Tilting composite wing unmanned manned aircraft

Abstract

The invention relates to the field of aircraft devices, in particular to a tilting composite wing unmanned manned aircraft. Comprising a fuselage, the side streamline of the fuselage is fusiform, and the fuselage comprises an outer cover, a rotating head, a rudder, wings, a first motor, a first lifting arm, a second lifting arm, an undercarriage and a shell. Projections of the front face and the side faces are streamlines, the overall appearance streamlines meet the requirement for low resistance during high-speed flight, the tilting rotors are adopted, the front face projection area of the fuselage is increased while the rotors are increased, the front face projection area is reduced, the endurance is prolonged, energy consumption is reduced, and the use requirements are better met; according to the invention, the rudder is designed into a plurality of small control surfaces, but a driving point is also ensured to be driven by one motor, the maneuverability of the rudder cannot be reduced by the cooperative work of the plurality of control surfaces, and the design of the plurality of control surfaces enables the size of the aircraft to be smaller and the occupied area to be smaller, so that the storage convenience of the aircraft in practical use in the future is facilitated.

Description

Technical Field

[0001] The present invention relates to the field of aircraft devices, and in particular to an unmanned manned aircraft with tilt-rotating composite wings. Background Art

[0002] With the rapid development of science and technology, aviation transportation and operational needs are becoming more diversified and complex. Traditional fixed-wing aircraft, with their mature wing design and power layout, have shown excellent fuel economy and speed advantages when cruising at high altitudes and high speeds, and can complete long-distance flight missions quickly and efficiently. However, their dependence on runways greatly limits their use scenarios. They cannot take off and land in areas lacking suitable runway facilities, and their control flexibility is poor when flying at low altitudes and low speeds, making it difficult to adapt to complex low-altitude environments and precise operation requirements.

[0003] Helicopters, with their ability to take off and land vertically and hover in the air, play an irreplaceable role in rescue, lifting, close-ground reconnaissance and other tasks. However, when the helicopter's rotor flies forward at high speed, the airflow speed between the forward and backward blades is very different, resulting in low aerodynamic efficiency and severe energy loss, thus limiting its flight speed and range. In addition, its complex mechanical structure and high maintenance cost have become bottlenecks for further development.

[0004] As an emerging concept, tilt-rotating composite wing aircraft attempts to integrate the strengths of fixed-wing and rotary-wing aircraft, and has been widely studied and explored in the past few decades. However, the existing design solutions still face many unsolved problems. For example, the tilt-rotating structure is subjected to complex mechanical loads during the conversion process. How to ensure its reliability and durability under long-term and frequent use, while achieving fast and accurate angle conversion, is a major challenge. In terms of flight attitude control, since it involves the switching of multiple flight modes and the coordinated work of multiple aerodynamic surfaces and power sources, how to build an efficient, accurate and stable control system to cope with various flight conditions and external interference still needs in-depth research. The configuration of the power system must not only meet the high power requirements during vertical take-off and landing, but also ensure high efficiency and energy saving during horizontal flight, and achieve smooth transition between different flight modes, which requires fine optimization of the selection, layout and energy management strategy of the power source. In addition, the overall aerodynamic shape design of the aircraft must not only consider the low resistance requirements during high-speed cruising, but also take into account the airflow characteristics during vertical take-off and landing and low-altitude maneuvers, and achieve aerodynamic performance optimization within the entire flight envelope, which is also the key technical difficulty faced in the design of existing tilt-rotating composite wing aircraft. The present invention is aimed at these problems and proposes a new tilt-rotating composite wing unmanned manned aircraft design scheme, striving to break through the existing technical bottleneck and achieve a qualitative leap in aircraft performance. Summary of the invention

[0005] The purpose of the present invention is to overcome the above problems and provide a tilt-rotating composite wing unmanned manned aircraft. To achieve the above purpose, the present invention adopts the following technical solutions:

[0006] A tilt-rotating composite wing unmanned manned aircraft comprises a fuselage, the side streamline of the fuselage is shuttle-shaped, the fuselage comprises an outer cover, a rotating head, a rudder, a wing, a first motor, a first lifting arm, a second lifting arm, a landing gear, and an outer shell;

[0007] The outer cover is arranged at the middle end of the outer side of the wing, and the rudders are arranged in five groups, each group of the rudders is symmetrical up and down, and each group of the rudders is coaxially linked;

[0008] The first lifting arm is arranged inside the wing, and the landing gear is arranged at both sides under the fuselage. The landing gear on one side is an integrated part. After the landing gear is retracted, it is stored in a reserved groove under the belly. Four second lifting arms are arranged, two of which are arranged at the front of the fuselage, and two of which are arranged at the rear of the fuselage. The second lifting arms are sleeved with the fuselage.

[0009] There are twelve rotating heads, and all the rotating heads are provided with a 90-degree rotating structure.

[0010] This aircraft is very consistent with the actual use needs and future technological development direction of future civil artificial intelligence manned aircraft. Since this aircraft uses a large-area ventral wing and four shorter fixed wings to provide most of the lift required for flight, it has the long-endurance characteristics of fixed-wing aircraft, and at the same time, the 12 rotors that can be tilted 90 degrees make it also have the take-off and landing function of a helicopter. Most of the lift of this aircraft during flight is provided by the belly and four fixed wings. Its flight lift is basically the same as that of the current civil aviation fixed-wing aircraft, and is provided by the fuselage. The side streamline of the fuselage is shuttle-shaped, which is the most ideal high-speed flight streamline shape. This aircraft uses a fishtail multi-rudder linkage rudder, which can ensure the overall height stability of the fuselage when the fuselage turns and reduce the wind resistance coefficient. There are 5 groups of rudders, and the upper and lower rudders are symmetrical in one group. The upper and lower coaxial linkage design, the power conversion box and the coaxial shaft motor work together to ensure that there are 6 propellers on the front and rear sides of the fuselage. Even if half of the motors stop, normal flight safety can be guaranteed. The rotating head is the tilting mechanism of the propeller. This machine uses 12 rotors in order to comply with the national noise standards.

[0011] As an improvement, there are four outer covers, the outer covers are sleeved with the first lifting arm through screws, and the outer covers are arranged at the middle outer edge position of the first lifting arm;

[0012] The rotating head is provided with a paddle shaft, the paddle shaft is arranged at the middle and upper position of the rotating head, the paddle shaft is provided with a paddle blade, the lower end of the paddle shaft is sleeved with a first umbrella gear, the first umbrella gear is sleeved with a first bearing, the outer periphery of the first bearing is sleeved with a shaft sleeve, the first bearing is sleeved with a second bearing, a third bearing is arranged in the shaft sleeve, a positioning ring is installed at the lower end of the shaft sleeve, an annular frame is sleeved on the positioning ring, the positioning ring is sleeved with the third bearing, the positioning ring is sleeved with the paddle shaft, lifting arms are fixedly provided on both sides of the left side of the annular frame, the first umbrella gear and the second umbrella gear are meshed, the second umbrella gear and the annular frame, the annular frame is sleeved with a central axis, an axis hole is provided at the center of the barrel bottom of the annular frame, the central axis is sleeved with the axis hole,

[0013] As an improvement, each of the rotating heads is provided with a second motor, and the second power motor is used to drive the rotating head to rotate;

[0014] The annular frame barrel bottom is also provided with 6 screw holes opposite to each other, and the screw holes are symmetrically arranged on the edge of the barrel. The annular frame is provided with a notch, and the positioning ring is provided with a meshing ring, and the meshing ring is sleeved with the positioning ring, and the second umbrella mesh and the third umbrella mesh are sleeved with each other, and the second transmission shaft is sleeved with the second transmission shaft. The fourth bearing is sleeved with the annular frame, and the third motor is sleeved on the second lifting arm, and the third motor is adjacent to the left side of the annular frame. The meshing ring is engaged with the first meshing wheel, and the first meshing wheel is used to drive the positioning ring to drive the paddle shaft to rotate, and the positioning ring is used to position the paddle shaft.

[0015] As an improvement, the second lifting arm is symmetrically arranged with the front edge facing inward, the second lifting arm is sleeved with the outer shell, the wing and the outer shell are fixedly connected, a first transmission shaft is arranged inside the wing, one end of the first transmission shaft is linked to the second transmission shaft in the lifting arm, the outer end of the first transmission shaft is meshed with two second gears, the two second gears respectively drive the two propellers on the first lifting arm, and the first transmission shaft is respectively provided with fifth bearings near both ends.

[0016] As an improvement, a notch is provided in the middle of the rotating head, and the notch is used for the operation of the propeller shaft. A conversion box is provided on the first motor, and a hanging ear is sleeved between the first motor and the housing. A seat plate is provided on the first motor.

[0017] A fourth motor is provided on both sides of the fuselage, and the fourth motor is used to drive the landing gear to be retracted and extended. The motor shaft of the fourth motor is sleeved with the horizontal shaft at the upper end of the landing gear. The rotating head 8 is provided with a third transmission shaft and a third gear. The third transmission shaft and the transmission shaft outside the third gear are both provided with a first shaft seat. The motor shaft of the fourth motor is sleeved with a second shaft seat. The landing gear and the housing are connected by a linkage shaft.

[0018] The fourth motor is mounted on one end of the outer side of the landing gear, the second shaft seat is arranged at the root of both ends of the landing gear, the seat plate is sleeved with the third shaft seat, the first transmission shaft is sleeved with the third shaft seat, the third gear is sleeved with the first transmission shaft, the fourth gear is sleeved on the fifth bearing, and the third gear is sleeved with the two second gears.

[0019] As an improvement, the tail of the fuselage is provided with five rocker arms, and the rudders are provided with ten in total, five of which are provided on the upper surface of the fuselage, and five of which are provided on the lower surface of the fuselage. The upper and lower rudders share one axis, and the ten rudders are arranged in linkage.

[0020] A fifth motor is provided at the tail of the fuselage, and the fifth motor drives ten rudder plates. One end of the rocker arm is locked and sleeved with the vertical shaft, and the other end of the rocker arm is rotatably sleeved with the vertical shaft at the lower edge of the rudder. The vertical shaft is arranged at the rear tail of the machine, and the vertical shaft runs through the tail of the fuselage up and down. The upper and lower ends of the vertical shaft are sleeved with seventh bearings, and the seventh bearing is sleeved with the fuselage. A connecting rod is provided between the rockers, and the connecting rod is a linkage pull rod. The connecting rod is sleeved with one end of the rocker arm. A cam is provided on the fuselage, and one end of the cam is mounted on the fifth motor, and the other end of the cam is mounted on the vertical shaft of the connecting rod. The cam drives the upper and lower rudders in the same coaxial direction to rotate through the linkage of the connecting rod.

[0021] As an improvement, the fuselage further includes a front windshield, a cabin door, a skylight, and a rear window;

[0022] The outer shell is provided with a shell bottom, the fuselage is provided with a floor, the floor is provided with a battery area, and a groove is provided at a position corresponding to the landing gear on the outer shell.

[0023] As an improvement, the fuselage also includes a main shaft and a sixth motor. The end of the main shaft is sleeved with a gear ring, the main shaft is meshed with a bevel gear, the sixth motor drives the main shaft to rotate, two sixth bearings are sleeved on the main shaft, the sixth bearing is arranged near the outer edge of the outer shell, the main shaft is arranged at the root of the wing, the main shaft and the wing are an integral part, the sixth motor is sleeved on the seat plate inside the outer shell, a seventh motor is arranged in the fuselage, the first transmission shaft and the seventh motor are connected by a joint, a first shaft sleeve is arranged on the sixth bearing, two groups of eighth motors are arranged on the wing, the two groups of the eighth motors are concentric shafts, and four propellers are arranged on the wing.

[0024] The advantages of the present invention are:

[0025] 1. The front and side projections of the present invention are streamlined, and the overall streamlined shape meets the need for low resistance during high-speed flight.

[0026] 2. The present invention adopts a tilt-rotor design. This design does not increase the frontal projection area of ​​the fuselage while adding the rotor. Reducing the frontal projection area ensures extended flight time and reduced energy consumption, which is more in line with usage requirements.

[0027] 3. The present invention designs the rudder into multiple small control surfaces, but the driving point is still guaranteed to be driven by one motor. The coordinated work of multiple control surfaces can ensure that its maneuverability will not be reduced. The multiple control surface design can make the size of the aircraft smaller and occupy less space, which is beneficial to the convenience of the aircraft in future practical use. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a structural diagram of a tilt-rotating composite wing unmanned manned aircraft in Example 1.

[0029] Figure 2 Schematic diagram of the flight state from the side of Example 1

[0030] Figure 3 Schematic diagram of the top view of the flight state and the rudder structure in Example 1

[0031] Figure 4 The front view of the standby state of embodiment 1 is Figure 2 Schematic diagram of the landing gear structure cutaway at a\a

[0032] Figure 5 For Example 1 Figure 3 Schematic diagram of the tail power system structure of the middle b\b

[0033] Figure 6 For Example 1 Figure 3 Side view of the cross-section structure of c\c

[0034] Figure 7 The schematic diagram of the rotational top view of d\d in Example 1 is

[0035] Figure 8 Schematic diagram of alternative power system scheme of embodiment 2

[0036] The symbols in the figure are:

[0037] 1. Outer cover; 2. Front windshield; 3. Skylight; 4. Rear window; 5. Door; 6. Second lifting arm; 7. Blades; 8. Rotating head; 9. First lifting arm; 10. Landing gear; 11. Outer shell;

[0038] 13. notch; 14. conversion box; 15. first shaft seat; 16. first motor; 17. mounting ear; 18. seat plate; 19. fourth motor;

[0039] 20. Second shaft seat; 21. Linkage shaft; 22. Third shaft seat; 24. Second transmission shaft; 26. Fourth meshing wheel; 27. Fifth bearing; 28. First transmission shaft; 29. ​​Third meshing wheel;

[0040] 30. second meshing wheel; 31. third transmission shaft; 32. third motor; 33. first meshing wheel; 34. middle shaft; 36. meshing ring;

[0041] 38. The third bearing; 39. The propeller shaft;

[0042] 40. Positioning ring; 41. Ring frame; 42. First bearing; 44. Third parachute; 45. Fourth bearing; 47. Second bearing; 48. First parachute; 49. Second parachute;

[0043] 50, second motor; 51, screw hole; 52, wing; 53, rudder; 54, vertical shaft; 55, rocker arm; 56, connecting rod; 57, cam; 58, fifth motor; 59, groove;

[0044] 60. Shell bottom; 61. Floor; 62. Battery area;

[0045] 100, gear ring; 101, first sleeve; 102, seventh motor; 103, joint; 105, main shaft; 106, sixth bearing;

[0046] 107, cone wheel; 108, sixth motor; 120, eighth motor. DETAILED DESCRIPTION

[0047] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0048] In the description of the embodiments of the present invention, it should be noted that if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the invented product is usually placed when used. It is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0049] In addition, the terms "horizontal", "vertical", "overhanging" and the like do not mean that the components must be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0050] In the description of the embodiments of the present invention, "plurality" means at least 2.

[0051] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0052] The present invention is described in detail and specifically by specific examples below to provide a better understanding of the present invention, but the following examples do not limit the protection scope of the present invention.

[0053] Example 1

[0054] This embodiment discloses a tilt-rotating composite wing unmanned manned aircraft.

[0055] like Figure 1-Figure 7 As shown, this embodiment includes a fuselage, the side streamline of the fuselage is shuttle-shaped, and the fuselage includes an outer cover 1, a rotating head 8, a rudder 53, a wing 52, a first motor 16, a first lifting arm 9, a second lifting arm 6, a landing gear 10, and a shell 11;

[0056] The outer cover 1 is arranged at the middle end of the outer side of the wing 52, and there are five groups of rudders 53, each group of rudders 53 is symmetrical up and down, and each group of rudders 53 is coaxially linked;

[0057] The first lifting arm 9 is arranged inside the wing 52, and the landing gear 10 is arranged at both sides under the fuselage. The single-side landing gear 10 is an integrated part. After the landing gear 10 is retracted, it is retracted into the reserved groove under the belly. Four second lifting arms 6 are arranged, two second lifting arms 6 are arranged at the front of the fuselage, and two second lifting arms 6 are arranged at the rear of the fuselage. The second lifting arms 6 are sleeved with the fuselage.

[0058] There are twelve rotating heads 8, and all the rotating heads 8 are provided with a 90-degree rotating structure.

[0059] There are four outer covers 1, and the outer covers 1 are connected to the first lifting arm 9 through screws, and the outer covers 1 are arranged at the middle outer edge position of the first lifting arm 9;

[0060] A paddle shaft 39 is provided on the rotating head 8, and the paddle shaft 39 is arranged in the middle and upper position of the rotating head 8. A paddle blade 7 is provided on the paddle shaft 39. A first umbrella tooth 48 is sleeved on the lower end of the paddle shaft 39, and a first bearing 42 is sleeved on the first umbrella tooth 48. A sleeve is sleeved on the outer periphery of the first bearing 42, and a second bearing 47 is sleeved on the first bearing 42. A third bearing 38 is provided in the sleeve. A positioning ring 40 is installed at the lower end of the sleeve. An annular frame 41 is sleeved on the positioning ring 40. The positioning ring 40 is sleeved on the third bearing 38. The positioning ring 40 is sleeved on the paddle shaft 39. Lifting arms are fixedly provided on both sides of the left side of the annular frame 41. The first umbrella tooth 48 and the second umbrella tooth 49 are meshed. The second umbrella tooth 49 and the annular frame 41 are sleeved on the central axis 34. An axial hole is provided at the center of the barrel bottom of the annular frame 41, and the central axis 34 is sleeved on the axial hole.

[0061] The side streamline of the fuselage is shuttle-shaped, and this design can effectively reduce air resistance and improve flight efficiency. The fuselage is mainly composed of an outer cover 1, a rotating head 8, a rudder 53, a wing 52, a first motor 16, a first lifting arm 9, a second lifting arm 6, a landing gear 10, a shell 11 and other components.

[0062] The outer cover 1 is arranged at the middle end of the outer side of the wing 52, and there are four outer covers in total, which are connected to the first lifting arm 9 through a screw and are located at the middle outer edge of the first lifting arm 9. The outer cover 1 not only protects the internal structure, but also optimizes the aerodynamic shape of the wing 52 to a certain extent.

[0063] There are five groups of rudders 53, each group is symmetrical up and down, with a total of ten, and each group of rudders 53 is designed to be coaxially linked. Five of the rudders 53 are set on the upper surface of the fuselage, and five are set on the lower surface of the fuselage, and the vertical shaft 54 ​​runs through the tail of the fuselage to achieve vertical linkage. The tail of the fuselage is equipped with a fifth motor 58, which drives the ten rudders 53 to rotate through mechanisms such as a cam 57 and a connecting rod 56, thereby achieving precise control of the flight direction of the aircraft.

[0064] The first lifting arm 9 is arranged inside the wing 52, and is used to carry some flight-related components and participate in the adjustment of the flight attitude. The landing gear 10 is arranged on both sides of the fuselage. The single-side landing gear 10 is an integrated part, and can be stored in the reserved groove under the belly after being retracted to reduce the air resistance during flight. The retraction and extension of the landing gear 10 is driven by the fourth motor 19 on both sides of the fuselage. The motor shaft is sleeved with the horizontal shaft at the upper end of the landing gear 10, and is connected to the outer shell 11 through the linkage shaft 21 to ensure the stability and reliability of the retraction and extension action.

[0065] Four second lifting arms 6 are provided, two at the front and two at the rear, and are sleeved with the fuselage. Its unique layout and connection method help to improve the stability and controllability of the aircraft in different flight states.

[0066] Each rotating head 8 is provided with a second motor 50, and the second motor 50 is used to drive the rotating head 8 to rotate;

[0067] There are also 6 screw holes 51 opposite to the bottom of the annular frame 41, and the screw holes 51 are symmetrically arranged on the edge of the barrel. A notch 13 is provided on the annular frame 41, and a meshing ring 36 is provided on the positioning ring 40. The meshing ring 36 and the positioning ring 40 are sleeved, and the second umbrella mesh 49 and the third umbrella mesh 44 are sleeved. The second transmission shaft 24 is sleeved on the axial hole of the third umbrella mesh 44, and the fourth bearing 45 is sleeved on the second transmission shaft 24. The fourth bearing 45 and the annular frame 41 are sleeved, and the third motor 32 is sleeved on the second lifting arm 6. The third motor 32 is adjacent to the left side of the annular frame 41, and the meshing ring 36 is engaged with the first meshing wheel 33. The first meshing wheel 33 is used to drive the positioning ring 40 to drive the paddle shaft 39 to rotate, and the positioning ring 40 is used to position the paddle shaft 39.

[0068] The second lifting arm 6 is symmetrically arranged with the front edge facing inward, the second lifting arm 6 is sleeved with the outer shell 11, the wing 52 is fixedly connected to the outer shell 11, and a first transmission shaft 28 is arranged inside the wing 52. One end of the first transmission shaft 28 is linked to the second transmission shaft 24 in the lifting arm, and the outer end of the first transmission shaft 28 is meshed with two second gears 30. The two second gears 30 respectively drive the two propellers on the first lifting arm 9. Fifth bearings 27 are respectively arranged near the two ends of the first transmission shaft 28.

[0069] A notch 13 is provided in the middle of the rotating head 8, and the notch 13 is used for the operation of the propeller shaft 39. A conversion box 14 is provided on the first motor 16. A hanging ear 17 is sleeved between the first motor 16 and the housing 11. A seat plate 18 is provided on the first motor 16.

[0070] A fourth motor 19 is provided on both sides of the fuselage, and the fourth motor 19 is used to drive the landing gear 10 to be retracted and extended. The motor shaft of the fourth motor 19 is sleeved with the horizontal shaft at the upper end of the landing gear 10. The rotating head 8 is provided with a third transmission shaft 31 and a third gear 29. The third transmission shaft 31 and the transmission shaft outside the third gear 29 are both provided with a first shaft seat 15. The motor shaft of the fourth motor 19 is sleeved with the second shaft seat 20. The landing gear 10 and the housing 11 are connected through a linkage shaft 21.

[0071] The fourth motor 19 is installed at one end of the outer side of the landing gear 10, the second axle seat 20 is arranged at the root of both ends of the landing gear 10, the third axle seat 22 is sleeved on the seat plate 18, the first transmission shaft 28 and the third axle seat 22 are sleeved, the third gear 29 is sleeved on the first transmission shaft 28, the fourth gear 26 is sleeved on the fifth bearing 27, and the third gear 29 and the two second gears 30 are sleeved.

[0072] There are twelve rotating heads 8, each of which is provided with a 90-degree rotating structure, which can flexibly adjust the posture of the aircraft during flight. The rotating head 8 is provided with a propeller shaft 39, which is located in the upper middle position. The lower end of the propeller shaft 39 is sleeved with a first umbrella gear 48, and the first umbrella gear 48 is sleeved with a first bearing 42. The outer periphery of the first bearing 42 is sleeved with a shaft sleeve, and a third bearing 38 is provided in the shaft sleeve. A positioning ring 40 is installed at the lower end of the shaft sleeve, and a ring frame 41 is sleeved on the positioning ring 40. The first bearing 42 is also sleeved with a second bearing 47, and the positioning ring 40 is sleeved with the third bearing 38 and the propeller shaft 39 at the same time. The left sides of the ring frame 41 are provided with lifting arms for fixing, and the first umbrella gear 48 and the second umbrella gear 49 are meshed. The second umbrella gear 49 is connected to the ring frame 41, and the middle shaft 34 is sleeved on the ring frame 41. The center position of the barrel bottom is provided with an axis hole, and the middle shaft 34 is sleeved with the axis hole. Each rotating head 8 is equipped with a second motor 50 for driving the rotating head 8 to rotate, thereby realizing a tilting function and enabling the aircraft to smoothly switch between vertical take-off and landing and horizontal flight.

[0073] The tail of the fuselage is provided with five rocker arms 55, and there are ten rudders 53 in total, five of which are arranged on the upper surface of the fuselage, and five of which are arranged on the lower surface of the fuselage. The upper and lower rudders 53 share one axis, and the ten rudders 53 are arranged in linkage.

[0074] A fifth motor 58 is provided at the tail of the fuselage, and the fifth motor 58 drives ten rudder plates 53. One end of the rocker arm 55 is locked and sleeved with the vertical shaft 54, and the other end of the rocker arm 55 is rotatably sleeved with the vertical shaft at the lower edge of the rudder 53. The vertical shaft 54 ​​is provided at the rear tail of the machine, and the vertical shaft 54 ​​runs through the tail of the fuselage from top to bottom. The upper and lower ends of the vertical shaft 54 ​​are sleeved with the seventh bearing, and the seventh bearing is sleeved with the fuselage. A connecting rod 56 is provided between the rocker arms 55, and the connecting rod 56 is a linkage pull rod. The connecting rod 56 and one end of the rocker arm 55 are sleeved. A cam 57 is provided on the fuselage, and one end of the cam 57 is mounted on the fifth motor 58, and the other end of the cam 57 is mounted on the vertical shaft of the connecting rod 56. The cam 57 drives the upper and lower rudders 53 in the same axial direction to rotate through the linkage of the connecting rod 56.

[0075] The fuselage also includes a front windshield 2, a cabin door 5, a skylight 3, and a rear window 4;

[0076] The outer shell 11 is provided with a shell bottom 60 , a floor 61 is provided inside the fuselage, a battery area 62 is provided on the floor 61 , and a groove 59 is provided at a position corresponding to the landing gear 10 on the outer shell 11 .

[0077] The outer shell 11 is provided with a shell bottom 60, and the fuselage is provided with a floor 61. The floor 61 is provided with a battery area 62 for placing energy supply equipment required by the aircraft. A groove 59 is provided at a position corresponding to the landing gear 10 on the outer shell 11 to facilitate smooth retraction and extension of the landing gear 10. In addition, the fuselage also includes components such as a front windshield 2, a cabin door 5, a skylight 3, and a rear window 4 to meet the functional requirements and comfort requirements of manned flight.

[0078] In the vertical take-off and landing stage of this embodiment, the second motors 50 of the twelve rotating heads 8 drive the rotating heads 8 to rotate to a suitable angle, so that the propeller shaft 39 is in a vertical direction. At this time, the blades 7 rotate at high speed to generate an upward lift to lift the aircraft steadily. At the same time, the propellers on the first lifting arm 9 and the second lifting arm 6 also work together to adjust the speed and angle according to the attitude control requirements of the aircraft to ensure the stability and accuracy of the vertical take-off and landing process.

[0079] When the aircraft needs to transition to horizontal flight, the rotating head 8 gradually tilts under the drive of the second motor 50, and the propeller shaft 39 gradually changes from the vertical direction to the horizontal direction. At this time, the blades 7 of the rotating head 8 generate forward thrust, which is similar to the propeller action of a fixed-wing aircraft. The propeller on the wing 52 continuously provides lift and partial thrust under the coordinated action of the first transmission shaft 28, the seventh motor 102 and other power components, and cooperates with the tilting process of the rotating head 8 to enable the aircraft to smoothly enter the horizontal flight state. During the horizontal flight process, the lift is mainly generated by the aerodynamic shape of the wing 52, the blades 7 of the rotating head 8 and the propeller on the wing 52 provide forward thrust, and the rudder 53, driven by the fifth motor 58, adjusts the angle according to the instructions of the flight control system to achieve the flight attitude control of the aircraft such as steering and pitching.

[0080] During the entire flight process, the flight control system receives information from various sensors of the aircraft in real time, such as attitude sensors, speed sensors, position sensors, etc., accurately monitors and analyzes the flight status of the aircraft, and accurately controls the speed of each motor, the tilt angle of the rotating head 8, the deflection angle of the rudder 53, etc. according to the preset flight program or ground control instructions, to ensure that the aircraft can maintain stable, efficient and safe flight performance in different flight stages and working conditions.

[0081] Theoretically, the cruising speed of this embodiment is greater than 560 kilometers per hour, and the endurance is greater than 1,600 kilometers.

[0082] Example 2

[0083] This embodiment discloses a tilt-rotating composite wing unmanned manned aircraft.

[0084] like Figure 8 As shown, this embodiment includes a fuselage, the side streamline of the fuselage is shuttle-shaped, and the fuselage includes an outer cover 1, a rotating head 8, a rudder 53, a wing 52, a first motor 16, a first lifting arm 9, a second lifting arm 6, a landing gear 10, and a shell 11;

[0085] The outer cover 1 is arranged at the middle end of the outer side of the wing 52, and there are five groups of rudders 53, each group of rudders 53 is symmetrical up and down, and each group of rudders 53 is coaxially linked;

[0086] The first lifting arm 9 is arranged inside the wing 52, and the landing gear 10 is arranged at both sides under the fuselage. The single-side landing gear 10 is an integrated part. After the landing gear 10 is retracted, it is retracted into the reserved groove under the belly. Four second lifting arms 6 are arranged, two second lifting arms 6 are arranged at the front of the fuselage, and two second lifting arms 6 are arranged at the rear of the fuselage. The second lifting arms 6 are sleeved with the fuselage.

[0087] There are twelve rotating heads 8, and all the rotating heads 8 are provided with a 90-degree rotating structure.

[0088] There are four outer covers 1, and the outer covers 1 are connected to the first lifting arm 9 through screws, and the outer covers 1 are arranged at the middle outer edge position of the first lifting arm 9;

[0089] A paddle shaft 39 is provided on the rotating head 8, and the paddle shaft 39 is arranged in the middle and upper position of the rotating head 8. A paddle blade 7 is provided on the paddle shaft 39. A first umbrella tooth 48 is sleeved on the lower end of the paddle shaft 39, and a first bearing 42 is sleeved on the first umbrella tooth 48. A sleeve is sleeved on the outer periphery of the first bearing 42, and a second bearing 47 is sleeved on the first bearing 42. A third bearing 38 is provided in the sleeve. A positioning ring 40 is installed at the lower end of the sleeve. An annular frame 41 is sleeved on the positioning ring 40. The positioning ring 40 is sleeved on the third bearing 38. The positioning ring 40 is sleeved on the paddle shaft 39. Lifting arms are fixedly provided on both sides of the left side of the annular frame 41. The first umbrella tooth 48 and the second umbrella tooth 49 are meshed. The second umbrella tooth 49 and the annular frame 41 are sleeved on the central axis 34. An axial hole is provided at the center of the barrel bottom of the annular frame 41, and the central axis 34 is sleeved on the axial hole.

[0090] Each rotating head 8 is provided with a second motor 50, and the second motor 50 is used to drive the rotating head 8 to rotate;

[0091] There are also 6 screw holes 51 opposite to the bottom of the annular frame 41, and the screw holes 51 are symmetrically arranged on the edge of the barrel. A notch 13 is provided on the annular frame 41, and a meshing ring 36 is provided on the positioning ring 40. The meshing ring 36 and the positioning ring 40 are sleeved, and the second umbrella mesh 49 and the third umbrella mesh 44 are sleeved. The second transmission shaft 24 is sleeved on the axial hole of the third umbrella mesh 44, and the fourth bearing 45 is sleeved on the second transmission shaft 24. The fourth bearing 45 and the annular frame 41 are sleeved, and the third motor 32 is sleeved on the second lifting arm 6. The third motor 32 is adjacent to the left side of the annular frame 41, and the meshing ring 36 is engaged with the first meshing wheel 33. The first meshing wheel 33 is used to drive the positioning ring 40 to drive the paddle shaft 39 to rotate, and the positioning ring 40 is used to position the paddle shaft 39.

[0092] The second lifting arm 6 is symmetrically arranged with the front edge facing inward, the second lifting arm 6 is sleeved with the outer shell 11, the wing 52 is fixedly connected to the outer shell 11, and a first transmission shaft 28 is arranged inside the wing 52. One end of the first transmission shaft 28 is linked to the second transmission shaft 24 in the lifting arm, and the outer end of the first transmission shaft 28 is meshed with two second gears 30. The two second gears 30 respectively drive the two propellers on the first lifting arm 9. Fifth bearings 27 are respectively arranged near the two ends of the first transmission shaft 28.

[0093] The fuselage also includes a main shaft 105 and a sixth motor 108. The end of the main shaft 105 is sleeved with a gear ring 100. The main shaft 105 is meshed with a bevel gear 107. The sixth motor 108 drives the main shaft 105 to rotate. Two sixth bearings 106 are sleeved on the main shaft 105. The sixth bearing 106 is arranged near the outer edge of the outer shell 11. The main shaft 105 is arranged at the root of the wing 52. The main shaft 105 and the wing 52 are an integral part. The sixth motor 108 is sleeved on the seat plate 18 inside the outer shell 11. The fuselage is provided with a seventh motor 102. The first transmission shaft 28 and the seventh motor 102 are connected by a joint 103. The sixth bearing 106 is provided with a first shaft sleeve 101. Two groups of eighth motors 120 are provided on the wing 52. The two groups of eighth motors 120 are concentric shafts. Four propellers are provided on the wing 52.

[0094] The wing 52 of this embodiment is fixedly connected to the outer shell 11, and a first transmission shaft 28 is provided inside. One end of the first transmission shaft 28 is linked to the second transmission shaft 24 in the lifting arm, and the outer end is meshed with two second gears 30 to drive the two propellers on the first lifting arm 9 respectively. The first transmission shaft 28 is provided with fifth bearings 27 near both ends to ensure the stable rotation of the transmission shaft. The wing 52 is also provided with a main shaft 105 and a sixth motor 108. The end of the main shaft 105 is sleeved with a gear ring 100 and meshed with a bevel gear 107. The sixth motor 108 drives the main shaft 105 to rotate. Two sixth bearings 106 are sleeved on the main shaft 105 and are arranged near the outer edge of the outer shell 11. The main shaft 105 and the wing 52 are an integral part, and the sixth motor 108 is sleeved on the seat plate 18 inside the outer shell 11. Four propellers are provided on the wing 52, and sufficient lift and thrust are provided for the aircraft through reasonable power distribution and transmission system design. In addition, two groups of eighth motors 120 are provided on the wing 52, and the two groups are concentric shafts. The eighth motor 120 is provided in the fuselage. The first transmission shaft 28 and the eighth motor 120 are connected through a joint 103, which further optimizes the power configuration and flight performance of the wing 52.

[0095] The specific embodiments of the present invention are described in detail above, but they are only examples, and the present invention is not equivalent to the specific embodiments described above. For those skilled in the art, any equivalent modifications and substitutions made to the present invention are also within the scope of the present invention. Therefore, the equalization changes and modifications made without departing from the spirit and scope of the present invention should be included in the scope of the present invention.

Claims

1. A tilt-rotating composite wing unmanned manned aircraft, characterized in that: The invention comprises a fuselage, wherein the side streamline of the fuselage is shuttle-shaped, and the fuselage comprises an outer cover (1), a rotating head (8), a rudder (53), a wing (52), a first motor (16), a first lifting arm (9), a second lifting arm (6), a landing gear (10), and an outer shell (11); The outer cover (1) is arranged at the middle end of the outer side of the wing (52); the rudders (53) are provided in five groups; each group of the rudders (53) is symmetrical up and down; and each group of the rudders (53) is coaxially linked; The first lifting arm (9) is arranged inside the wing (52), the landing gear (10) is arranged at both sides of the fuselage, the landing gear (10) on one side is an integrated part, and the landing gear (10) is stored in a reserved groove under the belly after being retracted, four second lifting arms (6) are arranged, two of the second lifting arms (6) are arranged at the front of the fuselage, and two of the second lifting arms (6) are arranged at the rear of the fuselage, and the second lifting arms (6) are sleeved with the fuselage; The rotating heads (8) are provided in twelve numbers, and all the rotating heads (8) are provided with a 90-degree rotating structure.

2. The tilt-rotating composite wing unmanned manned aircraft according to claim 1, characterized in that: There are four outer covers (1), the outer covers (1) are sleeved with the first lifting arm (9) via screws, and the outer covers (1) are arranged at the middle outer edge position of the first lifting arm (9); The rotating head (8) is provided with a propeller shaft (39), the propeller shaft (39) is arranged at the middle and upper position of the rotating head (8), the propeller shaft (39) is provided with a propeller blade (7), the lower end of the propeller shaft (39) is sleeved with a first umbrella gear (48), the first umbrella gear (48) is sleeved with a first bearing (42), the outer periphery of the first bearing (42) is sleeved with a shaft sleeve, the first bearing (42) is sleeved with a second bearing (47), the shaft sleeve is provided with a third bearing (38), and the lower end of the shaft sleeve is installed with a positioning ring (40), The positioning ring (40) is sleeved with an annular frame (41), the positioning ring (40) is sleeved with a third bearing (38), the positioning ring (40) is sleeved with a propeller shaft (39), lifting arms are fixedly connected on both sides of the left side of the annular frame (41), the first umbrella gear (48) is meshed with the second umbrella gear (49), the second umbrella gear (49) is sleeved with the annular frame (41), a central axis (34) is sleeved on the annular frame (41), an axis hole is provided at the center of the barrel bottom of the annular frame (41), and the central axis (34) is sleeved with the axis hole.

3. The tilt-rotating composite wing unmanned manned aircraft according to claim 2, characterized in that: Each of the rotating heads (8) is provided with a second motor (50), and the second power motor (50) is used to drive the rotating head (8) to rotate; The annular frame (41) is further provided with six screw holes (51) opposite to the bottom of the barrel, the screw holes (51) are symmetrically arranged on the edge of the barrel, the annular frame (41) is provided with a notch (13), the positioning ring (40) is provided with a meshing ring (36), the meshing ring (36) and the positioning ring (40) are sleeved, the second umbrella gear (49) and the third umbrella gear (44) are sleeved, the shaft hole of the third umbrella gear (44) is sleeved with a second transmission shaft (24), and the second transmission shaft The fourth bearing (45) is sleeved on the annular frame (41), the fourth bearing (45) is sleeved on the annular frame (41), the third motor (32) is sleeved on the second lifting arm (6), the third motor (32) is adjacent to the left side of the annular frame (41), the meshing ring (36) is meshed with the first meshing wheel (33), the first meshing wheel (33) is used to drive the positioning ring (40) to drive the propeller shaft (39) to rotate, and the positioning ring (40) is used to position the propeller shaft (39).

4. The tilt-rotating composite wing unmanned manned aircraft according to claim 3, characterized in that: The second lifting arm (6) is symmetrically arranged with its front edge facing inwards. The second lifting arm (6) is sleeved with the outer shell (11). The wing (52) is fixedly connected to the outer shell (11). A first transmission shaft (28) is arranged inside the wing (52). One end of the first transmission shaft (28) is linked to a second transmission shaft (24) in the lifting arm. The outer end of the first transmission shaft (28) is meshed with two second gears (30). The two second gears (30) respectively drive two propellers on the first lifting arm (9). Fifth bearings (27) are respectively arranged near both ends of the first transmission shaft (28).

5. The tilt-rotating composite wing unmanned manned aircraft according to claim 4, characterized in that: A notch (13) is provided in the middle of the rotating head (8), and the notch (13) is used for the operation of the propeller shaft (39). A conversion box (14) is provided on the first motor (16). A hanging ear (17) is sleeved between the first motor (16) and the housing (11), and a seat plate (18) is provided on the first motor (16); A fourth motor (19) is provided on both sides of the fuselage, and the fourth motor (19) is used to drive the landing gear (10) to be retracted or extended. The motor shaft of the fourth motor (19) is sleeved with the transverse shaft at the upper end of the landing gear (10). The rotating head (8) is provided with a third transmission shaft (31) and a third gear (29). The transmission shafts outside the third transmission shaft (31) and the third gear (29) are both provided with a first shaft seat (15). The motor shaft of the fourth motor (19) is sleeved with a second shaft seat (20). The landing gear (10) and the housing (11) are connected via a linkage shaft (21). The fourth motor (19) is mounted on an outer end of the landing gear (10); the second shaft seat (20) is arranged at the root of both ends of the landing gear (10); the third shaft seat (22) is sleeved on the seat plate (18); the first transmission shaft (28) and the third shaft seat (22) are sleeved; the third gear (29) is sleeved on the first transmission shaft (28); the fourth gear (26) is sleeved on the fifth bearing (27); and the third gear (29) and the two second gears (30) are sleeved.

6. The tilt-rotating composite wing unmanned manned aircraft according to claim 5, characterized in that: The tail of the fuselage is provided with five rocker arms (55), and a total of ten rudders (53) are provided, five of which are arranged on the upper surface of the fuselage, and five of which are arranged on the lower surface of the fuselage. The upper and lower rudders (53) share a common axis, and the ten rudders (53) are arranged in linkage. The tail of the fuselage is provided with a fifth motor (58), the fifth motor (58) drives ten rudders (53), one end of the rocker arm (55) is locked and sleeved with a vertical shaft (54), the other end of the rocker arm (55) is rotatably sleeved with a vertical shaft at the lower edge of the rudder (53), the vertical shaft (54) is arranged at the rear tail of the aircraft, the vertical shaft (54) passes through the tail of the fuselage up and down, the upper and lower ends of the vertical shaft (54) are sleeved with a seventh bearing, the seventh bearing and the machine The body is sleeved, a connecting rod (56) is provided between the rocking arm (55), the connecting rod (56) is a linkage pull rod, one end of the connecting rod (56) and the rocking arm (55) are sleeved, a cam (57) is provided on the body, one end of the cam (57) is mounted on the fifth motor (58), and the other end of the cam (57) is mounted on the vertical axis of the connecting rod (56), and the cam (57) drives the upper and lower coaxial rudders (53) to rotate through the connecting rod (56).

7. The tilt-rotating composite wing unmanned manned aircraft according to claim 6, characterized in that: The fuselage further comprises a front windshield (2), a cabin door (5), a skylight (3), and a rear window (4); The outer shell (11) is provided with a shell bottom (60), the fuselage is provided with a floor (61), a battery area (62) is provided on the floor (61), and a groove (59) is provided at a position corresponding to the landing gear (10) on the outer shell (11).

8. The tilt-rotating composite wing unmanned manned aircraft according to claim 4, characterized in that: The fuselage further comprises a main shaft (105) and a sixth motor (108). The end of the main shaft (105) is sleeved with a gear ring (100). The main shaft (105) is meshed with a bevel gear (107). The sixth motor (108) drives the main shaft (105) to rotate. Two sixth bearings (106) are sleeved on the main shaft (105). The sixth bearings (106) are arranged near the outer edge of the outer shell (11). The main shaft (105) is arranged at the root of the wing (52). The main shaft (105) and the fuselage are connected to each other. The wing (52) is an integral part, the sixth motor (108) is sleeved on a seat plate (18) inside the outer shell (11), a seventh motor (102) is arranged in the fuselage, the first transmission shaft (28) and the seventh motor (102) are connected via a joint (103), a first shaft sleeve (101) is arranged on the sixth bearing (106), two groups of eighth motors (120) are arranged on the wing (52), the two groups of the eighth motors (120) are coaxial, and four propellers are arranged on the wing (52).

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