A rudder mounting mechanism for a cargo fixed-wing unmanned aerial vehicle

Abstract

The application provides a rudder installation mechanism for a cargo fixed-wing unmanned plane, and relates to the technical field of fixed-wing unmanned planes. The rudder installation mechanism for the cargo fixed-wing unmanned plane comprises a fixed wing, an installation port arranged on the lower wall of the fixed wing, a step arranged on the lower edge of the installation port, a shell, a control box internally provided with a mainboard and a power supply package, a rudder body and a rocker arm arranged on the outer wall of the output shaft of the rudder body. The rudder body is fixed through a screw, the connection mode is stable, the shell does not need to be disassembled when the rudder body is disassembled, the inner shell with the installed rudder body is pushed upwards into the installation cavity, the double-shaft motor is rotated to drive the lock pin to form position locking, when disassembly is needed, the double-shaft motor is reversed to drive the lock pin to retreat to the inside of the inner shell, and the purpose of quick installation and disassembly is achieved. The installation position of the inner shell in the installation cavity and the position of the lock pin are respectively confirmed through a first proximity switch and a second proximity switch.

Description

Technical Field

[0001] This invention relates to the field of fixed-wing unmanned aerial vehicle (UAV) technology, specifically to a servo mounting mechanism for a cargo fixed-wing UAV. Background Technology

[0002] Fixed-wing unmanned aerial vehicles (UAVs) are a type of UAV with fixed wings whose wing sweep angle can be automatically or manually adjusted according to speed. Due to their excellent functionality and modular integration, they are now widely used in surveying, geology, petroleum, agriculture, forestry, and other professions, and have broad market prospects. A typical fixed-wing UAV system consists of five main parts: airframe structure, avionics system, power system, takeoff and landing system, and ground control station. Currently, the drive motors for the wing control surfaces of fixed-wing UAVs are generally installed inside the main wing surface, and are installed, inspected, and maintained through a mounting port. For large cargo fixed-wing UAVs with a high-wing configuration, due to the high stopping height, removing the mounting port requires detaching the servos from the mounting bracket through a narrow mounting opening, making disassembly and assembly extremely inconvenient. Therefore, existing technologies suffer from the problem of extremely inconvenient servo motor assembly and disassembly. To address this, a publicly available technology proposes a quick-release device and method for servo motors on cargo drones. This includes a wing-mounted stop frame with a cover on it, the cover being connected to the bottom surface of the frame via screws. A servo motor mounting bracket is also provided above the cover. The bracket includes two symmetrically fixed support columns on the upper surface of the cover, with a rotating shaft between the two columns. A servo motor mounting base plate is mounted on the rotating shaft. A hydraulic cylinder is located at one end of the upper surface of the cover, with a push rod hinged to its output end. The upper end of the push rod is hinged to the bottom end of the servo motor mounting base plate. The quick-release method involves mounting the servo motor on the servo motor mounting bracket and connecting it to the control surface mechanism via a plug-in connection. By vertically disassembling the cover, the servo motor is separated from the control surface mechanism, completing the disassembly of the servo motor. This allows for rapid disassembly and lowering of the servo motor simultaneously with the cover removal.

[0003] However, as can be seen from the technical content disclosed above, the servo motor is only fixed by two support columns and a servo motor mounting base plate that rotates between the two support columns via a rotating shaft. The fixing method is not stable enough and there is a problem of shaking during use. In addition, the cover and the fixed stop frame still need to be fixed with multiple sets of screws. After removing multiple screws, the cover can be dragged down to remove the servo motor, which does not achieve the claimed function of quick disassembly. Therefore, it is necessary to optimize and improve the servo motor mounting mechanism of this type of large cargo fixed-wing UAV. Summary of the Invention

[0004] (a) Technical problems to be solved

[0005] To address the shortcomings of existing technologies, this invention provides a servo mounting mechanism for cargo fixed-wing UAVs, which solves the problems of unstable servo mounting and lack of quick-release function in existing technologies for large fixed-wing UAVs.

[0006] (II) Technical Solution

[0007] To achieve the above objectives, the present invention provides the following technical solution: a servo mounting mechanism for a cargo fixed-wing UAV, comprising a fixed wing, a mounting port on the lower wall of the fixed wing, a step on the lower edge of the mounting port, a housing, a control box containing a main board and a power supply pack, a servo body, and a rocker arm on the outer wall of the output shaft of the servo body. The upper inner wall of the step has multiple sets of positioning holes. The outer wall of the housing has a flange edge that matches the shape of the inner cavity of the step. The upper wall of the flange edge has a first positioning structure that cooperates with the positioning holes. The housing has a mounting cavity that communicates with the lower wall of the housing. An inner shell is slidably connected to the inner wall of the mounting cavity. A confirmation mechanism is provided between the inner shell and the upper inner wall of the housing. The inner shell is installed in place by a position confirmation structure. The inner left and right walls of the inner shell are slidably connected to four sets of push plates via eight sets of first guide pillars. The four sets of push plates are arranged in pairs, close to the inner front wall and inner rear wall of the inner shell respectively. A locking structure is provided between the push plates and the outer shell to lock the position of the inner shell and the outer shell. A drive structure is provided on the inner wall of the inner shell to drive the locking structure. A limit switch is also provided between the inner wall of the inner shell and the push plates to control the travel of the drive structure. The servo motor body is fixedly connected to the lower inner wall of the inner shell. A second positioning structure is provided between the servo motor body and the lower inner wall of the inner shell for positioning the servo motor body during installation. The control box is located on the lower inner wall of the inner shell and on the left side of the servo motor body.

[0008] Preferably, the upper wall of the housing is provided with a clearance groove that runs vertically through the housing, and the end of the rocker arm away from the servo motor body passes through the clearance groove and extends to the top of the housing.

[0009] Preferably, one of the four corners of the mounting cavity inside the outer shell is provided with a positioning arc when viewed from above, and the shape of the outer wall of the inner shell when viewed from above matches the shape of the inside of the mounting cavity.

[0010] Preferably, the first positioning structure includes four sets of positioning posts, all of which are fixedly connected to the upper wall of the flange and are respectively aligned with multiple sets of positioning holes in the step. The inner sidewall of each positioning post is provided with a countersunk hole that runs vertically through it, and a screw is provided in the countersunk hole. The outer shell is fixedly connected to the mounting port of the fixed wing by the screw.

[0011] Preferably, the position confirmation structure includes four sets of support plates, a first sensing block, and four sets of first proximity switches. The four sets of support plates are fixedly connected in pairs to the inner front wall and inner rear wall of the inner shell, respectively. Two sets of support plates on the same side are close to the left and right side walls of the inner shell, respectively. The four sets of first proximity switches are fixedly connected to the upper side of the four sets of support plates, and the four sets of first sensing blocks are fixedly connected to the upper side of the inner mounting cavity of the outer shell and are respectively vertically opposite to the four sets of first proximity switches.

[0012] Preferably, the locking structure includes four sets of reinforcing plates and eight sets of locking pins. The four sets of reinforcing plates are fixedly connected in pairs to the left and right walls of the outer shell, and the eight sets of locking pins are fixedly connected in pairs to the opposite sides of the four sets of push plates. The end of the locking pin away from the push plate passes through the inner shell side wall, the outer shell side wall, and the inner wall of the reinforcing plate in sequence. The inner shell and the outer shell are locked together by the locking pin passing through the inner shell side wall, the outer shell side wall, and the inner wall of the reinforcing plate. The end of the locking pin away from the push plate is provided with an arc head.

[0013] Preferably, the drive structure includes two sets of dual-axis motors, four sets of screws, and four sets of threaded tubes. The two sets of dual-axis motors are respectively fixedly connected to the inner front wall and inner rear wall of the inner shell. The four sets of screws are respectively fixedly connected to the protruding shaft ends of the two sets of dual-axis motors. The four sets of threaded tubes are respectively threadedly connected to the ends of the four sets of screws away from the dual-axis motors. The ends of the four sets of threaded tubes away from the four sets of screws are respectively fixedly connected to the left and right opposite sides of the four sets of push plates. The screws located at both ends of the same set of dual-axis motors have opposite thread directions.

[0014] Preferably, the limit switch includes two sets of side baffles, a second sensing block, and two sets of second proximity switches. The two sets of side baffles are fixedly connected to the inner side wall of the inner shell and are respectively located on the left and right sides of the push plate. The two sets of second proximity switches are respectively fixedly connected to the left and right sides of the push plate and are close to the upper end of the push plate. The two sets of second sensing blocks are respectively fixedly connected between the opposite sides of the two sets of side baffles and are respectively opposite to the left and right sides of the two sets of second proximity switches.

[0015] Preferably, the second positioning structure includes a left positioning plate and a right positioning plate. The left positioning plate is fixedly connected to the lower inner wall of the inner shell. The right positioning plate is slidably connected to the right inner wall of the inner shell through two sets of second guide posts, and the right positioning plate is opposite to the left positioning plate. The servo body is disposed between the left and right positioning plates. A spring is sleeved on the outer wall of the second guide post between the right positioning plate and the right inner wall of the inner shell. An inclined surface is provided at the connection between the upper wall of the right positioning plate and the side of the right positioning plate facing the left positioning plate. The inclined surface and the side of the right positioning plate facing the left positioning plate are transitioned by a guide arc.

[0016] Preferably, the control box extends through the lower wall of the inner shell and is flush with the lower wall of the inner shell. The lower wall of the control box is provided with a display screen and a charging port arranged in a front-to-back pattern.

[0017] (III) Beneficial Effects

[0018] This invention provides a servo mounting mechanism for a cargo fixed-wing unmanned aerial vehicle (UAV). It offers the following advantages:

[0019] 1. Compared with existing technologies, the servo mounting mechanism for cargo fixed-wing UAVs has a servo body that is positioned by the left and right positioning plates and then falls onto the inner side wall of the inner shell. The servo body is then fixed with screws. After installation, there is no risk of shaking, and the connection method is stable.

[0020] 2. Compared with existing technologies, the servo mounting mechanism for cargo fixed-wing UAVs pre-positions the outer shell with the fixed-wing mounting port using positioning pins and then secures it with screws. When disassembling the servo unit, it is not necessary to remove the outer shell. The inner shell with the servo unit installed is pushed upwards into the mounting cavity of the outer shell. Once in place, two sets of dual-axis motors are activated to rotate, driving eight sets of locking pins through the inner shell, outer shell, and reinforcing plate, thus locking the position. When disassembly is required, simply support the lower wall of the inner shell and reverse the two sets of dual-axis motors, causing the eight sets of locking pins to retract into the inner shell. The inner shell can then be removed from the mounting cavity of the outer shell by its own weight, achieving rapid installation and disassembly. Furthermore, the installed mechanism is very stable and highly safe.

[0021] 3. Compared with existing technologies, the servo mounting mechanism for cargo fixed-wing UAVs uses a first proximity switch and a second proximity switch to confirm the installation position of the inner shell inside the mounting cavity and the position of the locking pin, respectively, which greatly improves the accuracy of the installation process. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0023] Figure 2 This is a partial cross-sectional view of the internal structure connecting the outer shell and inner shell of the present invention.

[0024] Figure 3 For the present invention Figure 2 A magnified view of a section at point A in the middle;

[0025] Figure 4 For the present invention Figure 2 A magnified view of a section at point B in the middle;

[0026] Figure 5 This is a schematic diagram of the connection structure of the dual-axis motor, screw, push plate, locking pin, and second proximity switch of the present invention;

[0027] Figure 6This is a schematic diagram of the control box structure from the top surface of the present invention;

[0028] Figure 7 This is a top-view schematic diagram of the internal structure of the outer shell of the present invention.

[0029] The components are as follows: 1. Outer shell; 2. Servo body; 3. Rocker arm; 4. Flange edge; 5. Positioning post; 6. Countersunk hole; 7. Reinforcing plate; 8. Locking pin; 9. Arc head; 10. Clearance groove; 11. Control box; 12. Threaded tube; 13. Left positioning plate; 14. Positioning arc; 15. Inner shell; 16. Bracket plate; 17. Side baffle; 18. First sensing block; 19. First proximity switch; 20. Push plate; 21. First guide post; 22. Second sensing block; 23. Second proximity switch; 24. Right positioning plate; 25. Inclined surface; 26. Guide arc; 27. Second guide post; 28. Spring; 29. ​​Dual-axis motor; 30. Screw; 31. Display screen; 32. Charging port. Detailed Implementation

[0030] 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.

[0031] Example:

[0032] like Figures 1 to 7 As shown, this embodiment of the invention provides a servo mounting mechanism for a cargo fixed-wing UAV, including a fixed wing, a mounting port on the lower wall of the fixed wing, a step on the lower edge of the mounting port, a housing 1, a control box 11 containing a motherboard and a power supply pack, a servo body 2, and a rocker arm 3 on the outer wall of the output shaft of the servo body 2. The upper wall of the housing 1 is provided with a vertically penetrating clearance groove 10. The end of the rocker arm 3 away from the servo body 2 passes through the clearance groove 10 and extends to the top of the housing 1. The servo body 2, rocker arm 3, and the driving method of the rocker arm 3 provided in this embodiment are consistent with the existing disclosed technology. This embodiment only optimizes and improves the mounting mechanism of the servo body 2 to achieve the purpose of stable installation and quick disassembly and reassembly.

[0033] like Figure 1As shown, to facilitate the installation of the outer shell 1, multiple sets of positioning holes are provided on the upper inner wall of the step. The outer wall of the outer shell 1 is provided with a flange edge 4 that matches the shape of the inner cavity of the step. The upper wall of the flange edge 4 is provided with a first positioning structure that works with the positioning holes. The first positioning structure includes four sets of positioning pins 5. The four sets of positioning pins 5 are all fixedly connected to the upper wall of the flange edge 4 and are respectively aligned with the multiple sets of positioning holes in the step. The inner wall of the positioning pin 5 is provided with a countersunk hole 6 that runs vertically through the steps. Screws are provided in the countersunk hole 6. The outer shell 1 is fixedly connected to the mounting port of the fixed wing by screws. The outer shell 1 is pre-installed with the mounting port on the fixed wing and will not be removed after installation. When the servo body 2 needs to be removed, only the inner shell 15 needs to be removed. The outer shell 1 is pushed into the mounting port from bottom to top, and positioned by aligning the multiple sets of positioning pins 5 with the multiple sets of positioning holes. Then, screws are inserted upward through the countersunk hole 6 to fix the outer shell 1 to the fixed wing.

[0034] like Figure 7 As shown, in order to prevent the inner shell 15 from being installed in the outer shell 1 in the wrong direction, the outer shell 1 has an installation cavity that is connected to the lower wall of the outer shell 1. The inner shell 15 is slidably connected to the inner side wall of the installation cavity. In the top view projection of the installation cavity inside the outer shell 1, one of the four corners is provided with a positioning arc 14. The shape of the outer wall of the inner shell 15 in the top view projection matches the shape of the inner cavity. By setting a positioning arc 14, the inner shell 15 is oriented in a unique direction when installed in the installation cavity. If the left and right directions are wrong, it cannot be installed. From the physical structure, it plays a role in preventing assembly errors.

[0035] like Figure 2 , Figure 3 To confirm whether the inner shell 15 is installed correctly, a position confirmation structure is provided between the inner shell 15 and the inner upper wall of the outer shell 1. The position confirmation structure includes four sets of support plates 16, first sensing blocks 18, and four sets of first proximity switches 19. The four sets of support plates 16 are fixedly connected in pairs to the inner front wall and inner rear wall of the inner shell 15. The two sets of support plates 16 on the same side are close to the left and right side walls of the inner shell 15. The four sets of first proximity switches 19 are fixedly connected to the upper walls of the four sets of support plates 16. The four sets of first sensing blocks 18 are all fixedly connected to the inner upper wall of the mounting cavity of the outer shell 1 and are respectively connected to the four sets of support plates 16. If the inner shell 15 is not properly installed, the locking pin 8 will not be able to pass smoothly through the inner shell 15, the outer shell 1, and the inner wall of the reinforcing plate 7, thus failing to lock and causing the threaded tube 12 and screw 30 to strip, or even damage the dual-axis motor 29. To avoid this situation, the inner shell 15 is pushed into the mounting cavity with the inner shell facing upward until the first proximity switch 19 contacts the first sensing block 18, at which point it is considered properly installed. The first proximity switch 19 generates a signal to the control box 11 by contacting the first sensing block 18, which is then displayed on the display screen 31. Only then can the control box 11 control the action of the dual-axis motor 29, greatly improving the safety of the device.

[0036] like Figure 1 , Figure 2 , Figure 3 as well as Figure 5 As shown, to enable quick-release assembly between the inner shell 15 and the outer shell 1, four sets of push plates 20 are slidably connected to the inner left and inner right walls of the inner shell 15 via eight sets of first guide posts 21. The four sets of push plates 20 are arranged in pairs, respectively close to the inner front and inner rear walls of the inner shell 15. A locking structure is provided between the push plates 20 and the outer shell 1 to lock the positions of the inner shell 15 and the outer shell 1. The locking structure includes four sets of reinforcing plates 7 and eight sets of locking pins 8. The four sets of reinforcing plates 7 are fixedly connected in pairs to the left and right walls of the outer shell 1, respectively. The eight sets of locking pins 8 are fixedly connected in pairs to the opposite sides of the four sets of push plates 20. The end of the locking pin 8 away from the push plate 20 passes through the side wall of the inner shell 15, the side wall of the outer shell 1, and the inner wall of the reinforcing plate 7 in sequence. The inner shell 15 and the outer shell 1 are locked together by a locking pin 8 that passes through the side wall of the inner shell 15, the side wall of the outer shell 1, and the inner wall of the reinforcing plate 7. The end of the locking pin 8 away from the push plate 20 is provided with an arc head 9. The push plate 20 is driven by the drive structure to move closer to or away from the inner side wall of the inner shell 15. When the inner shell 15 is installed in place, the drive structure drives the push plate 20 to move closer to the inner side wall of the inner shell 15 so that the locking pin 8 passes through the inner shell 15, the outer shell 1, and the inner wall of the reinforcing plate 7. The eight sets of locking pins 8 lock the vertical position between the inner shell 15 and the outer shell 1. When the inner shell 15 needs to be removed, the drive structure drives the push plate 20 to move in the opposite direction, and the locking pin 8 returns to the inside of the inner shell 15, thus releasing the locking state, thereby achieving the purpose of quick disassembly and quick assembly.

[0037] like Figure 2 , Figure 3 as well as Figure 5 As shown, in order to drive the locking mechanism, the inner wall of the inner shell 15 is provided with a drive structure for driving the locking mechanism. The drive structure includes two sets of dual-axis motors 29, four sets of screws 30, and four sets of threaded tubes 12. The two sets of dual-axis motors 29 are respectively fixedly connected to the front wall and the rear wall of the inner shell 15. The four sets of screws 30 are respectively fixedly connected to the protruding shaft ends of the two sets of dual-axis motors 29. The four sets of threaded tubes 12 are respectively threaded to the ends of the four sets of screws 30 away from the dual-axis motors 29. The ends of the four sets of threaded tubes 12 away from the four sets of screws 30 are respectively opposite to the four sets of push plates 20 on the left and right sides. The four sets of screws 30 are fixedly connected. The two sets of screws 30 located at both ends of the same set of dual-axis motors 29 have opposite thread directions. After the inner shell 15 is installed in place, the control box 11 controls the dual-axis motors 29 to start. The screws 30 located at both ends of the dual-axis motors 29 rotate in the same direction. Since the two sets of screws 30 have opposite thread directions, when the two sets of screws 30 rotate, they drive the threaded tubes 12 that are matched with them to move closer or further away from each other. When the two sets of threaded tubes 12 move in opposite or opposite directions, they drive the push plate 20 to move, so as to realize the locking state and unlocking state of the locking structure.

[0038] like Figure 2 , Figure 3 As shown, in order to control the moving distance of the locking pin 8, a limit switch for controlling the movement stroke of the drive structure is also provided between the inner wall of the inner shell 15 and the push plate 20. The limit switch includes two sets of side baffles 17, a second sensing block 22 and two sets of second proximity switches 23. The two sets of side baffles 17 are fixedly connected to the inner wall of the inner shell 15 and are located on the left and right sides of the push plate 20 respectively. The two sets of second proximity switches 23 are fixedly connected to the left and right sides of the push plate 20 respectively and are close to the upper end of the push plate 20. Two sets of second sensing blocks 22 are fixedly connected between opposite sides of two sets of side baffles 17 and are respectively opposite to two sets of second proximity switches 23. When the dual-axis motor 29 rotates and drives the two sets of push plates 20 to move in opposite directions, the movement stroke is controlled by the two sets of second proximity switches 23 located on the push plate 20 in conjunction with the two sets of second sensing blocks 22 to avoid excessive movement range causing impact. At the same time, by reasonably setting the distance between the two sets of second sensing blocks 22, the travel of the locking pin 8 can be adjusted to the most reasonable range, which not only meets the locking requirements, but also releases the locking state in the shortest time, further improving the effect of quick disassembly and quick assembly.

[0039] like Figure 2 , Figure 4 As shown, to facilitate left and right positioning during installation of the servo motor body 2 and the inner shell 15, the servo motor body 2 is fixedly connected to the lower inner wall of the inner shell 15. A second positioning structure for positioning the servo motor body 2 during installation is provided between the servo motor body 2 and the lower inner wall of the inner shell 15. The second positioning structure includes a left positioning plate 13 and a right positioning plate 24. The left positioning plate 13 is fixedly connected to the lower inner wall of the inner shell 15. The right positioning plate 24 is slidably connected to the right inner wall of the inner shell 15 via two sets of second guide posts 27, and the right positioning plate 24 is laterally opposite to the left positioning plate 13. The servo motor body 2 is positioned between the left positioning plate 13 and the right positioning plate 24. A spring 2 is sleeved on the outer wall of the second guide posts 27 and located between the right positioning plate 24 and the right inner wall of the inner shell 15. 8. An inclined surface 25 is provided at the connection between the upper wall of the right positioning plate 24 and the side of the right positioning plate 24 facing the left positioning plate 13. The inclined surface 25 and the side of the right positioning plate 24 facing the left positioning plate 13 are connected by a guide arc 26. When the servo body 2 is installed facing the lower inner wall of the inner shell 15, the left wall of the servo body 2 is first overlapped with the right wall of the left positioning plate 13, and then the servo body 2 is pressed down until the lower wall of the servo body 2 abuts against the lower inner wall of the inner shell 15. At this time, the servo body 2 will be pressed against the right wall of the left positioning plate 13 by the compression of the spring 28, thereby realizing the positioning of the left and right positions. After the positioning is completed, the servo body 2 and the inner shell 15 are locked with screws to improve the installation firmness and prevent shaking during use.

[0040] like Figure 2 , Figure 6In order to independently control the mounting mechanism, the control box 11 is located on the lower inner wall of the inner shell 15 and on the left side of the servo body 2. The control box 11 penetrates the lower wall of the inner shell 15 and the lower wall of the control box 11 is flush with the lower wall of the inner shell 15. The lower wall of the control box 11 is arranged with a display screen 31 and a charging port 32 in a front-to-back arrangement. The control box 11 is powered by an independent battery pack and is used to control the action of the dual-axis motor 29. When the battery pack is depleted, an external power source can also be connected through the charging port 32 to control the dual-axis motor 29. The display screen 31 is used to display power information, limit switch signals and position confirmation structure signals.

[0041] Working principle: The outer shell 1 is pre-installed with the mounting port on the fixed wing and is not removed after installation. When the servo body 2 needs to be removed, only the inner shell 15 needs to be removed. The outer shell 1 is pushed into the mounting port from bottom to top. After being positioned by aligning multiple sets of positioning pins 5 with multiple sets of positioning holes, the screw is then inserted upward through the countersunk hole 6 to fix the outer shell 1 to the fixed wing. By setting a positioning arc 14, the inner shell 15 is installed in a direction that is unique when facing the mounting cavity. If the left and right directions are reversed, it cannot be installed. This serves as an assembly error prevention function from a physical structure perspective. If the inner shell 15 is not installed in place, the locking pin 8 will not be able to pass smoothly through the inner shell 15, the outer shell 1, and the inner wall of the reinforcing plate 7, thus failing to achieve the locking function and causing the threaded tube 12 and the screw 30 to strip. This could even damage the dual-axis motor 29. To avoid this, the inner shell 15 is pushed upwards into the mounting cavity until the first proximity switch 19 contacts the first sensing block 18. Only then is the installation complete. The first proximity switch 19 generates a signal to the control box 11 by contacting the first sensing block 18, which is then displayed on the display screen 31. Only then can the control box 11 control the dual-axis motor 29, greatly improving the safety of the device. The push plate 20 is driven by the drive structure to move closer to or away from the inner wall of the inner shell 15. After the inner shell 15 is installed in place, the drive structure drives the push plate 20 to move closer to the inner wall of the inner shell 15, so that the locking pin 8 penetrates the inner shell 15, the outer shell 1, and the inner wall of the reinforcing plate 7. The eight sets of locking pins 8 lock the vertical position between the inner shell 15 and the outer shell 1. When the inner shell 15 needs to be removed, the drive structure drives the push plate 20 to move in the opposite direction, and the locking pin 8 retracts into the inner shell 15, thus releasing the locking state and achieving quick disassembly and assembly. After the inner shell 15 is installed in place, the control box 11 controls the dual-axis motor 29 to start. The screws 30 at the ends of the shafts of the dual-axis motor 29 rotate in the same direction. Since the threads of the two sets of screws 30 are opposite, the rotation of the two sets of screws 30 causes the threaded tubes 12 that they are engaged with to move closer or further apart. When the two sets of threaded tubes 12 move in opposite or opposite directions, they drive the push plate 20 to move, thereby achieving the locking and unlocking states of the locking structure. When the dual-axis motor 29 rotates and drives the two sets of push plates 20 to move in opposite or opposite directions... The movement stroke is controlled by two sets of second proximity switches 23 located on the push plate 20, in conjunction with two sets of second sensing blocks 22, to avoid excessive movement and potential impact. Simultaneously, by appropriately setting the distance between the two sets of second sensing blocks 22, the travel of the locking pin 8 can be adjusted to the optimal range, satisfying the locking requirements while simultaneously releasing the lock in the shortest possible time, further improving the quick-release and quick-installation effect. When the servo motor body 2 is installed facing the lower inner wall of the inner shell 15, first overlap the left wall of the servo motor body 2 with the right wall of the left positioning plate 13, then press the servo motor body 2 downwards until the lower wall of the servo motor body 2 abuts against the lower inner wall of the inner shell 15. At this point, due to the compression of the spring 28, the servo motor body 2 will press firmly against the right wall of the left positioning plate 13, thereby achieving left and right positioning. After positioning is completed...The servo motor body 2 is then secured to the inner housing 15 with screws to improve installation stability and prevent shaking during use. The control box 11 is powered by an independent battery pack and is used to control the dual-axis motor 29. When the battery pack is depleted, an external power source can be connected via the charging port 32 to control the dual-axis motor 29. The display screen 31 displays power information, limit switch signals, and position confirmation signals.

[0042] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A servo mounting mechanism for a cargo fixed-wing unmanned aerial vehicle, characterized in that: The system includes a fixed wing, a mounting port on the lower wall of the fixed wing, a step on the lower edge of the mounting port, a housing (1), a control box (11) containing a main board and a power supply pack, a servo motor body (2), and a rocker arm (3) on the outer wall of the output shaft of the servo motor body (2). The upper inner wall of the step has multiple sets of positioning holes. The outer wall of the housing (1) has a flange edge (4) that matches the shape of the inner cavity of the step. The upper wall of the flange edge (4) has a first positioning structure that works with the positioning holes. The housing (1) has a mounting cavity that communicates with the lower wall of the housing (1). The inner wall of the mounting cavity is slidably connected to an inner shell (15). A position confirmation structure for confirming whether the inner shell (15) is installed in place is provided between the inner shell (15) and the upper inner wall of the housing (1). The left inner wall and the right inner wall of the inner shell (15) are connected by eight The first guide post (21) is slidably connected to four sets of push plates (20). The four sets of push plates (20) are in pairs and are close to the inner front wall and inner rear wall of the inner shell (15). A locking structure for locking the position of the inner shell (15) and the outer shell (1) is provided between the push plate (20) and the outer shell (1). A driving structure for driving the locking structure is provided on the inner wall of the inner shell (15). A limit switch for controlling the driving structure's stroke is also provided between the inner wall of the inner shell (15) and the push plate (20). The servo motor body (2) is fixedly connected to the lower inner wall of the inner shell (15). A second positioning structure for positioning the servo motor body (2) during installation is provided between the servo motor body (2) and the lower inner wall of the inner shell (15). The control box (11) is located on the lower inner wall of the inner shell (15) and is located on the left side of the servo motor body (2).

2. The servo mounting mechanism for a cargo fixed-wing UAV according to claim 1, characterized in that: The upper wall of the outer casing (1) is provided with a clearance groove (10) that runs vertically through the casing. The end of the rocker arm (3) away from the servo motor body (2) passes through the clearance groove (10) and extends to the top of the outer casing (1).

3. The servo mounting mechanism for a cargo fixed-wing UAV according to claim 2, characterized in that: The mounting cavity inside the outer shell (1) has a positioning arc (14) at one of its four corners when viewed from above. The outer shape of the outer wall of the inner shell (15) when viewed from above matches the shape inside the mounting cavity.

4. The servo mounting mechanism for a cargo fixed-wing UAV according to claim 3, characterized in that: The first positioning structure includes four sets of positioning posts (5). The four sets of positioning posts (5) are fixedly connected to the upper wall of the flange edge (4) and are respectively aligned with multiple sets of positioning holes in the step. The inner side wall of the positioning post (5) is provided with a countersunk hole (6) that runs vertically through the bottom. A screw is provided in the countersunk hole (6). The outer shell (1) is fixedly connected to the fixed wing mounting port by the screw.

5. A servo mounting mechanism for a cargo fixed-wing UAV according to claim 4, characterized in that: The position confirmation structure includes four sets of support plates (16), a first sensing block (18), and four sets of first proximity switches (19). The four sets of support plates (16) are fixedly connected in pairs to the inner front wall and inner rear wall of the inner shell (15). The two sets of support plates (16) on the same side are close to the left and right side walls of the inner shell (15). The four sets of first proximity switches (19) are fixedly connected to the upper wall of the four sets of support plates (16). The four sets of first sensing blocks (18) are all fixedly connected to the upper wall of the mounting cavity of the outer shell (1) and are respectively vertically opposite to the four sets of first proximity switches (19).

6. A servo mounting mechanism for a cargo fixed-wing UAV according to claim 5, characterized in that: The locking structure includes four sets of reinforcing plates (7) and eight sets of locking pins (8). The four sets of reinforcing plates (7) are fixedly connected in pairs to the left and right walls of the outer shell (1). The eight sets of locking pins (8) are fixedly connected in pairs to the opposite sides of the four sets of push plates (20). The end of the locking pin (8) away from the push plate (20) passes through the side wall of the inner shell (15), the side wall of the outer shell (1), and the inner wall of the reinforcing plate (7) in sequence. The inner shell (15) and the outer shell (1) are locked together by the locking pin (8) passing through the side wall of the inner shell (15), the side wall of the outer shell (1), and the inner wall of the reinforcing plate (7). The end of the locking pin (8) away from the push plate (20) is provided with an arc head (9).

7. A servo mounting mechanism for a cargo fixed-wing UAV according to claim 6, characterized in that: The drive structure includes two sets of dual-axis motors (29), four sets of screws (30), and four sets of threaded tubes (12). The two sets of dual-axis motors (29) are fixedly connected to the inner front wall and inner rear wall of the inner shell (15), respectively. The four sets of screws (30) are fixedly connected to the protruding shaft ends of the two sets of dual-axis motors (29), respectively. The four sets of threaded tubes (12) are threadedly connected to the ends of the four sets of screws (30) away from the dual-axis motors (29), respectively. The ends of the four sets of threaded tubes (12) away from the four sets of screws (30) are fixedly connected to the left and right opposite sides of the four sets of push plates (20), respectively. The two sets of screws (30) located at both ends of the same set of dual-axis motors (29) have opposite thread directions.

8. A servo mounting mechanism for a cargo fixed-wing UAV according to claim 7, characterized in that: The limit switch includes two sets of side baffles (17), a second sensing block (22), and two sets of second proximity switches (23). The two sets of side baffles (17) are fixedly connected to the inner side wall of the inner shell (15) and are respectively located on the left and right sides of the push plate (20). The two sets of second proximity switches (23) are respectively fixedly connected to the left and right sides of the push plate (20) and are close to the upper end of the push plate (20). The two sets of second sensing blocks (22) are respectively fixedly connected between the opposite sides of the two sets of side baffles (17) and are respectively opposite to the left and right sides of the two sets of second proximity switches (23).

9. A servo mounting mechanism for a cargo fixed-wing UAV according to claim 8, characterized in that: The second positioning structure includes a left positioning plate (13) and a right positioning plate (24). The left positioning plate (13) is fixedly connected to the lower inner wall of the inner shell (15). The right positioning plate (24) is slidably connected to the right inner wall of the inner shell (15) through two sets of second guide posts (27), and the right positioning plate (24) and the left positioning plate (13) are opposite to each other. The servo body (2) is set between the left positioning plate (13) and the right positioning plate (24). A spring (28) is sleeved on the outer wall of the second guide post (27) between the right positioning plate (24) and the right inner wall of the inner shell (15). An inclined surface (25) is provided at the connection between the upper wall of the right positioning plate (24) and the side of the right positioning plate (24) facing the left positioning plate (13). The inclined surface (25) and the side of the right positioning plate (24) facing the left positioning plate (13) are connected by a guide arc (26).

10. A servo mounting mechanism for a cargo fixed-wing UAV according to claim 9, characterized in that: The control box (11) penetrates the lower wall of the inner shell (15) and the lower wall of the control box (11) is flush with the lower wall of the inner shell (15). The lower wall of the control box (11) is provided with a display screen (31) and a charging port (32) arranged in a front-to-back pattern.

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