Unmanned aerial vehicle launching and material delivery device and dual-mode general use method

Abstract

This invention discloses a UAV launch and material delivery device and a dual-mode universal usage method in the field of UAV technology. It includes a base for ground contact, a fixed frame mounted on the base, and the fixed frame connected to the base via a steering component. When the steering component operates, the fixed frame rotates along its rotation axis to form an adjustment zone. A rectangular frame is mounted on the fixed frame, with support rods symmetrically hinged to it. The bottom of the rectangular frame is hinged to the end of the support rods to allow for elevation angle adjustment of the rectangular frame. This invention effectively reduces the acceleration impact on the load during launch through a smooth energy storage and release mechanism and a composite buffer recoil structure, protecting the integrity of precision airborne electronic components and fragile materials. Simultaneously, it suppresses damage to the device itself from launch recoil, extends equipment lifespan, and improves the consistency of continuous multiple launches.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV launch and material delivery device and a dual-mode universal usage method. Background Technology

[0002] With the rapid development of low-altitude operation technology, drones, with their advantages of long endurance, high flight speed, and wide operational coverage, have become core operational equipment in fields such as low-altitude logistics, disaster reconnaissance, environmental monitoring, and emergency rescue. Meanwhile, efficient and reliable launch and delivery equipment is a key infrastructure for ensuring the rapid deployment of drones and the precise delivery of emergency supplies. Its launch stability, mission adaptability, and environmental adaptability directly determine the operational response speed and mission success rate, with particularly prominent needs in restricted operational scenarios such as complex terrain and mobile platforms.

[0003] Currently, small fixed-wing UAVs are launched in various ways, including catapult launch, hand-launched launch, and wheeled takeoff. The corresponding launch devices often employ elastic energy storage or pneumatic propulsion to accelerate the payload off-orbit. Emergency supply delivery relies heavily on UAV-borne drop systems or independent launch equipment. In actual emergency and field operation scenarios, UAV takeoff and supply delivery missions often occur simultaneously, requiring both rapid deployment of reconnaissance UAVs to obtain situational awareness and precise delivery of first aid and resupply supplies to designated locations.

[0004] However, existing related devices still have significant shortcomings in practical applications: On the one hand, existing catapult-type devices generally suffer from large launch impact and poor load adaptability. The direct release of stored energy can easily create a steep acceleration curve, and excessively high peak acceleration can damage the delicate sensors and electronic components inside the UAV, making it difficult to adapt to the delivery requirements of fragile emergency supplies. At the same time, the recoil force generated by launch can easily damage the device's own structure, shorten the equipment's service life, and make it difficult to guarantee launch consistency during continuous operation. On the other hand, existing devices generally have single functions and insufficient mission compatibility and environmental adaptability. Most devices are designed for a single model or a single operation scenario, and cannot quickly switch between UAV takeoff and material delivery tasks. This results in the need to equip multiple sets of equipment at the operation site, increasing the logistical burden and deployment time. In addition, most devices have a fixed launch attitude, making it difficult to quickly set up and adjust them on rugged terrain, narrow spaces, or mobile carriers. They also cannot dynamically correct launch parameters according to the site environment, and the control accuracy of the initial launch velocity and landing point is limited, making it difficult to meet the requirements of high-precision operations. Therefore, we urgently need a UAV launch and material delivery device and a dual-mode universal usage method to solve the above problems. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides a drone launch and delivery device and a dual-mode universal usage method. By using a moving pulley system to smoothly store and release energy and a composite buffer to reduce launch impact and protect the precision payload and the device itself, the device can be used for multiple purposes through a modular quick-release interface, reducing the amount of equipment carried. Furthermore, by using multi-sensor visual fusion and closed-loop ballistic calculation, the launch accuracy and mission success rate can be improved.

[0006] The objective of this invention is achieved as follows: It includes a base for contact with the ground; a fixed frame mounted on the base, the fixed frame being connected to the base via a steering component, which rotates along its axis of rotation when the steering component is in operation to form an adjustment zone; a rectangular frame mounted on the fixed frame, with support rods symmetrically hinged to the fixed frame, the bottom of the rectangular frame being hinged to the ends of the support rods to allow for elevation angle adjustment of the rectangular frame; a slide rail fixedly mounted on the rectangular frame, with a launch slide slidably connected to the slide rail, the launch slide having connecting buckles for adapting to different types of launch payloads, the launch slide being reciprocated along the slide rail path via an energy storage launch component on the rectangular frame; and a support frame fixedly mounted on the rectangular frame, with a first support member connected to the support frame via a drive component to transport and dock the payload to be launched to the launch slide, and a second support member mounted on the support frame, the second support member forming a payload storage station for supporting and limiting the payload to be launched.

[0007] Optionally, the steering component includes a first bearing seat fixedly mounted on a base, the bottom of the fixing frame rotatably connected to the first bearing seat, a guide rail fixedly mounted on the base, a first lead screw disposed within the guide rail, both ends of the first lead screw being rotatably connected to the inner wall of the guide rail via bearings, a second bearing seat slidably disposed within the guide rail, the connecting part of the second bearing seat being threadedly connected to the first lead screw, a steering drive motor fixedly connected to the guide rail, the output end of the steering drive motor being connected to the end of the first lead screw, and when the steering drive motor drives the first lead screw to rotate, the second bearing seat reciprocates along the guide rail path to form a moving area.

[0008] Optionally, a mounting platform is rotatably connected to the second bearing housing, and a sliding groove is provided on the mounting platform. A slide bar adapted to the sliding groove is fixedly connected to the bottom of the fixed frame. The slide bar is slidably disposed in the sliding groove. When in the moving area, the mounting platform rotates adaptively around the axis of the second bearing housing, and the slide bar slides along the sliding groove to form an oscillation relative to the fixed frame.

[0009] Optionally, the energy storage launcher includes a first drive motor symmetrically mounted on a rectangular frame, a first pulley symmetrically mounted on the rectangular frame, and a second pulley adapted to the first pulley symmetrically mounted on the other side of the rectangular frame. A first synchronous belt is symmetrically arranged on the rectangular frame, and two sets of the first synchronous belts are respectively connected to the first pulley and the second pulley on the corresponding side. The output ends of the two sets of the first drive motors are respectively connected to the corresponding first pulleys. Hooks for engaging the side wings of the launch slide are fixedly mounted on both sets of the first synchronous belts.

[0010] Optionally, a second lead screw is provided on the longitudinal beam of the rectangular frame and between the two sets of first synchronous belts. Both ends of the second lead screw are rotatably connected to the corresponding uprights on the rectangular frame via bearings. A first guide rail is fixedly installed on the rectangular frame and below the second lead screw. An energy storage buckle is slidably connected to the first guide rail. The connection of the energy storage buckle is threaded to the second lead screw. A second drive motor is fixedly connected to the rectangular frame. The output end of the second drive motor is connected to the end of the second lead screw. When the second drive motor drives the second lead screw to rotate, the energy storage buckle reciprocates along the path of the first guide rail.

[0011] Optionally, a second guide rail is symmetrically installed on the rectangular frame, and a movable pulley slider for spring mounting is slidably connected to each of the second guide rails. Fixed pulleys adapted to the movable pulley sliders are symmetrically installed on the rectangular frame. A spring group is symmetrically installed on the rectangular frame, and the spring group contains two springs. The two ends of the two springs are respectively connected to the rectangular frame and the movable pulley slider.

[0012] Optionally, a buffer block is slidably connected to the side of the slide rail away from the second lead screw. A mounting bracket is fixedly connected to the rectangular frame. Buffer springs are symmetrically installed on the mounting bracket. The other end of the buffer spring is connected to the buffer block. When the launch slide launches, it moves along the slide rail and contacts the buffer block to pull the buffer spring and form a first working area. When the launch slide resets, the buffer block cooperates with the buffer spring to reset and pull the launch slide along the slide rail to form a second working area. Chassis elastic band tensioning blocks are symmetrically installed on the rectangular frame. There are two sets of chassis elastic band tensioning blocks on one side. The two sets of notches are arranged opposite each other and are used to hang the outer ends of the two sections of the braking elastic element to form a fixed installation point. Belt tensioning blocks are symmetrically installed on the rectangular frame. The belt tensioning block on one side is located between the two sets of chassis elastic band tensioning blocks and is used to connect the inner ends of the two sections of the braking elastic element to form an inner traction connection end.

[0013] Optionally, the driving component includes a third motor symmetrically mounted on a support frame. A transmission group is symmetrically mounted on the support frame. The transmission group includes a third pulley and a fourth pulley. A second synchronous belt is driven through the third pulley and the fourth pulley. The output ends of the two sets of third motors are connected to the corresponding third pulleys. The first support component includes a limiting platform that slides symmetrically on the support frame via a fourth guide rail. Both sets of limiting platforms are connected to the second synchronous belt via fixing buckles. A rear baffle is provided on the support frame. The rear baffle is connected to the limiting platform. When the third motor drives the transmission group to run, the limiting platform and the rear baffle move along the path of the fourth guide rail to form a lifting area.

[0014] Optionally, the second support member includes a storage limiting upper plate and a storage limiting lower plate symmetrically mounted on the support frame. The storage limiting upper plate and the storage limiting lower plate on one side are arranged parallel to each other to jointly enclose and form a load sliding channel extending along the length direction of the support frame. A drive servo motor is installed on the support frame and located between the two sets of storage limiting upper plates and storage limiting lower plates. The output end of the drive servo motor is fixedly connected to a mounting hook. The mounting hook is arranged corresponding to the outlet end of the load sliding channel and is used to rotate with the drive servo motor to stop or release the load in the channel.

[0015] A dual-mode universal usage method for a drone launch and material delivery device includes the following steps:

[0016] S1, select the UAV launch mode or material delivery mode according to the mission requirements, and detachably install the corresponding load type bracket slide or box slide on the launch slide through the connecting buckle;

[0017] S2, control the drive servo of the second support to rotate, so that the mounting hook releases the load to be launched in the storage position, and the load falls into the limiting platform of the first support; then, the drive drives the limiting platform to descend along the fourth guide rail, transport the load to dock with the launch slide, and fix the load on the launch slide through the connecting buckle, while obtaining the weight of the load.

[0018] S3. Using the integrated visual detection module, the device acquires images and distance information containing the target area, identifies the target, and generates target spatial coordinates; obtains the current elevation angle attitude of the rectangular frame; based on the target spatial coordinates, load weight, current elevation angle attitude, and environmental parameters, calculates the required target azimuth, target elevation angle, and target value of energy storage pull force based on the ballistic model; controls the steering component to rotate the fixed frame around the axis of the first bearing seat to the target azimuth angle, and adjusts the support rod to make the rectangular frame reach the target elevation angle; simultaneously, controls the energy storage launch component to drive the launch slide to load the elastic component, and performs closed-loop control based on real-time pull force feedback until the target value of energy storage pull force is reached, and then locks the side wing of the launch slide to the energy storage buckle.

[0019] S4: Continuously analyze the real-time images collected by the vision detection module to determine the launch window or delivery timing that meets the preset conditions; when the optimal launch timing is identified, control the energy storage buckle to move to release the launch slide. The launch slide accelerates along the slide rail under the amplified force of the elastic element through the moving pulley slider and the fixed pulley, driving the load off the rail for launch.

[0020] S5: When the launch slide moves to the end of the slide rail, it contacts the buffer block. The remaining kinetic energy is absorbed by the buffer spring and the elastic element between the chassis rubber band tension block and the belt tension block, so as to realize the smooth reset of the launch device.

[0021] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0022] 1. This UAV launch and material delivery device and dual-mode universal usage method effectively reduces the acceleration impact on the load at the moment of launch through a smooth energy storage and release mechanism and a composite buffer recoil structure, protecting the integrity of precision airborne electronic components and fragile materials, while suppressing the damage of launch recoil force to the device itself, extending the service life of the equipment, and improving the consistency of continuous launch operations.

[0023] 2. This UAV launch and material delivery device and dual-mode universal usage method achieves rapid switching between UAV launch mode and material delivery mode through modular quick-release tooling interface, which greatly reduces the amount of equipment carried and deployment preparation time in multi-mission scenarios, and enhances the device's mission adaptability and relocation mobility.

[0024] 3. This UAV launch and material delivery device and dual-mode universal application method improves the accuracy of target coordinate measurement and launch velocity control through multi-sensor fusion visual positioning and closed-loop ballistic calculation control, reduces the dispersion of landing point, and improves the success rate of UAV takeoff and the hit rate of material delivery. At the same time, it supports dynamic optimization of operation parameters and enhances the reliability of mission execution in complex environments. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0026] Figure 1 This is a first-view overall structural diagram of a drone launch and material delivery device and a dual-mode universal usage method.

[0027] Figure 2 This is a second-view overall structural diagram of a drone launch and material delivery device and a dual-mode universal usage method.

[0028] Figure 3 This is a third-view overall structural diagram of a drone launch and material delivery device and a dual-mode universal usage method.

[0029] Figure 4 This invention relates to a drone launch and delivery device and a dual-mode universal usage method. Figure 3 Enlarged structural diagram at point A in the middle.

[0030] Figure 5 This invention relates to a drone launch and delivery device and a dual-mode universal usage method. Figure 3 Enlarged structural diagram at point B.

[0031] Figure 6 This is a schematic diagram of the first cross-section of a drone launch and delivery device and a dual-mode universal usage method.

[0032] Figure 7 This invention relates to a drone launch and delivery device and a dual-mode universal usage method. Figure 6 Enlarged structural diagram at point C.

[0033] Figure 8 This is a schematic diagram of the second cross-section of a drone launch and delivery device and a dual-mode universal usage method.

[0034] Figure 9 This is a schematic diagram of the signal transmission process for a drone launch and delivery device and a dual-mode universal application method.

[0035] The diagram shows the following components: 1. Base; 2. Fixing frame; 3. Rectangular frame; 4. Support rod; 5. Slide rail; 6. Launching slide; 7. Connecting buckle; 8. Support frame; 9. First bearing seat; 10. Guide rail; 11. First lead screw; 12. Second bearing seat; 13. Steering drive motor; 14. Mounting platform; 15. Sliding groove; 16. Sliding bar; 17. First drive motor; 18. First pulley; 19. Second pulley; 20. First synchronous belt; 21. Hook; 22. Second lead screw; 23. First guide rail; 24. Storage 25. Second drive motor; 26. Second guide rail; 27. Movable pulley slider; 28. Fixed pulley; 29. ​​Spring assembly; 30. Buffer block; 31. Mounting bracket; 32. Buffer spring; 33. Chassis elastic band tensioning block; 34. Belt tensioning block; 35. Third motor; 36. Third pulley; 37. Fourth pulley; 38. Second synchronous belt; 39. Fourth guide rail; 40. Limiting platform; 41. Rear baffle; 42. Storage limit upper plate; 43. Storage limit lower plate; 44. Drive servo motor; 45. Mounting hook. Detailed Implementation

[0036] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0037] like Figure 1-9 The device shown is a drone launch and delivery device and a dual-mode universal usage method, including a base 1 for contacting the ground.

[0038] A fixed frame 2 is mounted on a base 1 and connected to the base 1 via a steering component. When the steering component is in operation, the fixed frame 2 rotates along its rotation axis to form an adjustment zone. The steering component includes a first bearing seat 9 fixedly mounted on the base 1. The bottom of the fixed frame 2 is rotatably connected to the first bearing seat 9. A guide rail 10 is fixedly mounted on the base 1. A first lead screw 11 is provided inside the guide rail 10. Both ends of the first lead screw 11 are rotatably connected to the inner wall of the guide rail 10 via bearings. A second bearing seat 12 is slidably mounted inside the guide rail 10. The connecting part of the second bearing seat 12 is threadedly connected to the first lead screw 11. A steering drive motor 13 is fixedly connected to the guide rail 10. The output end of the steering drive motor 13 is connected to the end of the first lead screw 11. When the steering drive motor 13 drives the first lead screw 11 to rotate, the second bearing seat 12 slides back and forth along the path of the guide rail 10 to form a moving zone.

[0039] Here, the first bearing seat 9 is fixed at the center of the base 1, forming the main rotation support point of the fixed frame 2. The guide rail 10 is arranged along the radial direction of the base 1. The first lead screw 11 is arranged coaxially with the guide rail 10. The bottom of the second bearing seat 12 is embedded in the groove of the guide rail 10, forming circumferential limiting and sliding guidance. The base 1 can be fixed to the ground or installed on a mobile carrier through an adjustable leveling base. The mobile carrier includes vehicles, ships, etc., to adapt to the deployment needs of different terrains.

[0040] Furthermore, the steering drive motor 13 outputs torque to drive the first lead screw 11 to rotate, and the rotational motion is converted into the linear reciprocating motion of the second bearing seat 12 through the thread transmission. The second bearing seat 12 applies an eccentric thrust to the fixed frame 2 through the upper connecting structure, pushing the fixed frame 2 to rotate around the axis of the first bearing seat 9, thereby realizing the adjustment of the launch azimuth angle.

[0041] Furthermore, the steering layout using a central main support and side screw drive simplifies the slewing drive structure while ensuring load-bearing capacity, eliminating the need to process large-sized slewing bearings and reducing the manufacturing cost of the device. At the same time, the screw drive has a self-locking characteristic, which can maintain a stable azimuth angle after adjustment, and can resist attitude deviation caused by bumps even when operating on a moving carrier.

[0042] A mounting platform 14 is rotatably connected to the second bearing seat 12. A sliding groove 15 is provided on the mounting platform 14. A slide bar 16 adapted to the sliding groove 15 is fixedly connected to the bottom of the fixed frame 2. The slide bar 16 is slidably disposed in the sliding groove 15. When in the moving area, the mounting platform 14 rotates adaptively around the axis of the second bearing seat 12, and the slide bar 16 slides along the sliding groove 15 to form an oscillation relative to the fixed frame 2.

[0043] Here, the bottom of the mounting platform 14 is fitted into the inner ring of the second bearing seat 12 via a rotating shaft. The sliding groove 15 is opened through the length of the mounting platform 14. The cross-sectional shape of the slide bar 16 matches the cross-sectional shape of the sliding groove 15 to form a sliding fit relationship.

[0044] Furthermore, when the second bearing seat 12 translates along the guide rail 10, the fixed frame 2 moves around the first bearing seat 9 in an arc trajectory. The adaptive rotation of the mounting platform 14 and the relative sliding of the slide bar 16 can jointly compensate for the radial displacement difference and angular difference caused by the arc motion, avoid motion interference in the transmission structure, and ensure the smoothness of the steering process.

[0045] Furthermore, by adopting a composite compensation structure of rotation and sliding, the second bearing seat 12 can provide effective support for the fixed frame 2 at any position, ensuring the structural rigidity of the fixed frame 2 within the full range of rotation angles, while simplifying the design difficulty of the transmission chain.

[0046] A rectangular frame 3 is mounted on a fixed frame 2. Support rods 4 are symmetrically hinged to the fixed frame 2. The bottom of the rectangular frame 3 is hinged to the end of the support rods 4 to allow for adjustment of the elevation angle of the rectangular frame 3.

[0047] Here, the bottom rear side of the rectangular frame 3 is rotatably connected to the upper rear side of the fixed frame 2 through a hinge shaft. Two support rods 4 are symmetrically arranged on the left and right sides of the fixed frame 2. The two ends of the support rods 4 are connected to the fixed frame 2 and the rectangular frame 3 through hinge shafts to form a triangular support structure.

[0048] Furthermore, the support rod 4 can adopt an adjustable length rod structure. By changing the effective length of the support rod 4, the rectangular frame 3 can be driven to rotate around the bottom hinge axis, so as to realize the continuous adjustment of the launch elevation angle. After adjusting to the target angle, the rod length can be kept fixed by the locking structure to maintain the stability of the elevation attitude, thereby dynamically adjusting the launch attitude according to the real-time wind direction to counteract the crosswind effect.

[0049] Furthermore, the symmetrically arranged hinged support rods 4 are subjected to balanced forces, which can effectively withstand the axial recoil force generated during launch and prevent deviation of the elevation attitude. At the same time, the hinged adjustment structure is simple, easy to operate and maintain on site, and adaptable to different launch angle requirements in different scenarios such as rugged mountains and narrow urban buildings.

[0050] The slide rail 5 is fixedly installed on the rectangular frame 3. The launch slide 6 is slidably connected to the slide rail 5. The launch slide 6 is provided with a connecting buckle 7 for adapting to different types of launch payloads. The launch slide 6 is driven to move back and forth along the path of the slide rail 5 by the energy storage launch component on the rectangular frame 3.

[0051] Here, the slide rail 5 is fixedly arranged parallel to the length of the rectangular frame 3. The bottom of the launch slide 6 is provided with a slide groove structure that is compatible with the slide rail 5, forming a linear sliding fit. The connecting buckle 7 is arranged on the upper surface of the launch slide 6, forming a detachable load installation interface. The connecting buckle 7 is a quick-release buckle system, which is used to cooperate with the 3D printed redesignable bracket slide or box slide to realize the quick replacement of different load tooling.

[0052] Furthermore, the energy storage launcher and the launch slide 6 form a transmission connection. During the energy storage phase, the launch slide 6 is driven to move along the slide rail 5 towards the tail to complete the storage of elastic potential energy. During the release phase, the launch slide 6 is driven to move along the slide rail 5 towards the launch end to accelerate and push the load to complete the off-track action.

[0053] Furthermore, the linear launch mode guided by the slide rail 5 ensures the consistency of the payload's launch attitude and improves launch accuracy. The quick-release interface of the connecting buckle 7, combined with the 3D-printed redesignable tooling, can be adapted to different payload bearing requirements, making the device compatible with various types of launch payloads and expanding its application scenarios.

[0054] The energy storage launcher includes a first drive motor 17 symmetrically mounted on a rectangular frame 3. A first pulley 18 is symmetrically mounted on the rectangular frame 3, and a second pulley 19 adapted to the first pulley 18 is symmetrically mounted on the other side. A first synchronous belt 20 is symmetrically arranged on the rectangular frame 3. The two sets of first synchronous belts 20 are respectively connected to the first pulley 18 and the second pulley 19 on the corresponding sides. The output ends of the two sets of first drive motors 17 are respectively connected to the corresponding first pulley 18. Hooks 21 for engaging the side wings of the launch slide 6 are fixedly mounted on both sets of first synchronous belts 20.

[0055] Here, the first pulley 18 is located on the rear side of the rectangular frame 3, the second pulley 19 is located on the head side of the rectangular frame 3, the first synchronous belt 20 is tensioned and assembled along the length of the rectangular frame 3, and the hook 21 is fixed to the outside of the belt body of the first synchronous belt 20 and extends toward the launch slide 6.

[0056] Furthermore, during the energy storage phase, the first drive motor 17 drives the first pulley 18 to rotate, which in turn drives the first synchronous belt 20 to rotate along the slide rail 5. The hook 21 moves with the belt to the launch slide 6 and engages with the side wing of the launch slide 6. Then, it continues to drive the launch slide 6 to move towards the tail to complete the energy storage loading action. After the energy storage loading is completed, the first drive motor 17 reverses and drives the hook 21 back to the initial position, preparing for the next launch.

[0057] Furthermore, the layout of the dual-sided synchronous belt synchronous drive ensures balanced force distribution, preventing the launch slide 6 from becoming skewed or jammed during movement. The synchronous belt drive operates smoothly and can precisely control the energy storage displacement of the launch slide 6, ensuring the stability and consistency of the energy storage process.

[0058] A second lead screw 22 is installed on the longitudinal beam of the rectangular frame 3 between the two sets of first synchronous belts 20. Both ends of the second lead screw 22 are rotatably connected to the corresponding uprights on the rectangular frame 3 via bearings. A first guide rail 23 is fixedly installed on the rectangular frame 3 below the second lead screw 22. An energy storage buckle 24 is slidably connected to the first guide rail 23. The connection of the energy storage buckle 24 is threaded to the second lead screw 22. A second drive motor 25 is fixedly connected to the rectangular frame 3. The output end of the second drive motor 25 is connected to the end of the second lead screw 22. When the second drive motor 25 drives the second lead screw 22 to rotate, the energy storage buckle 24 reciprocates along the path of the first guide rail 23.

[0059] Here, the second lead screw 22 is arranged along the length of the rectangular frame 3, the first guide rail 23 is arranged parallel to the second lead screw 22, the bottom of the energy storage buckle 24 is in sliding fit with the first guide rail 23, the threaded hole on the side is in fit with the second lead screw 22 to form a lead screw transmission pair, and the buckle body extends out toward the side of the slide rail 5.

[0060] Furthermore, the second drive motor 25 drives the second lead screw 22 to rotate, and drives the energy storage buckle 24 to translate along the first guide rail 23 through thread transmission, adjusting the axial position of the energy storage buckle 24. When the launch slide 6 moves to the energy storage buckle 24 during the energy storage stage, the energy storage buckle 24 engages with the side wing of the launch slide 6 to complete the locking. When unlocking, the energy storage buckle 24 moves under the drive of the second drive motor 25 to release the engagement, thereby releasing the launch slide 6.

[0061] Furthermore, by adjusting the position of the energy storage latch 24 via the lead screw, the energy storage stroke can be continuously changed, achieving stepless adjustment of the initial launch velocity to adapt to the launch requirements of different weight loads. The lead screw drive has a self-locking characteristic, which can ensure the stability and reliability of the energy storage locked state.

[0062] A second guide rail 26 is symmetrically installed on the rectangular frame 3. A movable pulley slider 27 for spring mounting is slidably connected to each of the second guide rails 26. A fixed pulley 28 adapted to the movable pulley slider 27 is symmetrically installed on the rectangular frame 3. A spring group 29 is symmetrically installed on the rectangular frame 3. There are two springs in the spring group 29. The two ends of the two springs are respectively connected to the rectangular frame 3 and the movable pulley slider 27.

[0063] Here, the second guide rail 26 is arranged along the length of the rectangular frame 3 on the side of the slide rail 5, the bottom of the movable pulley slider 27 is in sliding fit with the second guide rail 26, the fixed pulley 28 is fixed on the rear upright of the rectangular frame 3, and the spring assembly 29 is arranged along the axial direction of the second guide rail 26, with its two ends connected to the front upright of the rectangular frame 3 and the movable pulley slider 27 respectively.

[0064] Furthermore, one end of the transmission rope is fixed to the tail support of the rectangular frame 3, and then passes sequentially around the movable pulley installed on the movable pulley slider 27, then around the fixed pulley 28, then around another movable pulley on the movable pulley slider 27, and finally around another fixed pulley 28. The other end is fixed to a fixed point at one end of the fixed pulley 28. The lead end of the transmission rope is connected to the side of the launching slide 6. Through the above winding method, a multi-stage movable pulley group is formed. During the energy storage stage, the launching slide 6 moves backward and pulls the movable pulley slider 27 along the second guide rail 26 through the transmission rope. The compressed spring group 29 stores elastic potential energy. During the release stage, the spring group 29 rebounds and drives the launching slide 6 to accelerate forward through the pulley group.

[0065] Furthermore, by adopting a structure combining a fixed pulley 28 and a multi-stage movable pulley slider 27, the mechanical advantages of the pulley system can be utilized to transform the short-stroke high-acceleration contraction of the spring assembly 29 into the long-stroke low-acceleration motion of the launch slide 6, thus smoothing the launch acceleration curve, reducing the impact load at the moment of launch, achieving flexible launch of precision loads, controlling the launch state more smoothly, and minimizing the impact on the launch object. This effectively protects the IMU inertial measurement unit and electronic components inside the fixed-wing UAV, as well as fragile medical emergency supplies.

[0066] A buffer block 30 is slidably connected to the side of the slide rail 5 away from the second lead screw 22. A mounting bracket 31 is fixedly connected to the rectangular frame 3. Buffer springs 32 are symmetrically installed on the mounting bracket 31. The other end of the buffer spring 32 is connected to the buffer block 30. When the launching slide 6 launches, it moves along the slide rail 5 and contacts the buffer block 30 to pull the buffer spring 32 to form the first working area. When the launching slide 6 resets, the buffer block 30 cooperates with the buffer spring 32 to reset, pulling the launching slide 6 to move along the slide rail 5 and form the second working area. The rectangular frame 3 is symmetrically installed with chassis elastic band tensioning blocks 33. There are two sets of chassis elastic band tensioning blocks 33 on one side. The two sets of notches are arranged opposite each other and are used to hang the outer ends of the two sections of the braking elastic element to form a fixed installation point. The rectangular frame 3 is symmetrically installed with belt tensioning blocks 34. The belt tensioning blocks 34 on one side are located between the two sets of chassis elastic band tensioning blocks 33 and are used to connect the inner ends of the two sections of the braking elastic element to form an inner pulling connection end.

[0067] Here, the buffer block 30 is fitted onto the exit end of the slide rail 5 and can slide along the axial direction of the slide rail 5. The mounting bracket 31 is fixed to the exit end of the rectangular frame 3. The buffer spring 32 is arranged along the direction of the slide rail 5, and the two ends are respectively connected to the mounting bracket 31 and the buffer block 30. The chassis elastic band tension block 33 and the belt tension block 34 are evenly arranged on the longitudinal beams on both sides of the rectangular frame 3. The outer ends of the two sections of the braking elastic element are respectively hung on the notches of the two sets of chassis elastic band tension blocks 33, and the inner ends are jointly hung on the belt tension block 34, forming a bidirectional symmetrical pulling braking force layout.

[0068] Furthermore, during the launch phase, when the launch slide 6 moves to the end of the slide rail 5, it contacts the buffer block 30. The buffer block 30 compresses the buffer spring 32 to absorb the remaining kinetic energy of the launch slide 6. At the same time, the two sections of recoil-controlling elastic members mounted between the chassis elastic band tension block 33 and the belt tension block 34 constrain the entire launch energy storage mechanism connected to the belt tension block 34 through bidirectional traction, causing the launch energy storage mechanism to oscillate slightly in the launch direction and quickly return to a stationary state, absorbing the recoil force generated during the launch process, limiting the recoil displacement of the launch energy storage mechanism, and suppressing the transmission of recoil impact to the load.

[0069] Furthermore, a composite buffering and recoil control structure with bidirectional pulling of the elastic element at the end of the slide can simultaneously absorb the remaining kinetic energy of the launch slide 6 and the overall recoil force of the launch energy storage mechanism, reducing the overall vibration amplitude, shortening the reset stabilization time, ensuring the consistency of the device during multiple consecutive launches and extending the service life of the facility, protecting the airborne electronic equipment and improving the consistency of multiple launches.

[0070] The support frame 8 is fixedly installed on the rectangular frame 3. The support frame 8 is connected to the first support member by a drive component to transport and dock the load to be launched to the launch slide 6. The support frame 8 is provided with a second support member, which forms a load storage station to support and limit the load to be launched.

[0071] Here, the support frame 8 is fixed above the tail of the rectangular frame 3 and is arranged along the inclined direction of the slide rail 5. The first support member is arranged on the inner side of the support frame 8 and can slide back and forth along the length of the support frame 8. The second support member is arranged above the first support member and is vertically aligned with the initial receiving position of the first support member.

[0072] Furthermore, the second support is used to temporarily store the payload to be launched. After receiving the loading command, the payload is released and falls onto the first support below under the action of gravity. The first support moves along the support frame 8 towards the launch slide 6 under the drive of the drive component, and transports the payload to the launch slide 6 to complete the docking and loading.

[0073] Furthermore, the integrated storage and conveying filling structure enables automatic loading of loads without the need for manual feeding, improving the automation level of the device and the convenience of field operations. The compact, layered layout also occupies less space.

[0074] The driving component includes a third motor 35 symmetrically mounted on the support frame 8. A transmission group is symmetrically mounted on the support frame 8. The transmission group includes a third pulley 36 and a fourth pulley 37. A second synchronous belt 38 is driven to the third pulley 36 and the fourth pulley 37. The output ends of the two sets of third motors 35 are connected to the corresponding third pulleys 36. The first support component includes a limiting platform 40 that slides symmetrically on the support frame 8 via a fourth guide rail 39. Both sets of limiting platforms 40 are connected to the second synchronous belt 38 via fixing buckles. A rear baffle 41 is provided on the support frame 8. The rear baffle 41 is connected to the limiting platform 40. When the third motor 35 drives the transmission group to run, the limiting platform 40 and the rear baffle 41 move along the path of the fourth guide rail 39 to form a lifting area.

[0075] Here, the third pulley 36 is arranged on the upper side of the support frame 8, the fourth pulley 37 is arranged on the lower side of the support frame 8, the second synchronous belt 38 is tensioned and assembled along the direction of the fourth guide rail 39, the fourth guide rail 39 is fixed to the inner side of the support frame 8 along the length direction of the support frame 8, the side of the limiting platform 40 forms a sliding fit with the fourth guide rail 39, the bottom is fixedly connected to the second synchronous belt 38, and the rear baffle 41 is vertically fixed to the tail end face of the limiting platform 40 to assist in fixing the load.

[0076] Furthermore, the third motor 35 drives the third pulley 36 to rotate, which in turn drives the second synchronous belt 38 to operate. The second synchronous belt 38 drives the limiting platform 40 to move back and forth along the fourth guide rail 39. When receiving materials, the limiting platform 40 moves upward to the storage station outlet to receive the released load. The rear baffle 41 blocks the tail of the load to prevent it from sliding out. Then it moves downward to transport the load to the launching slide 6.

[0077] Furthermore, the synchronous belt guide rail conveying structure ensures a smooth conveying process and high positional accuracy, guaranteeing precise docking between the load and the launch slide 6. The rear baffle 41 restricts the axial position of the load, preventing displacement during conveying and ensuring consistent loading posture.

[0078] The second support includes a storage limiting upper plate 42 and a storage limiting lower plate 43 symmetrically installed on the support frame 8. The storage limiting upper plate 42 and the storage limiting lower plate 43 on one side are arranged vertically parallel to each other to jointly enclose and form a load sliding channel extending along the length of the support frame. A drive servo motor 44 is installed on the support frame 8 between the two sets of storage limiting upper plates 42 and storage limiting lower plates 43. The output end of the drive servo motor 44 is fixedly connected to a load hook 45. The load hook 45 is arranged at the outlet end of the load sliding channel and is used to rotate with the drive servo motor 44 to stop or release the load in the channel.

[0079] Here, the upper storage limit plate 42 and the lower storage limit plate 43 are arranged parallel to each other along the inclined direction of the support frame 8. The distance between the two plates is adapted to the height of the load, forming a sliding channel for the load. The drive servo motor 44 is fixed to the middle upright plate of the support frame 8, and the hanging hook 45 is fixed to the output shaft of the drive servo motor 44 and extends into the sliding channel.

[0080] Furthermore, in the standby state, the load hook 45 is in the stop position, blocking the load in the channel to prevent it from sliding down. When released, the drive servo motor 44 drives the load hook 45 to rotate, disengaging from the load support position. Under the action of gravity, the load slides down along the channel formed by the upper and lower limit plates and falls onto the lower limit platform 40.

[0081] Furthermore, the structure of using an inclined slide formed by upper and lower limit plates in conjunction with gravity unloading is simple and reliable. It can complete the transfer of loads without the need for additional conveyor drive. The locking and releasing structure of the servo motor driven hook has a fast action response, simple control logic, and can accurately control the timing of unloading.

[0082] A dual-mode universal usage method for a drone launch and material delivery device includes the following steps:

[0083] S1, select the UAV launch mode or material delivery mode according to the mission requirements, and detachably install the corresponding load type bracket slide or box slide onto the launch slide 6 through the connecting buckle 7.

[0084] Here, the bracket slide is adapted to the fuselage shape of small fixed-wing UAVs, while the boxed slide is adapted to the size of standardized supply boxes. Both slides have a docking structure at the bottom that matches the connecting buckle 7, allowing for quick installation and disassembly. Both the bracket slide and the boxed slide can be manufactured using 3D printing redesign to meet the loading requirements of different models or different specifications of supply boxes.

[0085] Furthermore, when switching modes, first disengage the current slide from the connecting clip 7, remove the original tooling, then align the target tooling with the positioning structure of the launch slide 6, and fasten the connecting clip 7 to complete the fixation. This will complete the switching of working modes, such as switching from inspection mode to rescue mode, or from drone launch mode to material delivery mode.

[0086] Furthermore, the modular tooling replacement method is easy to operate and can quickly switch working modes without adjusting the main launch structure, which greatly reduces the amount of equipment carried for operations, as well as the preparation and deployment time before operations. The quick-release structure improves the flexibility and convenience of the launch pad, which is conducive to mission transportation and transfer.

[0087] S2, control the drive servo 44 of the second support to rotate, so that the mounting hook 45 releases the load to be launched in the storage position, and the load falls into the limiting platform 40 of the first support; then, the drive unit drives the limiting platform 40 to descend along the fourth guide rail 39, transporting the load to dock with the launch slide 6, and fixing the load on the launch slide 6 through the connecting buckle 7, while obtaining the weight of the load.

[0088] Here, the load weight can be calculated by collecting the initial tension value through the tension sensor connected to the energy storage transmission circuit, or it can be directly retrieved through the preset load type parameters to provide basic data for subsequent ballistic calculations.

[0089] Furthermore, when the limiting platform 40 carries the load down to the corresponding position of the launch slide 6, the mating structure at the bottom of the load docks with the tooling on the launch slide 6, and the connecting buckle 7 completes the locking and fixing. Then the limiting platform 40 continues to descend slightly to detach from the load and returns to the initial position to wait for the next loading.

[0090] Furthermore, the automated loading process enables smooth transfer and precise docking of the payload, avoiding attitude errors caused by manual loading. At the same time, it automatically acquires payload weight parameters, which can improve the accuracy of ballistic calculations and the efficiency of launch operations.

[0091] S3: The device uses an integrated visual detection module to acquire images and distance information containing the target area, identifies the target, and generates target spatial coordinates; it acquires the current elevation angle attitude of the rectangular frame 3; based on the target spatial coordinates, load weight, current elevation angle attitude, and environmental parameters, it calculates the required target azimuth angle, target elevation angle, and target value of energy storage pull force based on the ballistic model; it controls the steering component to rotate the fixed frame 2 around the axis of the first bearing seat 9 to the target azimuth angle, and adjusts the support rod 4 to make the rectangular frame 3 reach the target elevation angle; at the same time, it controls the energy storage launch component to drive the launch slide 6 to load the elastic component, and performs closed-loop control based on real-time pull force feedback until the target value of energy storage pull force is reached, and then locks the side wing of the launch slide 6 at the energy storage buckle 24.

[0092] Here, the visual detection module includes an industrial camera and a laser rangefinder, which are coaxially arranged at the head of the rectangular frame 3. The industrial camera is used to acquire visible light images of the target area, and the laser rangefinder is used to simultaneously acquire precise distance information between the target and the transmitting device. The two work together to achieve simultaneous visual and laser detection to generate the spatial coordinates of the target. Environmental parameters, including on-site wind speed, wind direction, and air temperature, can be acquired through the matching environmental sensors, and the elevation angle can be acquired through the tilt sensor.

[0093] Furthermore, the ballistic calculation process is completed by the host computer. The host computer receives images transmitted from the industrial camera and distance data transmitted from the laser rangefinder. It automatically identifies the target through a locally deployed large-scale model vision recognition system, generates an intelligent bounding box, optimizes the bounding area by combining scene depth information, automatically analyzes and locks the target area, and calculates the basic launch elevation angle, azimuth angle, and initial energy storage thrust by combining the target's three-dimensional coordinates and the weight parameters of the payload. Then, it corrects the ballistic parameters by combining environmental parameters to obtain the final target control parameters. Subsequently, the host computer sends control commands to the slave computer, which drives the steering drive motor 13 to complete the azimuth angle adjustment and drive the support. Rod 4 completes the elevation angle adjustment, driving the first drive motor 17 to complete the energy storage loading. During the energy storage loading process, the tension sensor collects the energy storage tension value in real time and feeds it back to the lower computer. The lower computer performs closed-loop adjustment through PID control algorithm to ensure that the energy storage tension accurately reaches the target value. At the same time, the lower computer controls the second drive motor 25 to drive the energy storage buckle 24 to complete the locking of the launch slide 6. The upper computer and the lower computer communicate through serial port. The upper computer is responsible for visual image processing tasks that require high computing power, while the lower computer is responsible for the real-time control tasks of each motor. This involves comprehensive calculation of control methods for different mechanical structure connection methods such as lead screw structure, gear structure and brushless motor synchronous belt structure.

[0094] Furthermore, the hardware solution employing simultaneous detection by industrial cameras and laser rangefinders can improve the measurement accuracy of target coordinates and achieve precise coordinate positioning. The distributed control architecture of the host and slave computers can separate the high-computing-power visual processing tasks from the real-time motor control tasks, improving system response speed and control accuracy. The multi-parameter fusion ballistic calculation method, combined with algorithms to seek the target distance and optimal launch angle, can improve the accuracy of launch and delivery, enabling the UAV to accurately and quickly reach the target location. The closed-loop energy storage pull control can ensure the accuracy of energy storage, reduce the impact of spring fatigue, ambient temperature and other factors on the initial launch velocity, and improve launch consistency.

[0095] As a preferred implementation, the host computer can use an Intel i7 NUC to handle visual image tasks requiring high computing power, including receiving images from industrial cameras, operating a locally deployed large-scale visual recognition system, target recognition and positioning, and dynamic optimization of ballistic model deduction and operating parameters. The slave computer can use an STM32F4ZGT6 microcontroller to communicate with the Intel i7 NUC as the host computer via a serial port. It receives control commands from the host computer, such as the target azimuth angle, target elevation angle, and target value of the energy storage tension, and is responsible for controlling the movement of various motors. This includes the comprehensive calculation of control methods for different mechanical structure connection methods, such as the lead screw structure involved in the steering drive motor 13, the synchronous belt structure involved in the first drive motor 17, and the lead screw structure involved in the second drive motor 25. Through the distributed control architecture of the host and slave computers, the high-computing-power visual processing tasks and real-time motor control tasks are effectively separated, which can improve the system's response speed and control accuracy, and ensure the stability and accuracy of the launch process.

[0096] S4: Continuously analyze the real-time images collected by the visual detection module to determine the launch window or delivery timing that meets the preset conditions; when the optimal launch timing is identified, control the energy storage buckle 24 to move to release the launch slide 6. The launch slide 6 accelerates along the slide rail 5 under the amplified force of the elastic element through the moving pulley slider 27 and the fixed pulley 28, driving the load off the rail for launch.

[0097] Here, the preset conditions for the launch window include the target entering the preset delivery area, the ambient wind speed being within the allowable range, and the device attitude being stable and without abnormalities. When all conditions are met, the device is determined to be in a launchable state. For UAV launch mode, the onboard lightweight vision module and IMU attitude sensing unit integrated on the payload can communicate with the flight control via serial port to identify the delivery window in real time and determine the launch timing, thereby achieving closed-loop control of the launch timing.

[0098] Furthermore, upon receiving the launch command, the energy storage latch 24 releases its lock on the launch slide 6 under the drive of the second drive motor 25. The spring assembly 29 releases its elastic potential energy, and through the multi-stage moving pulley assembly composed of the moving pulley slider 27 and the fixed pulley 28, the mechanical advantage is used to transform the short-stroke contraction of the spring assembly 29 into the long-stroke low-acceleration motion of the launch slide 6. When it reaches the end of the slide rail 5, the load reaches the takeoff speed or the initial delivery speed, and it leaves the slide to complete the launch. The acceleration curve is relatively flat throughout the acceleration process, which can reduce the instantaneous impact on the precision load.

[0099] Furthermore, the launch timing judgment based on industrial cameras and large-scale model visual recognition can improve the accuracy of the delivery mission. The smooth acceleration of the launch process by the pulley system can reduce the impact on the internal structure of the payload, which helps to improve the reliability of the launch process and the integrity rate of the payload. The host computer, based on the data base composed of real-time images and multi-dimensional sensor fusion information, can dynamically optimize and correct subsequent operation parameters, continuously improving launch accuracy.

[0100] S5: When the launch slide 6 moves to the end of the slide rail 5, it contacts the buffer block 30. The remaining kinetic energy is absorbed by the buffer spring 32 and the elastic element between the chassis elastic band tension block 33 and the belt tension block 34, so as to realize the smooth reset of the launch device.

[0101] Here, the energy absorption process is divided into two stages: slide buffering and overall mechanism retraction. In the slide buffering stage, the launching slide 6 impacts the buffer block 30, and the buffer block 30 compresses the buffer spring 32 to absorb the remaining kinetic energy of the slide. In the overall mechanism retraction stage, the two sections of retraction-controlling elastic elements mounted between the chassis elastic band tension block 33 and the belt tension block 34 absorb the recoil force generated by the launch through bidirectional traction, limiting the recoil displacement of the launch energy storage mechanism. The two stages work in sequence to jointly consume all the kinetic energy generated during the launch process and prevent the device from experiencing large-scale oscillations.

[0102] Furthermore, after the energy absorption is completed, the launch slide 6 returns to the initial standby position along the slide rail 5 under the rebound force of the buffer spring 32. The whole machine returns to a stationary state under the elastic force of the retraction elastic element, and can then enter the next loading and launching operation cycle. The entire reset process does not require manual intervention.

[0103] Furthermore, the composite buffer recoil structure can effectively dissipate the kinetic energy generated during the launch process, reduce the vibration and recoil of the entire device, significantly reduce the peak recoil force, reduce the impact transmission to the deployment platform or mobile carrier, enable the launch device to quickly return to a stable state, extend the service life of the device, and at the same time, the rapid reset feature can shorten the waiting time between two launches, support multiple launches in a row, and help improve the ability to operate continuously.

[0104] It is important to note that the device's communication system constructs a multi-layered, highly reliable transmission architecture. In addition to the dedicated frequency band for FPV image transmission, it also integrates a 4G / 5G cellular communication module, supporting dual-mode networking. Encryption algorithms are used to encrypt transmitted data, ensuring that the cloud platform at a distance can receive device status and high-definition images in real time, achieving data sharing within seconds and meeting the needs of multi-device collaborative scenarios. The device has a reserved Ethernet interface to support high-speed data transmission. When deployed on a fixed carrier, it can connect to a wired network to achieve priority scheduling of data transmission, reducing the latency of critical operations. All communication modules have anti-interference designs, which can effectively avoid interference and maintain communication stability in complex electromagnetic environments.

[0105] Example 1: Operation in UAV launch mode:

[0106] This embodiment corresponds to the operational scenario of rapid deployment and launch of a large number of small fixed-wing UAVs. The specific implementation process is as follows:

[0107] First, after deploying the device in the field, the ground station selects the UAV mode and enters the UAV model, selects the bracket slide that is compatible with the target UAV, aligns the bracket slide with the upper surface positioning structure of the launch slide 6, and engages the connecting buckle 7 to complete the tooling fixation, thus completing the configuration of the UAV launch mode.

[0108] Next, the small fixed-wing UAV to be launched is placed into the second support member of the support frame 8. The UAV body is inserted into the load sliding channel formed by the upper storage limit plate 42 and the lower storage limit plate 43. The mounting hook 45 supports the bottom of the UAV, so that the UAV is stably stored in the storage position.

[0109] Subsequently, the automatic loading process is executed, controlling the drive servo motor 44 to rotate, which drives the mounting hook 45 to rotate downward to release the stop. The drone slides down the inclined sliding channel by its own weight and falls onto the lower limiting platform 40. The rear baffle 41 blocks the tail of the drone to complete the axial positioning.

[0110] Next, the third motor 35 starts, driving the second synchronous belt 38 to rotate through the third pulley 36 and the fourth pulley 37, which in turn drives the limiting platform 40 to descend smoothly along the fourth guide rail 39 towards the launch slide 6, accurately transporting the drone to the top of the bracket slide. The drone body falls into the adapter slot of the bracket slide, and the connecting buckle 7 assists in locking to complete the loading. After the limiting platform 40 descends slightly to detach from the drone, it returns to the upper receiving position.

[0111] Afterwards, parameter calculation and attitude energy storage are performed. The system automatically adjusts the yaw angle based on the obstruction of the launch direction transmitted back by the industrial camera. The ground analysis software, combined with the locally deployed large model visual recognition system, automatically generates intelligent selection boxes, optimizes the selection area by combining scene depth information, automatically analyzes and locks the target area, and the tilt sensor collects the current elevation angle of the rectangular frame 3. Combined with the weight of the UAV and the environmental wind speed parameters, the target azimuth angle, target elevation angle and target value of energy storage pull are calculated through the ballistic model.

[0112] Next, the steering drive motor 13 starts, and through the cooperation of the first lead screw 11 and the second bearing seat 12, it pushes the fixed frame 2 to rotate around the axis of the first bearing seat 9 to the target azimuth angle. The length of the support rod 4 is adjusted, which drives the rectangular frame 3 to rotate around its bottom hinge axis to the target elevation angle and lock it. At the same time, the first drive motor 17 starts, and pulls the launch slide 6 backward through the hook 21 on the first synchronous belt 20. The launch slide 6 is linked with the multi-stage movable pulley group through the transmission rope, so that the movable pulley slider 27 moves along the second guide rail 26 and compresses the spring group 29 to store energy. The tension sensor transmits data back in real time. After the target tension value corresponding to the preset derailment initial velocity is reached, the energy storage buckle 24 is locked into the side wing of the launch slide 6. The first drive motor 17 reverses and drives the hook 21 to reset.

[0113] Finally, the launch and reset process is executed. The vision module continuously monitors the takeoff environment. After confirming that the launch conditions are met, the energy storage latch 24 releases the lock on the launch slide 6. The spring assembly 29 releases potential energy. Through the multi-stage moving pulley assembly composed of the moving pulley slider 27 and the fixed pulley 28, the short stroke contraction of the spring is converted into a long stroke low acceleration motion of the launch slide 6, which drives the launch slide 6 to accelerate forward along the slide rail 5. Since the acceleration curve is flat, the UAV IMU does not need a long preheating and calibration. When it reaches the end of the slide rail 5, the UAV smoothly leaves the rail and climbs by its own power, achieving a zero-accident takeoff.

[0114] The launch slide 6 moves to the end of the slide rail 5 and impacts the buffer block 30. The buffer spring 32 absorbs the remaining kinetic energy of the slide. At the same time, the recoil elastic element between the chassis elastic band tension block 33 and the belt tension block 34 absorbs the recoil force of the whole machine, so that the launch device can quickly return to a stable state and wait for the next launch operation.

[0115] Example 2: Material Delivery Operation Mode:

[0116] This embodiment corresponds to the operational scenario of precise delivery of emergency supplies at low altitudes. The specific implementation process is as follows: First, complete the mode switching and payload storage, select a boxed slide that is compatible with the box of supplies to be delivered, align the boxed slide with the upper surface positioning structure of the launch slide 6, and fasten the connecting buckle 7 to complete the tooling fixation, thus completing the configuration of the supply delivery mode.

[0117] Next, the packaged emergency medical supplies box is placed into the second support member of the support frame 8. The box is then inserted into the load sliding channel formed by the upper storage limit plate 42 and the lower storage limit plate 43. The hook 45 supports the bottom of the box, ensuring the supplies are stably stored in the storage position. Subsequently, the automatic loading process is executed. The drive servo motor 44 is rotated, causing the hook 45 to rotate downwards to release the stop. The box slides down the inclined sliding channel under its own weight and falls onto the lower limit platform 40. The rear baffle 41 blocks the tail of the box, completing the axial positioning.

[0118] Next, the third motor 35 starts, driving the second synchronous belt 38 through the third pulley 36 and the fourth pulley 37. This drives the limiting platform 40 to smoothly descend along the fourth guide rail 39 towards the launch slide 6, accurately conveying the material box to the top of the boxed slide. The material box falls into the limiting groove of the boxed slide, and the connecting buckle 7 assists in locking it to complete the loading. The limiting platform 40 descends slightly to detach from the material box and then returns to the upper receiving position. The system automatically identifies the load weight through the tension sensor. Afterward, parameter calculation and attitude energy storage are performed. The user clicks on the target point at the ground station or the vision system directly identifies the target. The industrial camera and laser rangefinder of the vision detection module simultaneously explore and collect images and distance information of the target delivery area. The main control chip combines the current wind speed and air pressure, and uses ballistic algorithms to back-calculate the required initial launch velocity and elevation angle, calculating the target azimuth, elevation angle, and target value of the energy storage tension.

[0119] Next, the steering drive motor 13 starts, and through the cooperation of the first lead screw 11 and the second bearing seat 12, it pushes the fixed frame 2 to rotate around the axis of the first bearing seat 9 to the target azimuth angle. The length of the support rod 4 is adjusted, which drives the rectangular frame 3 to rotate around its bottom hinge axis to the target elevation angle and lock it. At the same time, the first drive motor 17 starts, and pulls the launch slide 6 backward through the hook 21 on the first synchronous belt 20. The launch slide 6 is linked with the multi-stage movable pulley group through the transmission rope, so that the movable pulley slider 27 moves along the second guide rail 26 and compresses the spring group 29 to store energy. The tension sensor collects the tension value in real time, and the device automatically adjusts the position of the energy storage buckle 24 to load a specific tension value. After the target value is reached, the energy storage buckle 24 is locked into the side wing of the launch slide 6. The first drive motor 17 reverses and drives the hook 21 to reset.

[0120] Finally, the delivery and reset process is executed. The vision module continuously monitors the target area. Once the target enters the delivery window, the energy storage buckle 24 releases the lock on the launch slide 6. The spring assembly 29 releases potential energy, which, through the multi-stage movable pulley assembly consisting of the movable pulley slider 27 and the fixed pulley 28, drives the launch slide 6 to accelerate forward along the slide rail 5. After the material box reaches the initial delivery velocity, it leaves the rail and flies along a predetermined parabola, accurately landing in the air above the target area. It can achieve a soft landing with the help of the built-in parachute, completing precise delivery. For scenarios requiring precise delivery to high-rise buildings, it can be launched directly, delivering the material box to the target point with high precision. The launch slide 6 moves to the end of the slide rail 5 and impacts the buffer block 30. The buffer spring 32 absorbs the remaining kinetic energy of the slide, while the recoil elastic element between the chassis elastic band tension block 33 and the belt tension block 34 absorbs the recoil force of the entire machine. Subsequently, the device smoothly resets under the action of elastic force, waiting for the next delivery operation.

[0121] This scenario can also be used in anti-drone scenarios, where interceptor payloads are launched after automatically and accurately identifying intruding or illegal flying objects to strike the target.

[0122] The above description of the embodiments is only for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make several improvements and modifications to the present invention without departing from the principles of the present invention, and these improvements and modifications also fall within the protection scope of the claims of the present invention.

Claims

1. A drone launch and material delivery device, comprising a base (1) for contacting the ground, characterized in that: A fixed frame (2) is set on a base (1). The fixed frame (2) is connected to the base (1) through a steering component. When the steering component is working, the fixed frame (2) rotates along its rotation axis to form an adjustment area. A rectangular frame (3) is set on a fixed frame (2), and a support rod (4) is symmetrically hinged on the fixed frame (2). The bottom of the rectangular frame (3) is hinged to the end of the support rod (4) to form an adjustment of the elevation angle of the rectangular frame (3). The slide rail (5) is fixedly installed on the rectangular frame (3). The slide rail (5) is slidably connected to the launch slide (6). The launch slide (6) is provided with a connecting buckle (7) for adapting different types of launch payloads. The launch slide (6) is driven to move back and forth along the path of the slide rail (5) by the energy storage launch component on the rectangular frame (3). A support frame (8) is fixedly installed on a rectangular frame (3). A first support member is connected to the support frame (8) by a drive component to transport and dock the load to be launched to the launch slide (6). A second support member is provided on the support frame (8). The second support member forms a load storage station to support and limit the load to be launched.

2. The UAV launching and material delivery device according to claim 1, characterized in that: The steering component includes a first bearing seat (9) fixedly mounted on a base (1). The bottom of the fixing frame (2) is rotatably connected to the first bearing seat (9). A guide rail (10) is fixedly mounted on the base (1). A first lead screw (11) is provided in the guide rail (10). Both ends of the first lead screw (11) are rotatably connected to the inner wall of the guide rail (10) through bearings. A second bearing seat (12) is slidably provided in the guide rail (10). The connecting part of the second bearing seat (12) is threadedly connected to the first lead screw (11). A steering drive motor (13) is fixedly connected to the guide rail (10). The output end of the steering drive motor (13) is connected to the end of the first lead screw (11). When the steering drive motor (13) drives the first lead screw (11) to rotate, the second bearing seat (12) slides back and forth along the path of the guide rail (10) to form a moving area.

3. The UAV launching and material delivery device according to claim 2, characterized in that: A mounting platform (14) is rotatably connected to the second bearing seat (12). A sliding groove (15) is provided on the mounting platform (14). A slide bar (16) adapted to the sliding groove (15) is fixedly connected to the bottom of the fixed frame (2). The slide bar (16) is slidably disposed in the sliding groove (15). When in the moving area, the mounting platform (14) rotates adaptively around the axis of the second bearing seat (12), and the slide bar (16) slides along the sliding groove (15) to form an oscillation relative to the fixed frame (2).

4. The UAV launching and material delivery device according to claim 3, characterized in that: The energy storage launcher includes a first drive motor (17) symmetrically mounted on a rectangular frame (3). A first pulley (18) is symmetrically mounted on the rectangular frame (3), and a second pulley (19) adapted to the first pulley (18) is symmetrically mounted on the other side. A first synchronous belt (20) is symmetrically arranged on the rectangular frame (3). The two sets of first synchronous belts (20) are respectively connected to the first pulley (18) and the second pulley (19) on the corresponding side. The output ends of the two sets of first drive motors (17) are respectively connected to the corresponding first pulley (18). Hooks (21) for engaging the side wings of the launch slide (6) are fixedly mounted on both sets of first synchronous belts (20).

5. The UAV launching and material delivery device according to claim 4, characterized in that: A second lead screw (22) is provided on the longitudinal beam of the rectangular frame (3) and between the two sets of first synchronous belts (20). Both ends of the second lead screw (22) are rotatably connected to the corresponding uprights on the rectangular frame (3) through bearings. A first guide rail (23) is fixedly installed on the rectangular frame (3) and below the second lead screw (22). An energy storage buckle (24) is slidably connected on the first guide rail (23). The connection of the energy storage buckle (24) is threadedly connected to the second lead screw (22). A second drive motor (25) is fixedly connected on the rectangular frame (3). The output end of the second drive motor (25) is connected to the end of the second lead screw (22). When the second drive motor (25) drives the second lead screw (22) to rotate, the energy storage buckle (24) moves back and forth along the path of the first guide rail (23).

6. The UAV launching and material delivery device according to claim 5, characterized in that: The rectangular frame (3) is symmetrically equipped with a second guide rail (26), and each of the second guide rails (26) is slidably connected with a movable pulley slider (27) for spring mounting. The rectangular frame (3) is symmetrically equipped with a fixed pulley (28) that matches the movable pulley slider (27). The rectangular frame (3) is symmetrically equipped with a spring group (29), and the spring group (29) contains two springs. The two ends of the two springs are respectively connected to the rectangular frame (3) and the movable pulley slider (27).

7. The UAV launching and material delivery device according to claim 6, characterized in that: A buffer block (30) is slidably connected to the side of the slide rail (5) away from the second lead screw (22). A mounting bracket (31) is fixedly connected to the rectangular frame (3). Buffer springs (32) are symmetrically mounted on the mounting bracket (31). The other end of the buffer spring (32) is connected to the buffer block (30). When the launch slide (6) launches, it moves along the slide rail (5) and contacts the buffer block (30) to pull the buffer spring (32) to form the first working area. When the launch slide (6) resets, the buffer block (30) cooperates with the buffer spring (32) to reset to pull the launch. The slide (6) moves along the slide rail (5) and forms a second working area. The rectangular frame (3) is symmetrically equipped with chassis elastic band tensioning blocks (33). There are two sets of chassis elastic band tensioning blocks (33) on one side. The two sets of notches are arranged opposite each other and are used to hang the outer ends of the two sections of the braking elastic element to form a fixed installation point. The rectangular frame (3) is symmetrically equipped with belt tensioning blocks (34). The belt tensioning blocks (34) on one side are located between the two sets of chassis elastic band tensioning blocks (33) and are used to connect the inner ends of the two sections of the braking elastic element to form an inner pull connection end.

8. The UAV launching and material delivery device according to claim 7, characterized in that: The driving component includes a third motor (35) symmetrically mounted on a support frame (8). A transmission group is symmetrically mounted on the support frame (8). The transmission group includes a third pulley (36) and a fourth pulley (37). A second synchronous belt (38) is connected to the third pulley (36) and the fourth pulley (37). The output ends of the two sets of third motors (35) are connected to the corresponding third pulleys (36). The first support component includes a limiting platform (40) symmetrically sliding on the support frame (8) via a fourth guide rail (39). Both sets of limiting platforms (40) are connected to the second synchronous belt (38) via fixing buckles. A rear baffle (41) is provided on the support frame (8). The rear baffle (41) is connected to the limiting platform (40). When the third motor (35) drives the transmission group to run, the limiting platform (40) and the rear baffle (41) move along the path of the fourth guide rail (39) to form a lifting area.

9. The UAV launching and material delivery device according to claim 8, characterized in that: The second support includes a storage limiting upper plate (42) and a storage limiting lower plate (43) symmetrically installed on the support frame (8). The storage limiting upper plate (42) and the storage limiting lower plate (43) on one side are arranged parallel to each other to form a load sliding channel extending along the length of the support frame. A drive servo motor (44) is installed on the support frame (8) between the two sets of storage limiting upper plates (42) and storage limiting lower plates (43). The output end of the drive servo motor (44) is fixedly connected to a load hook (45). The load hook (45) is arranged at the outlet end of the load sliding channel and is used to rotate with the drive servo motor (44) to stop or release the load in the channel.

10. A dual-mode universal usage method for a UAV launch and material delivery device, as described in any one of claims 1-9, characterized in that: Includes the following steps: S1. Select the UAV launch mode or material delivery mode according to the mission requirements, and detachably install the corresponding load type bracket slide or box slide onto the launch slide (6) through the connecting buckle (7). S2, control the drive servo (44) of the second support to rotate, so that the mounting hook (45) releases the load to be launched in the storage position, and the load falls into the limiting platform (40) of the first support; then, the drive drives the limiting platform (40) to descend along the fourth guide rail (39), transports the load to dock with the launch slide (6), and fixes the load on the launch slide (6) through the connecting buckle (7), and at the same time obtains the weight of the load; S3, using the visual detection module integrated in the device to obtain images and distance information containing the target area, identify the target and generate target spatial coordinates; obtain the current elevation angle attitude of the rectangular frame (3); Based on the target spatial coordinates, load weight, current elevation attitude and environmental parameters, the required target azimuth, target elevation and energy storage pull target values ​​are calculated based on the ballistic model; the steering component is controlled to rotate the fixed frame (2) around the axis of the first bearing seat (9) to the target azimuth, and the support rod (4) is adjusted so that the rectangular frame (3) reaches the target elevation; at the same time, the energy storage launch component is controlled to drive the launch slide (6) to load the elastic component, and closed-loop control is performed based on real-time pull feedback until the energy storage pull target value is reached, and the side wing of the launch slide (6) is locked at the energy storage buckle (24); S4: Continuously analyze the real-time images collected by the visual detection module to determine the launch window or delivery timing that meets the preset conditions; When the optimal launch time is identified, the energy storage buckle (24) is controlled to move to release the launch slide (6). The launch slide (6) is accelerated along the slide rail (5) under the amplified force of the elastic element via the movable pulley slider (27) and the fixed pulley (28), which drives the load off the rail for launch. S5: When the launch slide (6) moves to the end of the slide rail (5), it contacts the buffer block (30). The remaining kinetic energy is absorbed by the buffer spring (32) and the braking elastic element between the chassis rubber band tension block (33) and the belt tension block (34), so as to realize the smooth reset of the launch device.

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