Self-stabilized wind-resistant vertical take-off fixed-wing unmanned aerial vehicle

Abstract

This invention discloses a self-stabilizing, wind-resistant VTOL fixed-wing UAV, belonging to the field of UAVs. The self-stabilizing, wind-resistant VTOL fixed-wing UAV includes a connector. A motor is fixedly connected to the top of the connector, and a rotating ring is fixedly connected to the top of the motor. A rotor blade is fixedly connected to the outer side of the rotating ring. A through groove is formed on the outer side of the rotating ring, and a cover plate is provided on the top of the rotating ring. An extension block is fixedly connected to the side of the cover plate near the through groove. A retaining plate is fixedly connected to the inner wall of the through groove, and a slot is formed on the inner side of the extension block. The retaining plate is located inside the slot. The rotating ring and the cover plate are snapped together by the retaining plate and the through groove. The rotating ring and the cover plate form a snap-fit ​​quick-release structure through the through groove, the retaining plate, the cylinder, and the round hole and slot of the extension block, achieving convenient assembly and disassembly with a stable connection. This effectively improves the efficiency of rotor blade assembly and disassembly and the ease of maintenance. Simultaneously, the tight snap-fit ​​ensures the dynamic balance of rotor rotation, enhancing the operational stability and wind resistance reliability of the UAV.

Description

Technical Field

[0001] This invention relates to a self-stabilizing, wind-resistant vertical take-off fixed-wing unmanned aerial vehicle (UAV) and pertains to the field of UAVs. Background Technology

[0002] Vertical takeoff and landing (VTOL) fixed-wing aircraft, similar in function to helicopters, can take off and land vertically without a runway. However, unlike helicopters, these aircraft can accelerate from a hovering position using powered tilting to transition into fixed-wing flight mode. VTOL fixed-wing UAVs combine the convenience of multi-rotor VTOL with the long endurance and high-speed cruising advantages of fixed-wing aircraft, and are widely used in inspection, surveying, security, logistics, and emergency rescue scenarios.

[0003] In the prior art, such as the vertical take-off and landing fixed-wing UAV with patent number CN105905294B, a combination of forward drive and fuselage rotor and wing rotor is used to facilitate the switching between vertical take-off and landing and fixed-wing flight. However, existing vertical take-off and landing fixed-wing UAVs cannot adaptively adjust to changes in the overall center of gravity. During load increases or decreases, battery consumption, and transitions between vertical take-off and landing and fixed-wing modes, the rotor's total lift center is prone to shifting from the overall center of gravity, leading to loss of pitch control, flight shaking, and decreased stability. Especially in complex wind environments such as strong winds and gusts, their anti-interference capabilities are insufficient, making it difficult to maintain stable flight. Furthermore, the rotor is prone to loosening and detachment after long-term use, affecting rotor dynamic balance and flight safety. In addition, the rotor lacks a complete protective structure, making it susceptible to collision damage during take-off, landing, and low-altitude flight. Exposed rotors are also significantly affected by crosswind disturbances, further reducing flight stability. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention discloses a self-stabilizing, wind-resistant vertical takeoff and landing (VTOL) fixed-wing UAV, comprising a main body and two fixed wings fixedly installed on the left and right sides of the main body. A tail fin is fixedly connected to the rear end of the main body. The main body, fixed wings, and tail fin constitute the basic aerodynamic and load-bearing structure. The rotor assembly is adjusted in the longitudinal direction of the fixed wings through an intermediate component. In conjunction with the tilt drive, blade rotation, quick-release assembly, and ring-shaped protective structure of the rotor assembly, the UAV sequentially completes vertical takeoff and landing, mode conversion, fixed-wing cruise, and full-process self-stabilizing and wind-resistant operation. The intermediate component is fixedly connected to the bottom of the fixed wings, and a groove is provided on the bottom of the fixed wings near the intermediate component. The rotor assembly is fixedly mounted on the bottom of the intermediate assembly; The rotor assembly includes a connector, which is fixedly connected to the intermediate assembly. A motor is fixedly connected to the top of the connector, and a rotating ring is fixedly connected to the top of the motor. Two rotating blades are fixedly connected to the outer side of the rotating ring, and the two blades are evenly distributed around the rotating ring. The rotating ring and the cover plate form a snap-fit ​​quick-release structure through a through groove, a retaining plate, and the round holes and slots of the cylinder and extension block. This structure is convenient for disassembly and assembly and has a stable connection, effectively improving the efficiency of blade disassembly and assembly and the convenience of maintenance. At the same time, the snap-fit ​​fit is tight, and there is no loosening or shaking during flight, ensuring the dynamic balance of rotor rotation and enhancing the operational stability and wind resistance reliability of the UAV. A through groove is opened on the outer side of the rotating ring, and a cover plate is set on the top of the rotating ring. An extension block is fixedly connected to the side of the cover plate near the through groove. A retaining plate is fixedly connected to the inner wall of the through groove, and a slot is opened on the inner side of the extension block. The retaining plate is located inside the slot. The rotating ring and the cover plate are installed by snap-fitting the retaining plate and the through groove.

[0005] Furthermore, two cylinders are slidably connected to the inner wall of the through slot, symmetrically arranged around the clamping plate. A circular hole is opened on the outer side of the extension block, penetrating the extension block and located above the slot opening. The cylinder is located inside the circular hole. There are two through slots, alternating with the rotating blade on the rotating ring. Multiple protective nets are fixedly connected to the outer side of the connector. A fixing rod is fixedly connected to the inner wall of the protective net, and a ring plate is fixedly connected to the end of the fixing rod away from the protective net. There are three ring plates, and multiple protective plates are fixedly connected to the outer side of the ring plates. These multiple protective plates and ring plates constitute... A mesh plate, with a multi-layered annular protective structure consisting of a protective net, protective plate, ring plate, fixing rod, and spring plate on the outside of the rotor, not only prevents the rotor blades from being damaged by collision, but also regulates airflow and reduces the disturbance of crosswinds and gusts to the rotor. Combined with dynamic adjustment of the center of gravity, rotor tilt control, and aerodynamic self-stabilization design, it enables the UAV to maintain attitude stability, accurate flight path, and flight safety in complex wind field environments. A slot is opened in the middle of the top of the cover plate, and a fixing post is fixedly connected inside the slot. The end of the fixing post away from the slot is fixedly connected to the protective net. A spring plate is fixedly connected to the outside of the fixing rod. The spring plate is located in the gap between the protective net and the ring plate. There are two extension blocks.

[0006] Furthermore, the connecting component includes a drive component. A cylinder is fixedly connected to the bottom of the motor, and a fixed base is fixedly connected to the end of the cylinder near the motor. In the initial state, the cylinder is perpendicular to the drive component. At this time, the intermediate plate is located inside the square hole, and the elastic plate is located inside the cylinder. Utilizing the elastic properties of the elastic plate, the elastic plate undergoes elastic deformation as the cylinder rotates and extends or retracts along the square hole on the cylinder, thereby completing the overall tilting of the upper motor, rotating ring, and blades. This achieves the angle change of the rotor from vertical upward to horizontal backward, completing the mode conversion of lift and thrust. At the same time, the positioning post on the side wall of the drive component slides circumferentially along the annular groove on the cylinder, limiting and guiding the tilting angle to ensure a smooth tilting process and precise angle. Without wobbling, the open end of the fixed base is rotatably connected to the output end of the drive component. One end of the drive component is located inside the cylinder. A middle plate is fixedly connected to the top of the drive component, and an elastic plate is fixedly connected to the end of the middle plate. There are two elastic plates, which are symmetrically arranged with the middle plate as the center. A square hole is opened on the outer side of the cylinder near the middle plate, and an annular groove is opened on the outer side of the cylinder away from the motor. The end of the annular groove away from the positioning post is a circular hole. When the rotor assembly is switched to the horizontal direction, the positioning post is located inside the circular hole of the annular groove. At this time, the positioning post is locked into the circular hole to achieve the positioning of the tilt angle, ensuring accurate, non-moving, and non-loosening position in both vertical and horizontal modes. A positioning post is fixedly connected to the side of the drive component near the annular groove.

[0007] Furthermore, the intermediate component includes a housing, which is fixedly connected to the bottom of the fixed wing. A central rod is slidably connected to the middle of the housing, penetrating through the housing. A rack is fixedly connected to the outer side of the central rod. A motor is fixedly connected to the inner wall of the housing near the rack. The intermediate component serves as the core component for the rotor assembly's fore-and-aft adjustment and attitude support along the fixed wing. The housing is fixed below the fixed wing. The motor drives the central rod to slide back and forth along the housing via gears meshing with the rack on the central rod, causing the end rotor assembly to move synchronously. This enables the rotor position to adaptively adjust with the overall center of gravity, allowing for real-time adjustment of the rotor position based on load, battery consumption, and flight mode, thus maximizing lift. The center of gravity is aligned with the center of gravity of the entire machine to improve pitch stability and wind resistance, and to avoid pitch deviation and attitude oscillation. The fixed block on the outer side of the intermediate rod moves synchronously with it, which plays a role in limiting and enhancing rigidity. The output end of the motor is equipped with a gear. The motor is connected to the intermediate rod through the gear meshing between the gear and the rack. A support member is rotatably connected to the middle of the outer side of the intermediate rod. A rotating member is fixedly connected to the inner wall of the housing near the support member. The rotating member contacts the support member. A through hole is opened on the side of the housing near the support member. A fixed block is fixedly connected to the outer side of the intermediate rod. There are multiple fixed blocks. Multiple racks and fixed blocks are arranged alternately. The end of the intermediate rod is fixedly connected to the connecting member.

[0008] Furthermore, the support component includes a connecting seat, which is rotatably connected to the intermediate rod. The outer side of the connecting seat is toothed, and the connecting seat meshes with the gear of the rotating component. A limit plate is fixedly connected to the side of the connecting seat near the through hole. During use, the support component can retract into the groove, making the overall shape of the drone more compact, reducing its lateral dimensions and storage volume, and improving the equipment's mobility and deployment capabilities. The support component adopts a structure of limit plate and arc-shaped pressure plate combined with spring compression. When stationary, the pressure plate expands outward to form a stable support, ensuring that the drone is parked securely and that the rotor and fuselage do not touch the ground. During flight, the support component drives the limit plate and pressure plate to retract into the groove of the fixed wing as a whole, without protruding. The aerodynamic shape reduces wind resistance, improves wind resistance and cruising efficiency. The limiting plate limits the swing range of the pressure plate to prevent excessive deflection. The spring keeps the pressure plate in an elastic and compressed state, which not only enhances the support rigidity but also buffers the impact of the ground. At the same time, it does not occupy space after being recovered and does not interfere with the movement of the rotor and fixed wing. The whole has the advantages of stable support, vibration damping, smooth aerodynamics and reliable structure. The pressure plate is set on the outer side of the limiting plate away from the connecting seat. The middle column is fixedly connected to the middle of the pressure plate. The end of the middle column away from the pressure plate is slidably connected to the limiting plate. The outer side of the middle column is fitted with a spring. The two ends of the spring are fixedly connected to the limiting plate and the pressure plate respectively. The pressure plate is arc-shaped.

[0009] Compared with the prior art, the beneficial effects of the present invention are as follows: This self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV features a snap-fit ​​quick-release structure where the swivel and cover plate are connected by through slots, clamping plates, and the round holes and grooves of the cylinder and extension block. This structure enables convenient assembly and disassembly while ensuring a stable connection, effectively improving the efficiency of blade assembly and disassembly and the ease of maintenance. At the same time, the snap-fit ​​fit is tight, preventing loosening or shaking during flight, thus ensuring the dynamic balance of the rotor rotation and enhancing the operational stability and wind resistance reliability of the UAV.

[0010] (II) This self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV has multiple protective plates and ring plates forming a mesh plate. The outer side of the rotor is composed of a multi-layered ring-shaped protective structure consisting of a protective net, protective plates, ring plates, fixing rods, and spring plates. This structure not only avoids damage to the rotor blades from collisions but also regulates airflow and reduces the disturbance of crosswinds and gusts to the rotor. Combined with dynamic adjustment of the center of gravity, rotor tilt control, and aerodynamic self-stabilization design, the UAV can maintain stable attitude, accurate flight path, and safe flight in complex wind field environments.

[0011] (III) This self-stabilizing, wind-resistant vertical take-off fixed-wing UAV utilizes the elastic properties of the elastic plate, which causes the elastic plate to undergo elastic deformation as the cylinder rotates and extend or retract along the square hole on the cylinder, thereby completing the overall tilting of the upper motor, rotating ring and blades, realizing the angle change of the rotor from vertical upward to horizontal backward, and completing the mode conversion of lift and thrust.

[0012] (iv) The self-stabilizing and wind-resistant vertical take-off fixed-wing UAV has a central rod that slides back and forth along the shell, driving the end rotor assembly to move synchronously. This enables the rotor position to be adaptively adjusted according to the center of gravity of the whole aircraft, so that the rotor position can be adjusted in real time according to the load, battery consumption and flight mode, so that the center of lift and the center of gravity of the whole aircraft are aligned, improving pitch stability and wind resistance, and avoiding pitch deviation and attitude oscillation. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the structure of the invention from a bottom view; Figure 3 This is a partial structural schematic diagram of the present invention; Figure 4 This is a schematic diagram of the rotor assembly of the present invention; Figure 5 This is a partial enlarged view of the rotor assembly of the present invention, which is a structural schematic diagram. Figure 6 This is a partial structural schematic diagram of the rotor assembly of the present invention; Figure 7 This is a partial cross-sectional structural schematic diagram of the rotor assembly of the present invention; Figure 8 This is a schematic diagram of the rotating ring structure of the present invention; Figure 9 This is a schematic diagram of the cover plate of the present invention; Figure 10 This is a schematic diagram of the structure of the connector of the present invention; Figure 11 This is a schematic diagram of the structure of the intermediate component of the present invention; Figure 12 This is a schematic diagram of the support component of the present invention.

[0014] In the diagram: 1. Main body; 2. Fixed wing; 3. Tail wing; 4. Rotor assembly; 41. Protective net; 42. Connector; 421. Drive component; 422. Cylinder; 423. Fixed base; 424. Elastic plate; 425. Annular groove; 426. Positioning post; 427. Intermediate plate; 428. Square hole; 43. Motor; 44. Rotating blade; 45. Rotating ring; 46. Spring plate; 47. Fixed rod; 48. Fixed post; 49. Protective plate; 410. Ring plate; 411. 412. Cover plate; 413. Slot; 414. Cylinder; 415. Plate; 416. Through slot; 417. Extension block; 418. Round hole; 419. Groove; 50. Intermediate component; 51. Housing; 52. Intermediate rod; 53. Rack; 54. Fixing block; 55. Support component; 551. Connecting seat; 552. Limiting plate; 553. Pressure plate; 554. Spring; 555. Intermediate column; 56. Rotating component; 57. Motor; 58. Through hole; 6. Groove. Detailed Implementation

[0015] Example 1, as Figures 1 to 9 As shown, this embodiment discloses a self-stabilizing and wind-resistant vertical take-off and landing fixed-wing UAV, including a main body 1 and two fixed wings 2 fixedly installed on the left and right sides of the main body 1. A tail wing 3 is fixedly connected to the rear end of the main body 1. The main body 1, fixed wings 2, and tail wing 3 constitute the basic aerodynamic and load-bearing body. The rotor assembly 4 is adjusted in the longitudinal direction of the fixed wings 2 through the intermediate component 5. With the tilt drive, blade rotation, quick-release assembly and ring protection structure of the rotor assembly 4, vertical take-off and landing, mode conversion, fixed-wing cruise and full-process self-stabilizing and wind-resistant operation are completed in sequence. The bottom of the fixed wings 2 is fixedly connected to the intermediate component 5, and a groove 6 is opened at the bottom of the fixed wings 2 near the intermediate component 5. Rotor assembly 4 is fixedly installed at the bottom of intermediate assembly 5; The rotor assembly 4 includes a connector 42, which is fixedly connected to the intermediate assembly 5. A motor 43 is fixedly connected to the top of the connector 42, and a rotating ring 45 is fixedly connected to the top of the motor 43. Two blades 44 are fixedly connected to the outer side of the rotating ring 45. The two blades 44 are evenly distributed around the rotating ring 45. The rotating ring 45 and the cover plate 411 form a snap-fit ​​quick-release structure through the through groove 415, the retaining plate 414, the cylinder 413, and the round hole 417 and slot 418 of the extension block 416. This structure facilitates easy assembly and disassembly and ensures a stable connection, effectively improving the assembly and disassembly efficiency of the blades 44. The system offers high efficiency and ease of maintenance, while ensuring a tight fit and preventing loosening or shaking during flight. This guarantees the dynamic balance of the rotor rotation, enhancing the operational stability and wind resistance of the UAV. The outer side of the swivel ring 45 has a through groove 415, and the top of the swivel ring 45 is equipped with a cover plate 411. An extension block 416 is fixedly connected to the side of the cover plate 411 near the through groove 415. A retaining plate 414 is fixedly connected to the inner wall of the through groove 415. A slot 418 is opened on the inner side of the extension block 416, and the retaining plate 414 is located inside the slot 418. The swivel ring 45 and the cover plate 411 are installed by the retaining plate 414 and the through groove 415.

[0016] Two cylinders 413 are slidably connected to the inner wall of the through groove 415. These two cylinders 413 are symmetrically arranged around the clamping plate 414. A circular hole 417 is opened on the outer side of the extension block 416, penetrating the extension block 416. The circular hole 417 is located above the slot opening 418, and the cylinders 413 are located inside the circular hole 417. There are two through grooves 415, which are alternately arranged with the rotating blade 44 on the rotating ring 45. A protective net 41 is fixedly connected to the outer side of the connecting piece 42. Multiple protective nets 41 are present. A fixing rod 47 is fixedly connected to the inner wall of the protective net 41. A ring plate 410 is fixedly connected to the end of the fixing rod 47 away from the protective net 41. There are three ring plates 410. Multiple protective plates 49 are fixedly connected to the outer side of the ring plates 410. Multiple protective plates 49 and ring plates 410 form a mesh plate. The outer side of the rotor consists of a multi-layered ring-shaped protective structure composed of a protective net 41, protective plates 49, ring plates 410, fixing rods 47 and spring plates 46. This structure not only prevents the rotor blades 44 from being damaged by collisions, but also regulates airflow and reduces the disturbance of crosswinds and gusts to the rotor. Combined with dynamic adjustment of the center of gravity, rotor tilt control and aerodynamic self-stabilization design, the UAV can maintain stable attitude, accurate flight path and safe flight in complex wind field environments. A slot 412 is provided in the middle of the top of the cover plate 411. A fixing post 48 is fixedly connected inside the slot 412. The end of the fixing post 48 away from the slot 412 is fixedly connected to the protective net 41. A spring plate 46 is fixedly connected to the outer side of the fixing rod 47. The spring plate 46 is located in the gap between the protective net 41 and the ring plates 410. There are two extension blocks 416.

[0017] Example 2, based on Example 1, combined with... Figure 10It can be seen that the connecting part 42 includes a driving part 421, and a cylinder 422 is fixedly connected to the bottom of the motor 43. A fixed seat 423 is fixedly connected to the end of the cylinder 422 near the motor 43. In the initial state, the cylinder 422 is in a position perpendicular to the driving part 421. At this time, the intermediate plate 427 is located inside the square hole 428, and the elastic plate 424 is located inside the cylinder 422. Utilizing the elastic properties of the elastic plate 424, the elastic plate 424 undergoes elastic deformation as the cylinder 422 rotates and extends or retracts along the square hole 428 on the cylinder 422, thereby completing the overall tilting of the upper motor 43, rotating ring 45, and rotating blade 44, realizing the angle change of the rotor from vertical upward to horizontal backward, and completing the mode conversion of lift and thrust. At the same time, the positioning post 426 on the side wall of the driving part 421 slides circumferentially along the annular groove 425 on the cylinder 422 to limit and guide the tilting angle, ensuring that the tilting process is stable, the angle is accurate, and there is no wobbling. The open end of the fixed base 423 is rotatably connected to the output end of the drive component 421. One end of the drive component 421 is located inside the cylinder 422. A middle plate 427 is fixedly connected to the top of the drive component 421. An elastic plate 424 is fixedly connected to the end of the middle plate 427. There are two elastic plates 424, which are symmetrically arranged with the middle plate 427 as the center. A square hole 428 is opened on the outer side of the cylinder 422 near the middle plate 427. An annular groove 425 is opened on the outer side of the cylinder 422 away from the motor 43. The end of the annular groove 425 away from the positioning post 426 is a circular hole. When the rotor assembly 4 switches to the horizontal direction, the positioning post 426 is located inside the circular hole of the annular groove 425. At this time, the positioning post 426 is inserted into the circular hole to achieve the positioning and locking of the tilt angle, ensuring that the position is accurate, does not move, and does not loosen in both vertical and horizontal modes. The positioning post 426 is fixedly connected to the side of the drive component 421 near the annular groove 425.

[0018] Example 3, based on Examples 1 and 2, combined with... Figures 11 to 12It can be seen that the intermediate component 5 includes a housing 51, which is fixedly connected to the bottom of the fixed wing 2. An intermediate rod 52 is slidably connected to the middle of the housing 51, and the intermediate rod 52 passes through the housing 51. A rack 53 is fixedly connected to the outer side of the intermediate rod 52. A motor 57 is fixedly connected to the inner wall of the housing 51 near the rack 53. The intermediate component 5 serves as the core component for the rotor assembly 4 to adjust forward and backward along the fixed wing 2 and for attitude support. The housing 51 is fixed below the fixed wing. The motor 57 drives the intermediate rod 52 to slide forward and backward along the housing 51 through gear meshing with the rack 53 on the intermediate rod 52, thereby driving the end rotor assembly 4 to move synchronously. This enables the rotor position to be adaptively adjusted according to the center of gravity of the entire aircraft, allowing the rotor position to be adjusted in real time according to the load, battery consumption, and flight mode, so that the center of lift is aligned with the center of gravity of the entire aircraft. The center of gravity remains aligned, improving pitch stability and wind resistance, and preventing pitch deviation and attitude oscillation. The fixing block 54 on the outer side of the intermediate rod 52 moves synchronously with it, serving to limit movement and enhance rigidity. The output end of the motor 57 is equipped with a gear, and the motor 57 is connected to the intermediate rod 52 through gear meshing between the gear and the rack 53. A support member 55 is rotatably connected to the middle of the outer side of the intermediate rod 52. A rotating member 56 is fixedly connected to the inner wall of the housing 51 near the support member 55. The rotating member 56 contacts the support member 55. A through hole 58 is opened on the side of the housing 51 near the support member 55. A fixing block 54 is fixedly connected to the outer side of the intermediate rod 52. There are multiple fixing blocks 54, and multiple racks 53 and fixing blocks 54 are alternately arranged. The end of the intermediate rod 52 is fixedly connected to the connector 42.

[0019] Support component 55 includes a connecting seat 551, which is rotatably connected to the intermediate rod 52. The outer side of the connecting seat 551 is toothed, and the connecting seat 551 meshes with the rotating component 56 via a gear. A limiting plate 552 is fixedly connected to the side of the connecting seat 551 near the through hole 58. During use, support component 55 can retract into the groove 6, making the overall shape of the UAV more compact, reducing its lateral dimensions and storage volume, and improving the mobile deployment capability of the equipment. Support component 55 adopts a structure in which the limiting plate 552 and the arc-shaped pressure plate 553 are combined with a spring to press together. When stationary, the pressure plate expands outward to form a stable support, ensuring that the UAV is parked stably and that the rotor and fuselage do not touch the ground. During flight, support component 55 drives the limiting plate 552 and the pressure plate 553 to retract into the groove 6 of the fixed wing 2 as a whole, without protruding the aerodynamic shape and reducing the impact of the airflow. To reduce wind resistance, improve wind resistance and cruise efficiency, the limiting plate 552 is used to limit the swing range of the pressure plate 553 and prevent excessive deflection. The spring 554 keeps the pressure plate 553 in an elastic and compressed state, which not only enhances the support rigidity but also buffers the ground impact. At the same time, it does not occupy space after being retracted and does not interfere with the movement of the rotor and fixed wing 2. The whole has the advantages of stable support, vibration damping, smooth aerodynamics and reliable structure. The pressure plate 553 is set on the outer side of the limiting plate 552 away from the connecting seat 551. The middle column 555 is fixedly connected to the middle of the pressure plate 553. The end of the middle column 555 away from the pressure plate 553 is slidably connected to the limiting plate 552. The spring 554 is sleeved on the outer side of the middle column 555. The two ends of the spring 554 are fixedly connected to the limiting plate 552 and the pressure plate 553 respectively. The pressure plate 553 is arc-shaped.

[0020] In operation, the motors 43 in the multiple rotor assemblies 4 drive the rotating ring 45 and the blades 44 to rotate at high speed, generating vertical lift to achieve vertical take-off, landing, and hovering. Simultaneously, the rotating component 56 drives the connecting seat 551 of the support component 55 to rotate, causing the connecting seat 551 to drive the pressure plate 553 and the limiting plate 552 to rotate around the intermediate rod 52, positioning the limiting plate 552 and the pressure plate 553 inside the groove 6. Subsequently, the driving component 421 within the connecting component 42 drives the fixed seat 423, the cylinder 422, and the components connected to the top of the cylinder 422 to rotate, causing the cylinder 422 to change from a state perpendicular to the driving component 421 to a rotating body parallel to the driving component 421. The motor 43 and the rotor tilt as a whole, realizing the mode switching of vertical lift and horizontal thrust, and completing the smooth connection between vertical take-off, transition and fixed-wing cruise. During the fixed-wing cruise, the motor 57 in the intermediate component 5 drives the intermediate rod 52 to slide axially along the housing 51 through the output end gear meshing with the rack 53 on the intermediate rod 52. This drives the rotor assembly 4 at the end of the intermediate rod 52 to move synchronously back and forth along the bottom of the fixed wing 2. This compensates for the center of gravity shift caused by load changes, fuel / battery consumption and tilting attitude in real time, so that the total lift center of the rotor is always aligned with the center of gravity of the whole aircraft, thus ensuring the stability of the pitch attitude from a structural point of view.

Claims

1. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV), characterized in that: include The main body (1) and two fixed wings (2) are fixedly installed on the left and right sides of the main body (1). The rear end of the main body (1) is fixedly connected to a tail wing (3). The bottom of the fixed wing (2) is fixedly connected to a middle component (5). The bottom of the fixed wing (2) near the middle component (5) is provided with a groove (6). Rotor assembly (4), which is fixedly installed at the bottom of intermediate assembly (5); The rotor assembly (4) includes a connector (42), which is fixedly connected to the intermediate assembly (5). A motor (43) is fixedly connected to the top of the connector (42), and a rotating ring (45) is fixedly connected to the top of the motor (43). A rotating blade (44) is fixedly connected to the outer side of the rotating ring (45). There are two rotating blades (44), which are evenly distributed around the rotating ring (45). A through groove is provided on the outer side of the rotating ring (45). 415), the top of the rotating ring (45) is provided with a cover plate (411), the cover plate (411) is fixedly connected to an extension block (416) on the side near the through groove (415), the inner wall of the through groove (415) is fixedly connected with a clamping plate (414), the inner side of the extension block (416) is provided with a slot (418), the clamping plate (414) is located inside the slot (418), and the rotating ring (45) and the cover plate (411) are installed by clamping the clamping plate (414) and the through groove (415).

2. The self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that: The inner wall of the through groove (415) is slidably connected with a cylinder (413). There are two cylinders (413), which are symmetrically arranged with the clamping plate (414) as the center. A circular hole (417) is opened on the outer side of the extension block (416). The circular hole (417) penetrates the extension block (416). The circular hole (417) is located above the slot (418). The cylinder (413) is located inside the circular hole (417). There are two through grooves (415). The two through grooves (415) and the rotating blade (44) are alternately arranged on the rotating ring (45).

3. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 2, characterized in that: A protective net (41) is fixedly connected to the outside of the connector (42). There are multiple protective nets (41). A fixing rod (47) is fixedly connected to the inner wall of the protective net (41). A ring plate (410) is fixedly connected to the end of the fixing rod (47) away from the protective net (41). There are three ring plates (410). A protective plate (49) is fixedly connected to the outside of the ring plate (410).

4. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 3, characterized in that: There are multiple protective plates (49). A slot (412) is provided at the top center of the cover plate (411). A fixing post (48) is fixedly connected inside the slot (412). One end of the fixing post (48) away from the slot (412) is fixedly connected to the protective net (41). A spring plate (46) is fixedly connected to the outside of the fixing rod (47). The spring plate (46) is located at the interval between the protective net (41) and the ring plate (410). There are two extension blocks (416).

5. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that: The connector (42) includes a drive component (421). A cylinder (422) is fixedly connected to the bottom of the motor (43). A fixed seat (423) is fixedly connected to one end of the cylinder (422) near the motor (43). The open end of the fixed seat (423) is rotatably connected to the output end of the drive component (421). One end of the drive component (421) is located inside the cylinder (422). An intermediate plate (427) is fixedly connected to the top of the drive component (421).

6. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 5, characterized in that: An elastic plate (424) is fixedly connected to the end of the intermediate plate (427). There are two elastic plates (424), which are symmetrically arranged with the intermediate plate (427) as the center. A square hole (428) is opened on the outer side of the cylinder (422) near the intermediate plate (427). An annular groove (425) is opened on the outer side of the cylinder (422) away from the motor (43). A positioning column (426) is fixedly connected to the side of the drive member (421) near the annular groove (425).

7. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that: The intermediate component (5) includes a housing (51), which is fixedly connected to the bottom of the fixed wing (2). A middle rod (52) is slidably connected to the middle of the housing (51), and the middle rod (52) passes through the housing (51). A rack (53) is fixedly connected to the outside of the middle rod (52). A motor (57) is fixedly connected to the inner wall of the housing (51) near the rack (53). The output end of the motor (57) is provided with a gear. The motor (57) is connected to the middle rod (52) through gear meshing between the gear and the rack (53).

8. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 7, characterized in that: A support member (55) is rotatably connected to the middle outer side of the intermediate rod (52). A rotating member (56) is fixedly connected to the inner wall of the housing (51) near the support member (55). The rotating member (56) is in contact with the support member (55). A through hole (58) is opened on the side of the housing (51) near the support member (55). A fixing block (54) is fixedly connected to the outer side of the intermediate rod (52). There are multiple fixing blocks (54). Multiple racks (53) and fixing blocks (54) are alternately arranged. The end of the intermediate rod (52) is fixedly connected to the connector (42).

9. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 8, characterized in that: The support member (55) includes a connecting seat (551), which is rotatably connected to the intermediate rod (52). The outer side of the connecting seat (551) is toothed. The connecting seat (551) meshes with the rotating member (56) gear. A limiting plate (552) is fixedly connected to the side of the connecting seat (551) near the through hole (58). A pressure plate (553) is provided on the outer side of the limiting plate (552) away from the connecting seat (551).

10. A self-stabilizing, wind-resistant vertical takeoff and landing fixed-wing UAV according to claim 9, characterized in that: A middle column (555) is fixedly connected to the middle part of the pressure plate (553). The end of the middle column (555) away from the pressure plate (553) is slidably connected to the limiting plate (552). A spring (554) is sleeved on the outside of the middle column (555). The two ends of the spring (554) are fixedly connected to the limiting plate (552) and the pressure plate (553) respectively. The pressure plate (553) is arc-shaped.

Images