Streamline wing arm composite lift force self-stabilization three-rotor power system

Abstract

The invention relates to the technical field of flight devices, in particular to a streamline wing arm composite lift force self-stabilizing three-rotor-wing power system which comprises a fairing, wing-shaped machine arms are arranged on the outer wall of the fairing in an annular array mode, the fairing comprises a fairing chassis, and arc-shaped side plates are fixedly connected to the three sides of the top of the fairing chassis correspondingly; the tops of the three arc-shaped side plates are fixedly connected with conical top blocks, the tops of the outer sides of the three arc-shaped side plates are all fixedly connected with hinge blocks, and the fairing and the wing-shaped machine arms are arranged, so that efficient operation and stable control of the streamline wing arm composite lift force self-stabilization three-rotor power system are achieved; according to the power system, the air resistance is effectively reduced and the flight efficiency is improved through the design of the streamline wing arms, and the automatic unfolding and folding of the wing-shaped arms and the flexible adjustment of the screw pitch of the rotor wing mechanism are realized through the precise mechanical structure design, so that the power requirements of the unmanned aerial vehicle in different flight states are met.

Description

Technical Field

[0001] The present invention relates to the technical field of flying devices, and more particularly to a streamlined wing-arm composite lift self-stabilizing three-rotor power system. Background Art

[0002] A multirotor aircraft, also known as a multi-axis aircraft or multi-propeller aircraft, is an aircraft with multiple rotors. This type of aircraft generates the necessary lift through the rotational motion of the rotors, thereby achieving vertical take-off, hovering in the air, and performing a series of complex flight maneuvers. In the field of multirotor aircraft design, the streamlined wing-arm compound lift self-stabilizing three-rotor power system represents a cutting-edge technological innovation. The core goal of this system is to improve the overall stability and lift efficiency of the aircraft. By adopting a streamlined wing-arm design, the system significantly reduces the air resistance encountered by the aircraft when moving in the air. At the same time, the application of the compound lift principle enables the aircraft to generate more powerful lift during flight. In addition, the integration of self-stabilization technology further enhances the stability of the aircraft, ensuring that the aircraft can maintain a stable and safe flight state even in a changing flight environment.

[0003] Patent document CN108248839A discloses an all-weather multi-rotor drone comprising a fuselage, an arm fixedly connected to the fuselage, a motor fixedly mounted on the arm, and a propeller fixedly mounted on the motor. The fuselage comprises a body and a nose fixedly mounted at one end of the body. The nose has a hemispherical shape, the top of the body is arc-shaped, and the tail of the body has a quarter-spherical shape. The bottom of the body comprises a streamlined arc segment connected to the nose and a horizontal segment integrally connected to the streamlined arc segment. The diameter of the streamlined arc segment decreases from the connection point between the nose and the horizontal segment. A first rain shield is attached to the exterior of the fuselage, closely fitting the fuselage. The present invention provides an all-weather multi-rotor drone with a streamlined body. By attaching a rain shield to the fuselage, the drone has low flight resistance and can meet the requirements of long-duration flight in severe rainy and snowy weather conditions.

[0004] A common problem in the propulsion systems of multirotor aircraft is their relatively low efficiency. In traditional designs, the rotors generate both lift and counter-torque, which must be balanced through additional control mechanisms, such as servo deflection, tail rotor compensation, or differential steering. However, these passive adjustment methods increase the mechanical complexity of the entire system, leading to increased energy loss. The drag generated by the control mechanisms themselves further reduces aerodynamic efficiency, and the complex transmission components also result in additional energy loss. Furthermore, the presence of horizontal force components in traditional solutions causes the aircraft to tilt during hovering, reducing the effective thrust-to-weight ratio and, in turn, affecting aircraft performance. Control delays and power compensation also result in additional energy waste. These factors, combined, limit the endurance and payload efficiency of multirotor systems, making them unable to meet the requirements of modern aircraft for lightweight and energy-efficient propulsion systems. Furthermore, the arms, when not in use, increase storage and transportation space requirements, posing a significant challenge in space-constrained applications. Summary of the Invention

[0005] In order to overcome the above-mentioned defects of the prior art, the present invention provides a streamlined wing-arm composite lift self-stabilizing three-rotor power system. The technical problem to be solved by the present invention is: the horizontal component of the traditional solution causes the aircraft to tilt and hover, reducing the effective thrust-to-weight ratio, and the control delay and power compensation cause additional energy waste. These factors limit the endurance and load efficiency of the multi-rotor system, and cannot meet the requirements of modern aircraft for lightweight and energy-efficient power systems. At the same time, the arms unfolded when not in use increase the space occupied for storage and transportation.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0007] A streamlined wing-arm composite lift self-stabilizing three-rotor power system comprises a fairing, wherein an outer wall of the fairing is provided with a wing-shaped machine arm in a circular array;

[0008] The fairing comprises a fairing chassis, the top three sides of the fairing chassis are all fixedly connected with arc-shaped side panels, and the tops of the three arc-shaped side panels are fixedly connected with conical top blocks.

[0009] As a further solution of the present invention: the outer tops of the three arc-shaped side panels are fixedly connected with hinge blocks, the inner tops of the three arc-shaped side panels are fixedly connected with top gear plates, the top of the fairing chassis is fixedly connected with a motor in the middle of the inner sides of the three arc-shaped side panels, and the output end of the motor is fixedly connected with a columnar vertical pole.

[0010] As a further solution of the present invention: the inner tops of the three arc-shaped side panels are fixedly connected to a second hinge block, the outer sides of the three second hinge blocks extend to the outer sides of the three arc-shaped side panels, and the outer sides of the three second hinge blocks are rotatably connected to a rotating short rod.

[0011] As a further solution of the present invention: the outer wall of the columnar upright is slidably connected to a sliding shaft, the three sides of the outer wall of the sliding shaft are fixedly connected to connecting blocks, the outer sides of the three connecting blocks are fixedly connected to vertical plates, the outer bottoms of the three vertical plates are fixedly connected to third hinge blocks, and the inner walls of the three third hinge blocks on the side away from the vertical plates are rotatably connected to rotating rods.

[0012] As a further solution of the present invention: the tops of the three rotating rods are rotatably connected to sliders, and the outer walls of the three sliders are slidably connected to the bottoms of the three rotating short rods.

[0013] As a further solution of the present invention: the three wing-shaped arms each include a wing-shaped arm body, the middle part of the top of the three wing-shaped arm bodies is fixedly connected to a cylindrical rotating rod, the outer walls of the three cylindrical rotating rods are rotatably connected to a cylindrical rotating rod connecting block, one side of the three cylindrical rotating rod connecting blocks is fixedly connected to the outside of the three rotating short rods, and the top ends of the three cylindrical rotating rods are fixedly connected to conical teeth.

[0014] As a further solution of the present invention: the bottoms of the three wing-shaped arm bodies are fixedly connected to the rotor mechanism, the outer sides of the three rotor mechanisms are rotatably connected to the rotating struts, and the outer walls of the three rotating struts away from the rotor mechanism are rotatably connected to the inner walls of the three hinge blocks.

[0015] As a further solution of the present invention: the three rotor mechanisms all include a rotor mechanism connecting block, the outer sides of the three rotor mechanism connecting blocks are fixedly connected with a fourth hinge block, the inner walls of the three fourth hinge blocks are rotatably connected to one side of the outer wall of the three rotating struts, and the tops of the three rotor mechanism connecting blocks are fixedly connected with a spherical rotating shaft connecting block.

[0016] As a further solution of the present invention: the top inner walls of the three spherical shaft connecting blocks are all rotatably connected with spherical shafts, and the tops of the three spherical shafts are all fixedly connected to the bottoms of the three wing-shaped machine arm bodies.

[0017] As a further solution of the present invention: one side of the three rotor mechanism connecting blocks is fixedly connected to a rotor connecting plate, and the outer sides of the three rotor connecting plates away from the rotor mechanism connecting blocks are fixedly connected to rotors.

[0018] The beneficial effects of the present invention are:

[0019] The present invention realizes the efficient operation and stable control of the streamlined wing-arm composite lift self-stabilizing three-rotor power system by providing a fairing and an wing-shaped arm. The power system not only effectively reduces air resistance and improves flight efficiency through the design of the streamlined wing-arm, but also realizes the automatic expansion and folding of the wing-shaped arm and the flexible adjustment of the rotor mechanism pitch through the precise mechanical structure design, thereby meeting the power requirements of the UAV in different flight states. In addition, the power system also has excellent controllability and flexibility, can adapt to different flight attitudes and wind direction changes, and provides a strong guarantee for the stable operation of the UAV. Therefore, the present invention has broad application prospects in the field of UAVs and will inject new vitality into the development of UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the main three-dimensional structure of the present invention;

[0021] Figure 2 It is a schematic diagram of a three-dimensional cross-sectional view of the main body of the present invention;

[0022] Figure 3 This is a schematic diagram of the three-dimensional separated cross-sectional structure of the main body of the present invention;

[0023] Figure 4 It is a schematic diagram of a three-dimensional cross-sectional structure of a fairing of the present invention;

[0024] Figure 5 This is a schematic diagram of a three-dimensional separated cross-sectional structure of a fairing according to the present invention;

[0025] Figure 6 This is a schematic diagram of the three-dimensional structure of the airfoil-shaped machine arm of the present invention;

[0026] Figure 7 It is a schematic diagram of the three-dimensional separation structure of the airfoil mechanism of the present invention;

[0027] Figure 8 It is a schematic diagram of the three-dimensional structure of the rotor mechanism of the present invention;

[0028] Figure 9 It is a schematic diagram of the three-dimensional unfolded structure of the main body of the present invention.

[0029] In the figure: 1. fairing; 11. fairing chassis; 12. curved side panels; 13. conical top block; 14. hinge block; 15. motor; 16. top gear plate; 17. second hinge block; 18. rotating short rod; 19. columnar vertical rod; 110. sliding shaft; 111. connecting block; 112. vertical plate; 113. third hinge block; 114. rotating rod; 115. slider; 2. wing-shaped machine arm; 21. wing-shaped machine arm body; 22. columnar rotating rod; 23. columnar rotating rod connecting block; 24. conical teeth; 25. rotor mechanism; 251. rotor mechanism connecting block; 252. fourth hinge block; 253. spherical shaft connecting block; 254. spherical shaft; 255. rotor connecting plate; 256. rotor; 26. rotating support rod. DETAILED DESCRIPTION

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0031] like Figure 1 As shown, the present invention provides a streamlined wing-arm composite lift self-stabilizing three-rotor power system, comprising a fairing 1, and an outer wall of the fairing 1 is provided with a ring array of wing-shaped arms 2.

[0032] like Figure 2-8As shown, the fairing 1 includes a fairing chassis 11, the top three sides of the fairing chassis 11 are fixedly connected with arc-shaped side panels 12, the tops of the three arc-shaped side panels 12 are fixedly connected with conical top blocks 13, the outer tops of the three arc-shaped side panels 12 are fixedly connected with hinge blocks 14, the inner tops of the three arc-shaped side panels 12 are fixedly connected with top gear plates 16, the top of the fairing chassis 11 is fixedly connected with a motor 15 in the middle of the inner sides of the three arc-shaped side panels 12, the output end of the motor 15 is fixedly connected with a columnar upright 19, the inner tops of the three arc-shaped side panels 12 are fixedly connected with second hinge blocks 17, the outer sides of the three second hinge blocks 17 extend to the outer sides of the three arc-shaped side panels 12, and the three The outer sides of the second hinge blocks 17 are rotatably connected to the rotating short rods 18, the outer walls of the columnar vertical rods 19 are slidably connected to the sliding shafts 110, the outer walls of the sliding shafts 110 are fixedly connected to the connecting blocks 111 on three sides, the outer sides of the three connecting blocks 111 are fixedly connected to the vertical plates 112, the outer bottoms of the three vertical plates 112 are fixedly connected to the third hinge blocks 113, the inner walls of the three third hinge blocks 113 away from the vertical plates 112 are rotatably connected to the rotating rods 114, the tops of the three rotating rods 114 are rotatably connected to the sliders 115, the outer walls of the three sliders 115 are slidably connected to the bottoms of the three rotating short rods 18, the three wing-shaped arms 2 all include an wing-shaped arm body 21, and the three wings The middle part of the top of the three-wing-shaped arm body 21 is fixedly connected with a columnar rotating rod 22, and the outer walls of the three columnar rotating rods 22 are rotatably connected with a columnar rotating rod connecting block 23. One side of the three columnar rotating rod connecting blocks 23 is fixedly connected to the outside of the three rotating short rods 18. The tops of the three columnar rotating rods 22 are fixedly connected with conical teeth 24. The bottoms of the three wing-shaped arm bodies 21 are fixedly connected with rotor mechanisms 25. The outer sides of the three rotor mechanisms 25 are rotatably connected with rotating struts 26. The outer walls of the three rotating struts 26 away from the rotor mechanism 25 are rotatably connected to the inner walls of the three hinge blocks 14. The three rotor mechanisms 25 include rotor mechanism connecting blocks 251. The outer sides of the wing mechanism connecting blocks 251 are all fixedly connected to fourth hinge blocks 252. The inner walls of the three fourth hinge blocks 252 are all rotatably connected to one side of the outer wall of the three rotating struts 26. The tops of the three rotor mechanism connecting blocks 251 are all fixedly connected to spherical shaft connecting blocks 253. The inner walls of the tops of the three spherical shaft connecting blocks 253 are all rotatably connected to spherical shafts 254. The tops of the three spherical shafts 254 are all fixedly connected to the bottoms of the three wing-shaped arm bodies 21. One side of the three rotor mechanism connecting blocks 251 is all fixedly connected to a rotor connecting plate 255. The outer sides of the three rotor connecting plates 255 away from the rotor mechanism connecting block 251 are all fixedly connected to rotors 256.

[0033] When the three wing-shaped arms 2 need to be unfolded, the UAV is started to rotate the fairing 1 and the wing-shaped arms 2 as a whole. After the fairing 1 and the wing-shaped arms 2 rotate as a whole, the centrifugal force will cause the second hinge blocks 17 on the three sides of the outer wall to rotate accordingly, and the rotating short rod 18 transmits power to the columnar rotating rod connecting block 23 of the wing-shaped arms 2. The three rotating rods 114 rotate with the third hinge block 113 as the axis, and drive the three sliders 115 to slide at the bottom of the three rotating short rods 18 to support the rotating short rods 18. The columnar rotating rod 22 drives the wing-shaped arms The main body 21 and the rotor mechanism 25 are initially unfolded. As the rotation speed gradually increases, the wing-shaped arm main body 21 is further unfolded. The unfolding of the three wing-shaped arm main bodies 21 drives the three rotating rods 114 to unfold again with the three third hinge blocks 113 as the axis. Since the three sliders 115 have slid to the end of the rotating short rod 18, the three third hinge blocks 113 drive the vertical plate 112, and drive the sliding shaft 110 to slide toward the top on the outer wall of the columnar vertical rod 19 through the connecting block 111, further stabilizing the unfolded state of the wing-shaped arm 2 and ensuring that it can rotate at high speed. The rotor mechanism 25 rotates steadily, and as the speed continues to increase, the rotor mechanism 25 begins to rotate to generate lift, providing the UAV with the power required for flight. In this process, the streamlined wing arm design effectively reduces air resistance and improves the flight efficiency of the UAV. When the three wing-shaped arm bodies 21 are fully unfolded, the three conical teeth 24 engage with the top three sides of the top gear plate 16. When the pitch of the wing-shaped arm body 21 needs to be adjusted, it is only necessary to start the motor 15 to rotate the columnar pole 19, thereby driving the top gear plate 16 to rotate. The rotation of the top gear plate 16 causes the three The conical teeth 24 rotate accordingly. Since the conical teeth 24 are fixedly connected to the airfoil arm body 21 through the cylindrical rotating rod 22, the rotation of the conical teeth 24 will drive the airfoil arm body 21 and the rotor mechanism 25 to rotate synchronously, thereby adjusting the pitch of the rotor mechanism 25 to meet the power requirements of the drone in different flight states. At the same time, the spherical shaft 254 design of the rotor mechanism 25 enables the rotor 256 to be fine-tuned within a certain range to adapt to different flight attitudes and wind direction changes, thereby enhancing the controllability and flexibility of the drone.

[0034] In addition, when the three wing-shaped arm bodies 21 are fully deployed, the airflow generated by the rotor 256 will be optimized through the design of the streamlined wing arms, further reducing air resistance and improving the flight stability and efficiency of the UAV;

[0035] When the UAV lands or needs to fold the wing-shaped arm 2 to reduce its size, the overall speed decreases, and the above-mentioned unfolding process is reversed to achieve the folding of the wing-shaped arm main body 21 and the rotor mechanism 25, so that the wing-shaped arm 2 is gradually folded to achieve a compact storage state, which is convenient for the transportation and storage of the UAV. In addition, the structural design of the entire power system is compact, and the connection between the components is firm and reliable, ensuring the stable operation of the UAV in high-speed flight and complex environments. In terms of design, the folding and unfolding mechanism of the UAV's wing-shaped arm 2 adopts advanced mechanical design principles, and achieves fast and smooth conversion through precise gears and articulated systems. This design not only improves the maneuverability of the UAV, but also ensures its reliability under various flight conditions. When unfolded, the UAV's wing-shaped arm 2 can quickly reach the optimal flight posture, and when folded, it can quickly reduce its size to adapt to different transportation and storage requirements. The flexibility and practicality of this design make the UAV more efficient and convenient when performing tasks.

[0036] Working principle of the present invention:

[0037] When the three wing-shaped arms 2 need to be unfolded, the UAV is started to rotate the fairing 1 and the wing-shaped arms 2 as a whole. After the fairing 1 and the wing-shaped arms 2 rotate as a whole, the centrifugal force will cause the second hinge blocks 17 on the three sides of the outer wall to rotate accordingly. The rotating short rod 18 transmits power to the columnar rotating rod connecting block 23 of the wing-shaped arms 2. The three rotating rods 114 rotate with the third hinge block 113 as the axis, and drive the three sliders 115 to slide at the bottom of the three rotating short rods 18 to support the rotating short rods 18. The cylindrical rotating rod 22 drives the wing-shaped machine arm main body 21 and the rotor mechanism 25 to initially unfold. As the rotation speed gradually increases, the wing-shaped machine arm main body 21 further unfolds. The unfolding of the three wing-shaped machine arm main bodies 21 drives the three rotating rods 114 to unfold again with the three third hinge blocks 113 as the axis. Since the three sliders 115 have slid to the end of the rotating short rod 18, the three third hinge blocks 113 drive the vertical plate 112, and drive the sliding shaft 110 to the top of the outer wall of the columnar vertical rod 19 through the connecting block 111. The top gear 16 rotates and the top gear 16 rotates, and the top gear 16 rotates to rotate the three conical teeth 24. Since the conical teeth 24 are fixedly connected to the wing-shaped arm body 21 through the columnar rotating rod 22, the conical teeth 24 are engaged with the top three sides of the top gear disc 16. The rotation will drive the wing-shaped arm body 21 and the rotor mechanism 25 to rotate synchronously, thereby adjusting the pitch of the rotor mechanism 25. When the three wing-shaped arm bodies 21 are fully unfolded, the airflow generated by the rotor 256 will be optimized through the design of the streamlined wing arm. When the UAV lands or needs to fold the wing-shaped arm 2 to reduce the volume, the overall speed drops, and the above-mentioned unfolding process is reversed to realize the folding of the wing-shaped arm body 21 and the rotor mechanism 25, so that the wing-shaped arm 2 is gradually folded to achieve a compact storage state.

[0038] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system is characterized by: It comprises a fairing (1), wherein an outer wall of the fairing (1) is provided with airfoil arms (2) in an annular array; The fairing (1) comprises a fairing chassis (11), the top three sides of the fairing chassis (11) are fixedly connected with arc-shaped side panels (12), and the tops of the three arc-shaped side panels (12) are fixedly connected with conical top blocks (13).

2. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 1, characterized in that: The outer tops of the three arc-shaped side panels (12) are fixedly connected to hinge blocks (14), the inner tops of the three arc-shaped side panels (12) are fixedly connected to top gear plates (16), the top of the fairing chassis (11) is fixedly connected to a motor (15) in the middle of the inner sides of the three arc-shaped side panels (12), and the output end of the motor (15) is fixedly connected to a columnar upright pole (19).

3. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 2, characterized in that: The inner tops of the three arc-shaped side panels (12) are all fixedly connected to a second hinge block (17), the outer sides of the three second hinge blocks (17) are all extended to the outer sides of the three arc-shaped side panels (12), and the outer sides of the three second hinge blocks (17) are all rotatably connected to a rotating short rod (18).

4. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 2, characterized in that: The outer wall of the columnar upright (19) is slidably connected to a sliding shaft (110), and the three sides of the outer wall of the sliding shaft (110) are fixedly connected to connecting blocks (111), the outer sides of the three connecting blocks (111) are fixedly connected to a vertical plate (112), the outer bottoms of the three vertical plates (112) are fixedly connected to a third hinge block (113), and the inner walls of the three third hinge blocks (113) on a side away from the vertical plate (112) are rotatably connected to a rotating rod (114).

5. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 4, characterized in that: The tops of the three rotating rods (114) are all rotatably connected to sliders (115), and the outer walls of the three sliders (115) are all slidably connected to the bottoms of the three rotating short rods (18).

6. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 1, characterized in that: The three wing-shaped machine arms (2) each include a wing-shaped machine arm body (21), the middle portions of the tops of the three wing-shaped machine arm bodies (21) are fixedly connected to a columnar rotating rod (22), the outer walls of the three columnar rotating rods (22) are rotatably connected to a columnar rotating rod connecting block (23), one side of the three columnar rotating rod connecting blocks (23) is fixedly connected to the outer sides of the three rotating short rods (18), and the tops of the three columnar rotating rods (22) are fixedly connected to a conical tooth (24).

7. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 6, characterized in that: The bottoms of the three wing-shaped arm bodies (21) are fixedly connected to a rotor mechanism (25), the outer sides of the three rotor mechanisms (25) are rotatably connected to a rotating support rod (26), and the outer walls of the three rotating support rods (26) away from the rotor mechanism (25) are rotatably connected to the inner walls of the three hinge blocks (14).

8. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 7, characterized in that: The three rotor mechanisms (25) each include a rotor mechanism connecting block (251), the outer sides of the three rotor mechanism connecting blocks (251) are fixedly connected to a fourth hinge block (252), the inner walls of the three fourth hinge blocks (252) are rotatably connected to one side of the outer wall of the three rotating struts (26), and the tops of the three rotor mechanism connecting blocks (251) are fixedly connected to a spherical shaft connecting block (253).

9. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 8, characterized in that: The top inner walls of the three spherical shaft connecting blocks (253) are all rotatably connected to spherical shafts (254), and the tops of the three spherical shafts (254) are all fixedly connected to the bottoms of the three wing-shaped machine arm bodies (21).

10. The streamlined wing-arm composite lift self-stabilizing tri-rotor power system according to claim 9, characterized in that: One side of each of the three rotor mechanism connection blocks (251) is fixedly connected to a rotor connection plate (255), and the outer sides of each of the three rotor connection plates (255) away from the rotor mechanism connection block (251) are fixedly connected to a rotor (256).

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