-off speed. When the drone reaches take-off speed, keep the motors rotating at a constant speed. After adjusting the flight attitude through the power system of the UAV, start the UAV grasping and releasing latch device, the UAV and the UAV grasping and releasing the latch are separated, and the UAV ejects and takes off.

The invention is suitable for small and medium-sized unmanned aerial vehicles with a take-off weight of less than 500kg, a wingspan of less than 6m, and a take-off speed of less than 50m/s. By controlling the rotation speed of the motor of the rotary projectile device, the launch speed of the small and medium-sized UAV is between 0m/s and 50m/s.

The invention provides emission energy through a motor, occupies a small space, has a simple mechanism, is convenient for deployment and withdrawal, and can be used in vehicles. The auxiliary power is provided by the power unit of the UAV, and the pitch angle during take-off is controlled, which is convenient to operate; the launch, installation and release of the UAV are realized by the UAV grasping and releasing the latch, which is convenient to use. The take-off speed of the UAV can be effectively adjusted by controlling the motor, which is suitable for the launch of small and medium-sized UAVs with different weights and different take-off speeds. Compared with the traditional short-distance take-off method, the present invention can effectively reduce the overload during the take-off process of small and medium-sized UAVs, and prolong the service life of the UAVs. It is low in production cost, small in floor space, easy to operate, and can be used in vehicles and ships

Description of drawings

Fig. 1 is a schematic diagram of a rotating frame column;

Fig. 2 is a schematic diagram of cooperation between the motor and the gear plate;

Fig. 3 is a schematic diagram of the assembly of the motor, the motor gear, the counterweight bar, the fastener, the interlocking cross bar and the support bar;

Figure 4 is a schematic diagram of the connection between the interlocking cross bar, the movable swing arm, and the grasping and releasing latch of the drone;

Fig. 5 is a structural schematic diagram of the UAV grasping and releasing the mortise lock;

Fig. 6 is a structural schematic diagram of the buckle in the UAV grasping and releasing the mortise lock;

Fig. 7 is a structural schematic diagram of a small and medium-sized unmanned aerial vehicle rotating projectile device. in:

1. Triangular bracket 2. Support rod 3. Motor fixing lug 4. Positioning plate 5. Motor

6. Motor gear 7. Gear plate 8. Weight lever 9. Weight block 10. Fasteners

11. Interlocking cross bar 12. Connecting piece 13. Movable swing arm 14. UAV grab and release latch

15. Pin 16. Fixed shaft 17. Lock 18. Lock 19. Tension spring

Detailed ways

Below in conjunction with accompanying drawing, the present invention is further described

The small and medium-sized unmanned aerial vehicle rotary projecting device of the present embodiment.

It includes a projectile frame column, a driving mechanism, and a rotating mechanism.

As shown in Figure 7. Two motors 5 are fixed on the projecting frame column. Two motor gears 6 are installed on the output shafts of the two motors 5 respectively. The gear plate 7 is sleeved on the two motor gears 6, and the internal teeth of the gear plate 7 mesh with the two motor gears 6. When the motor 5 rotates, the two motor gears 6 drive the gear plate 7 to rotate. The counterweight bar 8 and the interlocking cross bar 11 are located above the gear plate, and are jacketed symmetrically on the support bar 2 and fastened by fasteners 10 . The counterweight 9 is mounted on the counterweight bar 8 and can slide along the counterweight bar 8 . One end of the movable swing arm 13 is hinged with the end of the interlocking cross bar 11 through the connector 12;

As shown in Figure 1. The projectile frame column includes a tripod 1, a support rod 2, a motor fixing lug 3, and a positioning plate 4. The tripod 1 is used to support the whole device, and is fixed on one end of the support rod 2 by welding; the tripod 1 is an adjustable mechanism, and the levelness of the tripod 1 is adjusted by adjusting the lengths of the three supporting legs of the tripod 1 and the height of the support rod 2. The motor fixing lugs 3 are located at the other end of the support rod 2, and are symmetrically distributed on the circumference of the support rod 2; the motor fixing lugs 3 have installation holes for fixing the motor. The positioning plate 4 is sleeved on the support rod 2 and located above the motor fixing lug 3 for supporting the rotation mechanism.

As shown in FIG. 2 , the driving mechanism includes two motors 5 , two motor gears 6 and a gear plate 7 . The two motors 5 are respectively fixed on the motor fixing lugs of the support rod 2 . Two motor gears 6 are installed on the output shafts of the two motors 5 respectively. The gear plate 7 is circular, and its inner ring surface is toothed; the gear plate 7 is set on the two motor gears 6, and the inner teeth of the gear plate 7 mesh with the two motor gears 6. When the motor 5 rotates, The gear disc is driven to rotate by two motor gears 6 .

As shown in Figure 3 and Figure 4. The rotating mechanism includes a counterweight bar 8, a counterweight 9, two fasteners 10, a linkage cross bar 11, a connector 12, a movable swing arm 13 and a latch 14 for grasping and releasing the UAV. The counterweight bar 8 and the interlocking cross bar 11 are located above the positioning plate 4, and are clamped on the circumference of the support bar 12 symmetrically. Two fasteners 10 are located above the counterweight bar 8 and the interlocking cross bar 11 , and are clamped on the circumference of the support bar 12 for fastening the counterweight bar 8 and the interlocking bar 11 . The counterweight 9 is mounted on the counterweight bar 8 and can slide along the counterweight bar 8 . One end of the movable swing arm 13 is hinged with the end of the interlocking cross bar 11 through the connector 12; the other end of the movable swing arm 13 is hinged with a UAV grasping and releasing latch 14, through which the UAV grips and releases the latch. 14. Mount the drone on this embodiment.

One end of the counterweight rod 8 is a semicircular fixed sleeve, and the inner diameter of the fixed sleeve is the same as the outer diameter of the support rod 2; on pole 2. One end of the interlocking cross bar 11 is also a semicircular fixing sleeve, and the inner diameter of the fixing sleeve is identical with the outer diameter of the support rod 2; the other end of the interlocking cross bar 11 has a hinged hole. The interlocking cross bar 11 is located on the upper surface of the positioning plate 4, and is symmetrically distributed on the circumference of the support rod 2 with the counterweight rod 8, and is clamped on the positioning plate 4 by a fixed sleeve at one end of the interlocking cross bar. The two fasteners 10 are semi-circular sleeves, and there are radially protruding connecting lugs on the circumference of each fastener 10. The two fasteners 10 are clamped on the support rod 2, and the two The fastener 10 is located above the interlocking crossbar 11 and the counterweight bar 8 ; the two fasteners 10 are fastened to each other to realize the fixing of the counterweight bar 8 and the interlocking crossbar 11 . The movable swing arm 13 is rod-shaped, and has through holes at both ends, which are respectively used to cooperate with the connector 12 and the latch 14 for grasping and releasing the drone.

As shown in Figure 5. The latch 14 for grasping and releasing the drone includes a latch connection end 15 , a latch 16 , a fixed shaft 17 , a lock catch 18 and a tension spring 19 . The UAV grasps and releases the latch 14 and is connected to the movable rocker arm by the lug at the upper end of the latch connection end 15, and the lower end is fixed with a lock catch 18 by a fixed shaft 17, and the lock catch 18 can rotate around the fixed shaft 17. The upper end of the mortise lock connecting end 15 has a pair of connecting lugs, and the lower end has two pairs of small holes with a radius equal to that of the fixed shaft 17; the fixed shaft 17 is a cylindrical shaft with two radii and equal lengths. The upper end of the lock buckle 18 is a latch 16 that can move up and down, and the lower end has a tension spring 19 that prevents two lock buckles 18 from approaching each other. The lock buckle 18 is completely symmetrical on both sides and has a small hole equal to the radius of the fixed shaft 17 in the upper part of the middle. The lower end of the lock buckle 18 is an outward slope, and the upper end is an inward slope; The side of latch 16 is a triangle that fits with the upper end of snap close 18 and can move up and down.

When grasping, align the buckle 18 of the drone's grasping and releasing latch 14 with the special slot of the drone and push it down. The locking buckle 18 is subjected to the interaction force of the slot to the locking buckle to compress the tension spring 19, After the lock 18 enters the slot, it is subjected to the tension of the tension spring 19, and the lock 18 returns to its original position. At this time, the mutual locking of the lock 18 and the slot of the drone is realized, and the grasp of the drone is realized. . The bolt 16 is equipped with an electric device to make the bolt 16 move up and down, start the electric device to drive the bolt 16 to move downward, squeeze the lock 18 on both sides and compress the tension spring 19, so as to realize the separation of the lock 18 and the UAV slot. The release of the drone can be realized.

When using this embodiment, the UAV grasping and releasing latch 14 is inserted into a special slot on the UAV to realize the gripping of the UAV. Synchronously adjust the length of the tripod 1, raise the height of the UAV to grasp and release the latch 14, raise the UAV to the specified launching height, and fix the tripod 1 and the support rod 2. According to this UAV quality and take-off speed, adjust the quality of the counterweight 9 on the counterweight bar 8 and the position on the support bar 2. Preparations for the drone launch are complete. When launching the drone, start the motor and the power system of the drone at the same time, and the linkage cross bar 11 drives the movable swing arm 13 and the drone to accelerate the rotation. When the speed of the drone reaches the take-off speed, keep the rotation mechanism rotating at a constant speed , after adjusting the flight attitude of the drone itself through the power system of the drone, start the drone to grasp and release the mortise lock, and release the drone to take off.

In this embodiment, by adjusting the quality of the counterweight 9 and the position of the counterweight 9 on the support rod 8, the counterweight of the projectile device when projecting different UAVs is realized. When the rotating mechanism rotates, as the rotation speed increases, the radius of rotation of the UAV grasping and releasing the latch 14 hinged on the movable rocker arm 12 around the support rod 2 can be effectively increased, thereby reducing the time when the UAV reaches the take-off speed. The rotational angular velocity of the crossbar 11 is linked to increase the stability of the projectile system. The movable swing arm 13 is hinged with the UAV grasping and releasing the latch 14, and the UAV can adjust its pitch angle during acceleration and take-off by its own power system.

Claims (5)

1. a rotation casting device that is used for unmanned plane is characterized in that, comprises impelling frame column, driver train, rotating mechanism; Driver train comprises two motors (5), two motor gears (6) and toothed disc (7); Two motors (5) are fixed on the impelling frame column; Two motor gears (6) are contained in respectively on the output shaft of two motors (5); Toothed disc (7) is sleeved on two motor gears (6), and the internal tooth of toothed disc (7) and two motor gears (6) engagement; Rotating mechanism comprises that weight linear meter (8), clump weight (9), two fasteners (10), interlock cross bar (11), attaching parts (12), activity swing arm (13) and unmanned plane grasp release mortise lock (14); Weight linear meter (8) and interlock cross bar (11) are positioned at the top of toothed disc, and the chuck of symmetry and tightens up through two fasteners (10) on strut bar (2); Clump weight (9) is contained on the weight linear meter (8), and can slide along weight linear meter (8); One end of activity swing arm (13) is hinged with the termination of interlock cross bar (11) through attaching parts (12); The other end of activity swing arm (13) is hinged with unmanned plane and grasps release mortise lock (14).

2. a kind of according to claim 1 rotation casting device that is used for unmanned plane is characterized in that, impelling frame column comprises A-frame (1), strut bar (2), motor fixedly auricle (3), dowel disc (4); A-frame (1) is an adjustable mechanism, is fixed on an end of strut bar (2); Dowel disc (4) is sleeved on the strut bar (2), is positioned at the fixedly top of auricle (3) of motor;

3. a kind of according to claim 1 rotation casting device that is used for unmanned plane is characterized in that two fasteners (10) all are positioned at the top of weight linear meter (8) and interlock cross bar (11), and cover is clipped on the circumference of strut bar (12); Weight linear meter (8) one ends are semi-round fixed cover, and the internal diameter of this fixed cover is identical with the external diameter of strut bar (2); One end of interlock cross bar (11) also is semi-round fixed cover, and the internal diameter of this fixed cover is identical with the external diameter of strut bar (2); There is hinge hole the other end termination of interlock cross bar (11); Interlock cross bar (11) is positioned at the upper surface of dowel disc (4), on the circumference that is distributed in strut bar (2) of weight linear meter (8) symmetry, and is installed on the dowel disc (4) through the fixed cover of interlock cross bar one end.

4. like the said a kind of rotation casting device that is used for unmanned plane of claim 3, it is characterized in that two fasteners (10) are the semicircle cover, the radially attachment lug of protrusion is all arranged on the circumference of each fastener (10).

5. a kind of according to claim 1 rotation casting device that is used for unmanned plane is characterized in that, unmanned plane grasps release mortise lock (14) and comprises mortise lock coupling end (15), latch (16), anchor shaft (17), snap close (18) and tension spring (19); Unmanned plane grasps release mortise lock (14) and is connected on the movable rocking arm through mortise lock coupling end (15), and the lower end is fixed with snap close (18) through anchor shaft (17), and snap close (18) can rotate around anchor shaft (17); The upper end of snap close (18) is for there being latch (16), and there is tension spring (19) lower end; Described snap close (18) is that the place of two complete symmetries in side and upper middle has an aperture that equates with anchor shaft (17) radius, and the lower end of snap close (18) is outer mutually inclined-plane, and the upper end is inside inclined-plane; The side of described latch (16) is and snap close (18) upper end cncr triangle, can moves up and down.

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