Unmanned aerial vehicle vehicle-mounted launching device and method

Abstract

The present invention provides a vehicle-mounted launch device and method for a drone, belonging to the technical field of drone launch. The vehicle-mounted launch device for a drone includes: a lower frame; an upper frame, the upper frame is connected to the lower frame through a connecting rod; a support leg, the support leg is fixedly connected to the lower end of the lower frame; two limit plates, both of which are fixedly connected to the upper end of the upper frame; a limit rod, the limit rod is arranged in the two limit plates; the angle of the upper frame can be adjusted according to actual needs through an angle adjustment mechanism, so as to provide an optimal launch posture for the drone; the drone can be quickly deployed under different terrain conditions, and the launch angle can be flexibly adjusted according to different mission requirements, thereby increasing the adaptability and scope of use of the device. In addition, the vehicle-mounted design allows the entire launch device to be easily transported to any location, enhancing the maneuverability and response speed of the operation.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle (UAV) launch, and in particular relates to a vehicle-mounted launch device and method for an unmanned aerial vehicle (UAV). Background Art

[0002] There are many land-based launch methods for drones, including hand-throw launch, zero-length launch, catapult launch, taxiing takeoff and vertical takeoff. Among them, zero-length launch mostly uses rocket-assisted launch without taxiing. The drone flies away from the launch device under the thrust of one or two booster rockets. After the drone takes off, the booster rocket falls by its own weight, and the flight mission is completed by the engine on the drone. Rocket-assisted launch technology is mature, has a large thrust range, and is low in cost, and has been serialized. Through the rocket-assisted launch device, the drone can achieve a faster take-off speed and a greater rise height, thereby meeting specific flight needs.

[0003] After searching, it was found that the Chinese patent with the authorization announcement number "CN113815886B" proposed the demand for long-flight UAVs and disclosed a slender-wing UAV takeoff system. The takeoff system can be divided into three parts according to the functions performed, namely: UAV, launch vehicle and takeoff frame. The UAV is installed in the takeoff frame, and the positioning and fixation of the UAV is achieved through the takeoff frame. The takeoff frame is installed on the top of the launch vehicle, and the launch vehicle is started to accelerate the UAV to achieve the vehicle-mounted takeoff of the UAV. The takeoff system is innovatively designed for the long-flight UAV takeoff system, which reduces the aerodynamic resistance of the UAV while reducing the takeoff weight, ensuring the long-flight flight of the UAV.

[0004] However, the current ground-launching method of UAVs cannot be manually adjusted in angle, has low accuracy, cannot be adjusted to a specified position or cannot be adjusted according to the range of the scene, and includes safety risks during storage, transportation and operation. If not properly controlled, it may cause accidents such as fire or explosion. Summary of the invention

[0005] The purpose of the present invention is to provide a vehicle-mounted launch device and method for a UAV, aiming to solve the problems in the prior art that the ground launch method of UAVs cannot be manually fine-tuned in angle, has low accuracy, cannot be adjusted to a specified position or cannot be adjusted according to the range of the scene, and includes safety risks during storage, transportation and operation. If improperly controlled, it may cause accidents such as fire or explosion.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] UAV vehicle-mounted launching device, including:

[0008] Lower frame;

[0009] An upper frame, wherein the upper frame is connected to the lower frame via a connecting rod;

[0010] A supporting leg, the supporting leg being fixedly connected to the lower end of the lower frame;

[0011] Two limit plates, both of which are fixedly connected to the upper end of the upper frame;

[0012] A first limiting rod, wherein the first limiting rod is arranged in the two limiting plates;

[0013] A rocket support seat, the rocket support seat is rotatably connected to the surface of the first limit rod;

[0014] A rocket body, wherein the rocket body is located on the upper side of the rocket support seat, and the rocket support seat is used to support the rocket body;

[0015] A rocket pusher seat, the rocket pusher seat is connected to the head of the rocket body;

[0016] Two wing soft supports, both of which are arranged at the upper end of the upper frame through a connecting rod, and are used to accommodate the UAV;

[0017] A rocket support torsion spring, wherein the rocket support torsion spring is sleeved on the surface of the first limit rod, and the rocket support torsion spring is in contact with the rocket support seat;

[0018] An angle adjustment mechanism, which is arranged on the upper side of the lower frame, and the upper frame is lifted up by the angle adjustment mechanism to facilitate the later launch;

[0019] A tension adjustment component, which is disposed at the upper end of the upper frame and is used to control the strength of the drone and adjust the launch speed;

[0020] The locking mechanism is arranged on the upper side of the upper frame and is used to lock the drone.

[0021] As a preferred solution of the present invention, the angle adjustment mechanism includes a first support frame, a second support frame, a screw rod, a handle, a bolt bearing, a single-head movable support column and a double-head movable support column, the first support frame and the second support frame are both fixedly connected to the upper end of the lower frame, the screw rod is threadedly connected to the first support frame and the second support frame and passes through the first support frame, the handle is fixedly connected to one end of the screw rod, the bolt bearing is threadedly connected to the surface of the screw rod through a nut, the double-head movable support column is arranged at the close ends of the lower frame and the upper frame through a connecting rod, one side of the single-head movable support column is fixedly connected to the lower end of the upper frame, and the other side of the single-head movable support column is connected to the surface of the bolt bearing through a connecting rod.

[0022] As a preferred solution of the present invention, the tension adjustment assembly includes a fixing rod and a fixing nut, the fixing rod is fixedly connected to one side of the rocket support seat, and the fixing nut is threadedly connected to the surface of the fixing rod.

[0023] As a preferred solution of the present invention, the locking mechanism includes a first connecting rod, a U-shaped support block, a drone fixing pin, a long rod, a front bracket torsion spring, a middle connecting rod, a middle nut and a second connecting rod, wherein the first connecting rod, the U-shaped support block, the drone fixing pin and the second connecting rod are provided with two groups, the two first connecting rods are fixedly connected to the upper end of the upper frame, the long rod is fixedly connected to the close ends of the two first connecting rods, the front bracket torsion spring is sleeved on the surface of the long rod, one of the second connecting rods is respectively fixedly connected to the close ends of the two wing soft supports, the other second connecting rod is fixedly connected to the proximal ends of the two first connecting rods, the middle connecting rod is sleeved on the surfaces of the two second connecting rods, the middle nut is threadedly connected to the surface of the middle connecting rod, the two U-shaped support blocks are respectively fixedly connected to the upper ends of the two first connecting rods, and the two drone fixing pins are respectively located in the two U-shaped support blocks.

[0024] As a preferred solution of the present invention, a stabilizing rod is provided at the lower end of the supporting leg, and the stabilizing rod is a solid structure.

[0025] As a preferred solution of the present invention, two gaskets are fixedly connected to the upper side of the lower frame, and the bottom of the upper frame is in contact with the gaskets, so that when the upper frame is folded and stored, there will be no collision between metals.

[0026] As a preferred solution of the present invention, a fixing ring is fixedly connected to the upper end of the upper frame, and a spring is provided between the fixed rod and the fixing ring.

[0027] As a preferred solution of the present invention, a plug hole is provided at one side end of the lower frame, a plurality of limiting holes are provided on the surface of the handle, a limiting rod is provided in the plug hole, and the limiting rod is located in the limiting hole.

[0028] As a preferred solution of the present invention, the upper ends of the two wing soft supports are fixedly connected with pads.

[0029] The present invention also discloses a vehicle-mounted launching method for an unmanned aerial vehicle, using the launching device of the present invention, comprising the following steps:

[0030] S1. First, place the lower frame on the ground and fix it with the support legs to ensure that the upper frame and the lower frame are connected through the connecting rod; the first support frame and the second support frame are fixed to the upper end of the lower frame, the screw rod passes through the first support frame and the second support frame and is rotated by the handle, the bolt bearing is connected to the screw rod, one end of the single-headed movable support column is connected to the upper frame, and the other end is connected to the bolt bearing through the connecting rod, and the double-headed movable support column is used to assist the structure to maintain stability; the fixed force rod is fixed to one side of the rocket support seat, and the pressure when the drone is placed is adjusted by rotating the fixed force nut to control the force during launch; the two first connecting rods are fixed to the upper frame, and the U-shaped support block is located on the first connecting rod, which is used to fix the drone fixing pin, and the drone is fixed The fixing pin is used to fix the drone. The torsion spring of the front bracket provides a buffer before the drone is launched. The middle connecting rod, the middle nut and the second connecting rod work together to ensure that the drone is firmly locked. The screw is rotated by rotating the handle to drive the single-head movable support column to move up and down, so as to adjust the angle of the upper frame and ensure that the drone is in a tilted state. The drone to be launched is placed on the wing soft support, and the drone is fixed with the drone fixing pin. After checking that all parts are safely locked, the position of the fixing nut is adjusted according to the required launch speed to change the pressure exerted on the drone by the wing soft support. The drone fixing pin in the locking mechanism is released. At this time, the drone is only held by the wing soft support, and the rocket body pushes the drone to take off.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] 1. The angle adjustment mechanism can adjust the angle of the upper frame according to actual needs, thereby providing the UAV with an optimal launch posture. This not only allows the UAV to be quickly deployed under different terrain conditions, but also allows the launch angle to be flexibly adjusted according to different mission requirements, increasing the adaptability and scope of use of the device. In addition, the vehicle-mounted design allows the entire launch device to be easily transported to any location, enhancing the maneuverability and response speed of the operation. By setting up a locking mechanism and a tension adjustment component, the device can ensure that the UAV is firmly fixed before launch, and can adjust the appropriate fixing force according to the specific model to prevent safety hazards caused by over-tightening or over-loosening. At the same time, a stabilizing rod is designed at the lower end of the support leg to increase the stability of the overall structure when placed on the ground; and the presence of the gasket avoids possible damage caused by direct contact between the upper and lower frames. These considerations in details jointly ensure the reliability of the equipment for long-term use.

[0033] 2. Precision components such as the rocket push seat and angle adjustment mechanism can provide a stable launch platform for the UAV. The design of the rocket support torsion spring ensures that the UAV is given sufficient support force at the moment of launch without causing structural damage or position displacement due to sudden impact. In addition, the tension adjustment component allows the operator to accurately adjust the launch force according to the specific model and weight of the UAV, thereby optimizing the power distribution during takeoff and improving the success rate and accuracy of the launch. Such a design not only reduces errors caused by human factors, but also ensures that each launch can achieve the expected effect, which is especially important for performing reconnaissance, monitoring or other tasks that require precise positioning. Through the application of these technical means, the device can significantly improve the efficiency and quality of UAV mission execution while ensuring safety.

[0034] 3. The UAV vehicle-mounted launch device and method adopts a modular design concept. For example, key components such as the rocket support seat and the wing soft support are assembled in a way that is easy to disassemble and replace. In this way, during daily maintenance or when encountering a malfunction, the staff can quickly locate the problem and repair it in time, reducing the maintenance time and cost. In addition, considering the folding storage function, when not in use, the upper frame can be folded up to reduce the volume, which is convenient for storage and transportation, and also reduces the demand for storage space. This humanized design greatly simplifies the logistics support work and extends the service life of the entire device. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0036] Figure 1 This is an observation diagram of the present invention;

[0037] Figure 2 It is a front view of the present invention;

[0038] Figure 3 For the present invention Figure 2 Enlarged view of point A in the middle;

[0039] Figure 4 It is a top view of the present invention;

[0040] Figure 5 It is the main stereoscopic view in the present invention;

[0041] Figure 6 For the present invention Figure 5 Enlarged view of point B in the middle;

[0042] Figure 7 For the present invention Figure 5 Enlarged view of point C in the middle.

[0043] In the figure: 1. Rocket body; 2. Rocket pusher seat; 301. First support frame; 302. Screw rod; 303. Handle; 304. Second support frame; 305. Bolt bearing; 306. Single-head movable support column; 4. Support leg; 501. Fixed rod; 502. Fixed nut; 6. Spring; 7. Rocket support seat; 8. Pad; 901. First connecting rod; 902. Long rod; 903. Front bracket torsion spring; 10. U-shaped support block; 11. UAV fixing pin; 1201. middle connecting rod; 1202. middle nut; 13. wing soft support; 14. second connecting rod; 15. lower frame; 16. upper frame; 1701. limit plate; 1702. first limit rod; 1703. rocket support torsion spring; 18. fixing ring; 19. double-headed movable support column; 20. gasket; 21. limit hole; 22. second limit rod; 23. stabilizer bar; 24. socket. DETAILED DESCRIPTION

[0044] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0045] Example 1

[0046] See also Figure 1-Figure 7 , the present invention provides the following technical solutions:

[0047] UAV vehicle-mounted launching device, including:

[0048] Lower frame 15;

[0049] The upper frame 16 is connected to the lower frame 15 through a connecting rod;

[0050] Support leg 4, support leg 4 is fixedly connected to the lower end of the lower frame 15;

[0051] Two limiting plates 1701, both of which are fixedly connected to the upper end of the upper frame 16;

[0052] A first limiting rod 1702, which is disposed inside the two limiting plates 1701;

[0053] A rocket support seat 7, the rocket support seat 7 is rotatably connected to the surface of the first limiting rod 1702;

[0054] The rocket body 1 is located on the upper side of the rocket support seat 7, and the rocket support seat 7 is used to support the rocket body 1;

[0055] A rocket pusher seat 2, which is connected to the head of the rocket body 1;

[0056] Two wing soft supports 13, both of which are arranged at the upper end of the upper frame 16 through a connecting rod, and are used to accommodate the UAV;

[0057] A rocket support torsion spring 1703, the rocket support torsion spring 1703 is sleeved on the surface of the first limit rod 1702, and the rocket support torsion spring 1703 is in contact with the rocket support seat 7;

[0058] An angle adjustment mechanism, which is arranged on the upper side of the lower frame 15, and the upper frame 16 is lifted up by the angle adjustment mechanism to facilitate the later launch;

[0059] The tension adjustment component is arranged at the upper end of the upper frame 16 and is used to control the strength of the drone and adjust the launch speed;

[0060] A locking mechanism, which is disposed on the upper side of the upper frame 16 and is used to lock the drone;

[0061] The angle adjustment mechanism includes a first support frame 301, a second support frame 304, a screw rod 302, a handle 303, a bolt bearing 305, a single-head movable support column 306 and a double-head movable support column 19. The first support frame 301 and the second support frame 304 are both fixedly connected to the upper end of the lower frame 15, the screw rod 302 is threadedly connected to the first support frame 301 and the second support frame 304 and passes through the first support frame 301, the handle 303 is fixedly connected to one end of the screw rod 302, the bolt bearing 305 is threadedly connected to the surface of the screw rod 302 through a nut, and the double-head movable support column 19 is arranged at the adjacent ends of the lower frame 15 and the upper frame 16 through a connecting rod, one side of the single-head movable support column 306 is fixedly connected to the lower end of the upper frame 16, and the other side of the single-head movable support column 306 is connected to the surface of the bolt bearing 305 through a connecting rod;

[0062] The tension adjustment assembly includes a fixed rod 501 and a fixed nut 502, wherein the fixed rod 501 is fixedly connected to one side of the rocket support seat 7, and the fixed nut 502 is threadedly connected to the surface of the fixed rod 501;

[0063] The locking mechanism includes a first connecting rod 901, a U-shaped support block 10, a drone fixing pin 11, a long rod 902, a front bracket torsion spring 903, a middle connecting rod 1201, a middle nut 1202 and a second connecting rod 14, wherein the first connecting rod 901, the U-shaped support block 10, the drone fixing pin 11 and the second connecting rod 14 are provided with two groups, the two first connecting rods 901 are fixedly connected to the upper end of the upper frame 16, the long rod 902 is fixedly connected to the adjacent ends of the two first connecting rods 901, and the front bracket torsion spring 903 is set It is arranged on the surface of the long rod 902, wherein one of the second connecting rods 14 is fixedly connected to the proximal ends of the two wing soft supports 13, and the other second connecting rod 14 is fixedly connected to the proximal ends of the two first connecting rods 901. The middle connecting rod 1201 is sleeved on the surfaces of the two second connecting rods 14, and the middle nut 1202 is threadedly connected to the surface of the middle connecting rod 1201. The two U-shaped support blocks 10 are fixedly connected to the upper ends of the two first connecting rods 901, and the two drone fixing pins 11 are respectively located in the two U-shaped support blocks 10.

[0064] In a specific embodiment of the present invention, the lower frame 15 constitutes the basic structure of the device, providing a stable support for the upper components. The upper frame 16 is connected to the lower frame 15 through a connecting rod to form a movable structure, which serves as the main platform for placing the rocket body 1 and other auxiliary devices. The support legs 4 enhance the stability of the entire launch device. A space is formed between the limiting plates 1701 to accommodate the first limiting rod 1702. The first limiting rod 1702 is used as a basis for installing the rocket support seat 7. The rocket support seat 7 can rotate around the first limiting rod 1702, and a rocket support torsion spring 1703 is sleeved on its surface to facilitate adjusting the angle and maintaining the position of the rocket body 1. The rocket body 1 serves as the power source for the propulsion of the UAV, and the rocket push seat 2 Used to push the rocket into the air, the wing soft support 13 is provided with two, working through a connecting rod mechanism, mainly used to place and protect the wings of the UAV, the rocket support torsion spring 1703 ensures that the rocket support seat 7 can rotate freely within a specific range, and can automatically reset to the initial position, correctly install the UAV on the rocket support seat 7, and fix it with a locking mechanism, use the angle adjustment mechanism to set the optimal inclination angle of the upper frame 16, adjust the force of the wing soft support 13 on the UAV through the tension adjustment component to ensure appropriate launch force, check whether all connection parts are firm and reliable, and then proceed to the next step. The first support frame 301 is fixedly connected to the lower frame 15 as one end support point of the screw rod 302, and the second support frame 304 is also connected to the lower frame 15. The frame 15 is fixedly connected and is located at a relative position of the first support frame 301, serving as the other end support point of the screw rod 302. The screw rod 302 passes through the first support frame 301 and the second support frame 304 by a threaded connection, so that the screw rod 302 can rotate freely between the two support frames. The handle 303 is used to manually rotate the screw rod, thereby realizing the operation of the entire mechanism. The bolt bearing 305 is threadedly connected to the surface of the screw rod 302 through a nut. When the screw rod 302 is rotated, the bolt bearing can move along the direction of the screw rod. One end of the single-head movable support column 306 is fixed to the bottom of the upper frame 16, and the other end is connected to the bolt bearing 305 through a connecting rod. As the bolt bearing 305 moves along the screw rod 302, the single-head movable support column 306 will change accordingly. Its position, thereby driving the change of the tilt angle of the upper frame 16. The double-headed movable support column 19 is arranged on the side close to the lower frame 15 and the upper frame 16 through a connecting rod, which plays an auxiliary supporting role and allows the upper frame to adjust its angle as needed. When the operator rotates the handle 303, the screw rod 302 rotates accordingly. As the screw rod 302 rotates, the bolt bearing 305 will move linearly along the screw rod 302. The position change of the bolt bearing 305 directly causes the single-headed movable support column 306 connected thereto to be displaced. The displacement of the single-headed movable support column 306 causes the upper frame 16 to rotate around the axis formed by the double-headed movable support column 19, thereby changing its angle relative to the horizontal plane. In this way, the tilt degree of the upper frame 16 can be very finely controlled.In order to adapt to different launch requirements, the fixed rod 501 serves as the basic structure of the entire tension adjustment mechanism, providing a path for the fixed nut 502 to move along its surface. The surface of the fixed rod 501 has threads for the movement of the fixed nut 502, and the positive and negative threads are used to adjust the tension of the fixed rod 501. The fixed rod 501 is used for the placement of the UAV. By rotating the fixed nut 502, its position on the fixed rod 501 can be changed, thereby adjusting the support strength of the wing soft support 13. Clockwise rotation of the fixed nut will cause it to move inward along the fixed rod, increasing the pressure on the UAV, thereby increasing the support strength of the UAV wing; conversely, counterclockwise rotation reduces the pressure. The first connecting rod 901 provides basic support for the entire locking mechanism, and the U-shaped support block 10 is used to place The UAV fixing pin 11 is placed and supported. The UAV fixing pin 11 is locked by cooperating with a specific part of the UAV. The front bracket torsion spring 903 provides a certain elastic restoring force, which helps to maintain the stability of the device. The middle connecting rod 1201 plays the role of connecting and enhancing the overall rigidity. The middle nut 1202 can adjust its position by rotation, thereby adjusting the tightness of the entire mechanism. The second connecting rod 14 facilitates the docking of the middle connecting rod 1201. When the UAV is placed in place, the UAV fixing pin 11 is inserted into the U-shaped support block 10, and ensure that they are correctly inserted into the reserved holes or other matching structures on the UAV. By rotating the middle nut 1202, the pressure of the middle connecting rod 1201 on the second connecting rod 14 can be adjusted, thereby controlling the clamping force of the entire locking mechanism on the UAV. Properly tightening the middle nut can make the drone more firmly fixed on the launch platform. The front bracket torsion spring 903 provides additional elastic support to help keep the device stable when subjected to slight external force. In this device, the launch plane must be raised to 16 degrees for vehicle-mounted launch. Due to the large wingspan of the drone, the width of the vehicle is limited and only 4 drones can be placed at an angle. When loading the vehicle, the drones close to the cab are loaded first, in order of 1, 2, 3, and 4. When launching, 4 is launched first, in order of 4, 3, 2, and 1. In this way, there is no interference between drones during loading and launching. The drone launch angle adjustment is accurate and easy to operate; the reliability of drone locking and release is high.

[0065] For details, please refer to Figure 1-Figure 7 A stabilizing rod 23 is provided at the lower end of the supporting leg 4, and the stabilizing rod 23 is a solid structure.

[0066] In this embodiment: the main function of the stabilizer bar 23 is to increase the contact area between the support leg 4 and the ground, thereby dispersing the pressure, reducing the pressure per unit area, and preventing the ground from sinking or becoming unstable due to excessive local pressure. The stabilizer bar 23 is made of solid material, and the entire plate body is made of solid material. Such a design can significantly improve the rigidity and load-bearing capacity of the support leg 4 when in contact with the ground.

[0067] For details, please refer to Figure 1-Figure 7 Two gaskets 20 are fixedly connected to the upper side of the lower frame 15, and the bottom of the upper frame 16 is in contact with the gasket 20, so that when the upper frame 16 is folded and stored, there will be no collision between metals.

[0068] In this embodiment: the gasket 20 is located at the position where the bottom of the upper frame 16 is about to contact. The specific shape and size of the gasket need to be customized according to the contact surface of the upper and lower frames to ensure that it can completely cover the contact area and will not hinder the normal movement of the upper frame 16. When the upper frame 16 is folded and stored, its bottom will be pressed on the gasket 20 instead of directly contacting the metal surface of the lower frame 15. The buffer layer provided by the gasket 20 can effectively absorb and disperse pressure, reduce scratches, dents or other damage caused by hard contact, and due to the elastic properties of the gasket, it can also slow down the impact generated when the upper frame 16 is lowered, thereby reducing the noise level.

[0069] For details, please refer to Figure 1-Figure 7 The upper end of the upper frame 16 is fixedly connected with a fixing ring 18 , and a spring 6 is provided between the fixed rod 501 and the fixing ring 18 .

[0070] In this embodiment: the presence of spring 6 provides a certain elastic space for the fixed rod 501. When the drone needs to adjust the pressure, the spring can absorb part of the force to prevent sudden changes from causing impact or damage to the drone. By rotating the fixed nut 502, its position on the fixed rod 501 can be changed to adjust the support force for the drone. The spring 6 plays a role of buffering and auxiliary regulation in this process. The elastic restoring force provided by the spring helps to maintain the stability of the entire device. Even if there is a slight external interference in the launch preparation stage, the spring can help the device quickly return to the set state.

[0071] For details, please refer to Figure 1-Figure 7 A plug hole 24 is provided at one side end of the lower frame 15 , a plurality of limiting holes 21 are provided on the surface of the handle 303 , a second limiting rod 22 is provided in the plug hole 24 , and the second limiting rod 22 is located in the limiting hole 21 .

[0072] In this embodiment: the insertion hole 24 provides a fixed position for the second limiting rod 22, so that it can be inserted and remain stable. The limiting holes 21 are evenly distributed at different positions of the handle, so that when the handle is rotated to a specific angle, the second limiting rod 22 can be inserted into one of the holes. The function of the second limiting rod 22 is to lock the position of the handle by inserting different limiting holes, thereby fixing the angle of the upper frame 16. The operator first adjusts the screw rod 302 by rotating the handle 303, thereby driving the bolt bearing 305 to move, changing the position of the single-head movable support column 306, and finally adjusting the angle of the upper frame 16. Once the desired angle is reached, the operator can select the limiting hole 21 at the corresponding position on the handle 303, and then remove the second limiting rod 22 from the insertion hole 24 and insert it into the selected limiting hole. In this way, the handle 303 is fixed, thereby locking the current angle setting. When the angle needs to be adjusted again, just pull out the second limiting rod 22, rotate the handle 303 again, and then select the appropriate limiting hole to lock it.

[0073] For details, please refer to Figure 1-Figure 7 The upper ends of the two wing soft supports 13 are fixedly connected with pads 8.

[0074] In this embodiment: the pad 8 is in direct contact with the wing of the drone and is made of a material with a certain elasticity. The shape and size of the pad 8 are customized according to the structure and size of the drone wing to ensure that it can fully cover and support the key parts of the wing. The design of the pad 8 should take into account the versatility of different types of drones. When the drone is placed on the soft support 13 of the wing, the pad 8 provides an additional buffer layer to reduce the scratches or dents that may be caused by the hard support surface to the wing. The pad 8 increases the contact area and helps to better disperse the pressure, so that the wing is placed more firmly on the support, reducing the risk of sliding or shifting. Since the pad has a certain elasticity, it can adapt to wings of different shapes and sizes, providing a wider compatibility and a better user experience.

[0075] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. UAV vehicle-mounted launch device, characterized in that: include: Lower frame (15); An upper frame (16), the upper frame (16) being butt-jointed with the lower frame (15) via a connecting rod; A supporting leg (4), the supporting leg (4) being fixedly connected to the lower end of the lower frame (15); Two limit plates (1701), both limit plates (1701) are fixedly connected to the upper end of the upper frame (16); A first limiting rod (1702) disposed inside the two limiting plates (1701); A rocket support seat (7) rotatably connected to the surface of the first limiting rod (1702); A rocket body (1), which is located on the upper side of a rocket support seat (7), and the rocket support seat (7) is used to support the rocket body (1); A rocket push seat (2), the rocket push seat (2) being connected to the head of the rocket body (1); Two wing soft supports (13), both of which are arranged at the upper end of the upper frame (16) through a connecting rod and are used to accommodate the UAV; A rocket supporting torsion spring (1703), which is sleeved on the surface of the first limiting rod (1702), and the rocket supporting torsion spring (1703) is in contact with the rocket supporting seat (7); An angle adjustment mechanism, the angle adjustment mechanism being arranged on the upper side of the lower frame (15), and the upper frame (16) is lifted by the angle adjustment mechanism; A tension adjustment component, the tension adjustment component being arranged at the upper end of the upper frame (16) and being used to adjust the firing speed; A locking mechanism, the locking mechanism being arranged on the upper side of the upper frame (16) and being used to lock the drone; The angle adjustment mechanism comprises a first support frame (301), a second support frame (304), a screw rod (302), a handle (303), a bolt bearing (305), a single-head movable support column (306) and a double-head movable support column (19), wherein the first support frame (301) and the second support frame (304) are both fixedly connected to the upper end of the lower frame (15), and the screw rod (302) is threadedly connected to the first support frame (301) and the second support frame (304) and passes through the first support frame (301). 1), the handle (303) is fixedly connected to one end of the screw rod (302), the bolt bearing (305) is threadedly connected to the surface of the screw rod (302) through a nut, the double-headed movable support column (19) is arranged at the adjacent ends of the lower frame (15) and the upper frame (16) through a connecting rod, one side of the single-headed movable support column (306) is fixedly connected to the lower end of the upper frame (16), and the other side of the single-headed movable support column (306) is connected to the surface of the bolt bearing (305) through a connecting rod; The tension adjustment assembly comprises a fixing rod (501) and a fixing nut (502), wherein the fixing rod (501) is fixedly connected to one side of the rocket support seat (7), and the fixing nut (502) is threadedly connected to the surface of the fixing rod (501); The locking mechanism comprises a first connecting rod (901), a U-shaped support block (10), a drone fixing pin (11), a long rod (902), a front bracket torsion spring (903), a middle connecting rod (1201), a middle nut (1202) and a second connecting rod (14), wherein the first connecting rod (901), the U-shaped support block (10), the drone fixing pin (11) and the second connecting rod (14) are provided in two groups, two of the first connecting rods (901) are fixedly connected to the upper end of the upper frame (16), the long rod (902) is fixedly connected to the adjacent ends of the two first connecting rods (901), and the front bracket torsion spring (903) is fixedly connected to the upper end of the upper frame (16). ) is sleeved on the surface of the long rod (902), wherein one of the second connecting rods (14) is fixedly connected to the proximal ends of the two wing soft supports (13), and the other second connecting rod (14) is fixedly connected to the proximal ends of the two first connecting rods (901). The middle connecting rod (1201) is sleeved on the surfaces of the two second connecting rods (14), and the middle nut (1202) is threadedly connected to the surface of the middle connecting rod (1201). The two U-shaped support blocks (10) are fixedly connected to the upper ends of the two first connecting rods (901), and the two UAV fixing pins (11) are respectively located in the two U-shaped support blocks (10).

2. The UAV vehicle-mounted launch device according to claim 1, characterized in that: A stabilizing rod (23) is provided at the lower end of the supporting leg (4), and the stabilizing rod (23) is a solid structure.

3. The UAV vehicle-mounted launch device according to claim 2 is characterized in that: Two gaskets (20) are fixedly connected to the upper side of the lower frame (15), and the bottom of the upper frame (16) is in contact with the gaskets (20).

4. The UAV vehicle-mounted launch device according to claim 3 is characterized in that: A fixing ring (18) is fixedly connected to the upper end of the upper frame (16), and a spring (6) is provided between the fixed rod (501) and the fixing ring (18).

5. The UAV vehicle-mounted launch device according to claim 4 is characterized in that: A plug hole (24) is provided at one side end of the lower frame (15), a plurality of limiting holes (21) are provided on the surface of the handle (303), a second limiting rod (22) is provided in the plug hole (24), and the second limiting rod (22) is located in the limiting hole (21).

6. The UAV vehicle-mounted launch device according to claim 5, characterized in that: The upper ends of the two wing soft supports (13) are both fixedly connected with a pad (8).

7. A method for launching a UAV on a vehicle, characterized in that: The UAV vehicle-mounted launching device according to any one of claims 1 to 6 is adopted, and the UAV vehicle-mounted launching method comprises the following steps: Place the lower frame (15) on the ground and fix it with the support legs (4), ensuring that the upper frame (16) and the lower frame (15) are connected via the connecting rod; the UAV is placed in an inclined state; place the UAV to be launched on the wing soft support (13), fix the UAV with the UAV fixing pin (11), and check that all parts are securely locked; The position of the fixed force nut (502) is adjusted to change the pressure applied to the UAV by the wing soft support (13); the UAV fixing pin (11) in the locking mechanism is released so that the UAV is held only by the wing soft support (13), and the rocket body (1) pushes the UAV to launch.

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