Aircraft

Abstract

The invention discloses an aircraft, and belongs to the technical field of aerospace, the aircraft comprises a fuselage, the tail of the fuselage is provided with an empennage, the two sides of the fuselage are provided with wings, the wings are provided with rotors, the orientation of the rotors is the same as the orientation of front flanges of the wings, the wings can rotate around deflection shafts, and the wings have unfolding positions and folding positions in the rotation process; when the wings are in the unfolding position, the wings are in a horizontal state, the front flanges of the wings and the nose of the fuselage face the same direction, and the wing surfaces of the wings are parallel to the longitudinal axis of the fuselage; when the wings are in the folding position, the wings are in a vertical state, the front flanges of the wings face upwards, and the wing surfaces of the wings are perpendicular to the longitudinal axis of the fuselage. The wings are switched between the horizontal state and the vertical state, so that the aircraft can be in a multi-rotor-wing form and a fixed-wing form and can be switched, the aircraft has two flight modes of the multi-rotor wing and the fixed wing, and the advantages of the multi-rotor-wing aircraft and the advantages of the fixed-wing aircraft are integrated.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and particularly to an aircraft. Background Art

[0002] UAVs are mainly divided into rotor UAVs and fixed-wing UAVs. The former has a small footprint and flexible flight modes, and can take off and land vertically and hover, but has a slow flight speed and a short range. Fixed-wing UAVs have a fast flight speed and a long range, but the fixed wing has a large footprint and requires a large takeoff distance, and cannot achieve vertical takeoff and landing and hovering, so the convenience and flexible practicality are lacking. Therefore, there is an urgent need for an aircraft that can combine the advantages of both. Summary of the Invention

[0003] The purpose of the present invention is to solve the above technical problems and provide an aircraft whose wings can be switched between a horizontal state and a vertical state, so that the aircraft has two forms of a multi-rotor form and a fixed-wing form and can be switched, thus combining the advantages of both multi-rotor and fixed-wing flight modes and integrating the advantages of multi-rotor aircraft and fixed-wing aircraft.

[0004] To achieve the above purpose, the present invention provides the following solution: The present invention discloses an aircraft, including a fuselage, a tail wing is provided at the tail of the fuselage, wings are provided on both sides of the fuselage, rotors are provided on the wings, the orientation of the rotors is the same as the orientation of the leading edge of the wings, the wings can rotate around a deflection axis, and the wings have an unfolded position and a folded position during the rotation process; when the wings are in the unfolded position, the wings are in a horizontal state, the leading edge of the wings is in the same orientation as the nose of the fuselage, and the wing surface of the wings is parallel to the longitudinal axis of the fuselage; when the wings are in the folded position, the wings are in a vertical state, the leading edge of the wings faces upward, and the wing surface of the wings is perpendicular to the longitudinal axis of the fuselage.

[0005] Preferably, the deflection axis is inclined towards the fuselage, the deflection axis has a first included angle with the plane common to the length and width directions of the wings, the deflection axis has a second included angle with the plane common to the width and thickness directions of the wings, the deflection axis has a third included angle with the plane common to the length and thickness directions of the wings, the deflection axis has a fourth included angle with the plane common to the transverse axis and the longitudinal axis of the fuselage, the deflection axis has a fifth included angle with the plane common to the longitudinal axis and the vertical axis of the fuselage, the deflection axis has a sixth included angle with the plane common to the transverse axis and the vertical axis of the fuselage, the first included angle is the same as the fourth included angle, the second included angle is the same as the fifth included angle, and the third included angle is the same as the sixth included angle.

[0006] Preferably, the rotors are spaced along the length direction of the wings, and at least two of the rotors are respectively close to the wing root and the wing tip of the wings.

[0007] Preferably, the fuselage and the wing are rotatably connected through a rotating mechanism. The rotating mechanism includes a first connecting rod, a second connecting rod, and the deflection shaft. One end of the first connecting rod is fixedly connected to the wing, the other end of the first connecting rod is hinged to the deflection shaft, one end of the second connecting rod is fixedly connected to the fuselage, and the other end of the second connecting rod is hinged to the deflection shaft.

[0008] Preferably, the deflection shaft is biased towards the nose of the fuselage and is close to the wing root of the wing.

[0009] Preferably, an embedding groove is provided on the upper wing surface of the wing, and an embedding block is provided on the side of the fuselage. The shape of the embedding block matches that of the embedding groove. The first connecting rod and the deflection shaft are located in the embedding groove. A first mounting hole for inserting and fixing the first connecting rod is provided on the embedding groove, and a second mounting hole for inserting and fixing the second connecting rod is provided on the embedding block. The embedding block can be embedded into the embedding groove when the wing rotates to the deployment position. After the embedding block is embedded into the embedding groove, the embedding block can be smoothly transitioned with the upper wing surface of the wing.

[0010] Preferably, a driving mechanism for driving the wing to rotate is further included.

[0011] Preferably, the driving mechanism includes a rotating motor, a ball screw, an auxiliary guide rail, a driving block, and a driving rod. The ball screw and the auxiliary guide rail are arranged side by side on the fuselage. The axis of the ball screw and the extending direction of the auxiliary guide rail are both parallel to the longitudinal axis of the fuselage. The driving block is threadedly connected to the ball screw through a slider. The slider is slidably connected to the auxiliary guide rail. One end of the driving rod is ball-jointed to the slider, and the other end of the driving rod is ball-jointed to the rear wing edge of the wing root of the wing. The ball screw is driven to rotate by the rotating motor.

[0012] Preferably, the driving mechanism is installed inside the fuselage. Strip-shaped guide openings for the ends of the driving block and the driving rod to be hinged are provided on both sides of the fuselage. The strip-shaped guide openings extend along the transverse axis direction of the fuselage.

[0013] Preferably, the fuselage is streamlined.

[0014] The present invention has achieved the following technical effects compared with the prior art:

[0015] In the aircraft of the present invention, the wing and the fuselage are rotationally connected, and the wing can rotate around a deflection axis so that the wing can switch between a horizontal state and a vertical state, enabling the aircraft to switch between a multi-rotor configuration and a fixed-wing configuration, having both a multi-rotor flight mode and a fixed-wing flight mode, thus combining the advantages of both multi-rotor aircraft and fixed-wing aircraft. The setting method of this aircraft can be adopted for both unmanned aircraft and piloted aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0017] Figure 1 Schematic perspective view of the aircraft (wing folded state) in the embodiment;

[0018] Figure 2 Schematic perspective view of the aircraft (wing transition state) in the embodiment;

[0019] Figure 3 Schematic perspective view of the aircraft (wing deployed state) in the embodiment;

[0020] Figure 4 Schematic structural view of the rotating mechanism in the embodiment;

[0021] Figure 5 Exploded structural view of the rotating mechanism in the embodiment;

[0022] Figure 6 Schematic structural view of the driving mechanism in the embodiment;

[0023] Figure 7 Partial enlarged schematic view of the driving mechanism in the embodiment;

[0024] Figure 8 Schematic structural view of the fuselage at the strip-shaped guide opening in the embodiment;

[0025] Figure 9 Schematic view of the positional relationship between the driving mechanism and the fuselage in the embodiment;

[0026] Figure 10 Schematic side view of the aircraft (wing folded state) in the embodiment;

[0027] Figure 11 Schematic front view of the aircraft (wing folded state) in the embodiment;

[0028] Figure 12 It is a top - view structural schematic diagram of the aircraft (wing - folded state) in the embodiment;

[0029] Figure 13 It is a top - view structural schematic diagram of the aircraft (wing - deployed state) in the embodiment.

[0030] Explanation of the reference numerals in the drawings:

[0031] 1, fuselage; 2, tail wing; 3, wing; 4, rotor; 5, rotating mechanism; 6, driving mechanism;

[0032] 11, embedded block; 12, strip - shaped guide opening;

[0033] 21, tail - wing aileron;

[0034] 31, embedded groove; 32, wing aileron;

[0035] 41, power cabin;

[0036] 51, first connecting rod; 52, second connecting rod; 53, deflection shaft; 54, single - ear hinge; 55, double - ear hinge; 56, nut; 57, brass bushing;

[0037] 61, rotating motor; 62, ball screw; 63, auxiliary guide rail; 64, driving block; 65, driving rod; 66, ball joint; 67, mounting bracket; 68, travel switch. Detailed implementation manners

[0038] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0039] The purpose of the present invention is to provide an aircraft to solve the problems existing in the prior art. The wing and the fuselage are in a rotational connection relationship, and the wing can rotate around a deflection shaft so that the wing can be switched between a horizontal state and a vertical state, enabling the aircraft to switch between a multi - rotor form and a fixed - wing form, having both a multi - rotor flight mode and a fixed - wing flight mode, thus combining the advantages of both.

[0040] To make the above - mentioned objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below in conjunction with the drawings and specific implementation manners.

[0041] This embodiment provides an aircraft, as Figures 1 to 13The aircraft can be a drone or a manned aircraft, and includes a fuselage 1, a tail 2 is provided at the rear of the fuselage 1, and wings 3 are provided on both sides of the fuselage 1. Rotors 4 are provided on the wings 3, and the direction of the rotors 4 is the same as the direction of the front edge of the wings 3. The wings 3 can rotate around the deflection axis 53, and the wings 3 have an unfolded position and a folded position during the rotation process.

[0042] like Figure 3 and Figure 13 As shown, when the wing 3 is in the deployed position, the wing 3 is in a horizontal state, the front edge of the wing 3 is in the same direction as the nose of the fuselage 1, and the wing surface of the wing 3 is parallel to the longitudinal axis of the fuselage 1. At this time, the aircraft is in the form of a fixed-wing aircraft, flies in a fixed-wing aircraft manner, has the flight characteristics of a fixed-wing aircraft, and can be used for various tasks requiring fast flight speed and long range, such as cruising.

[0043] like Figure 1 , Figure 10 , Figure 11 and Figure 12 As shown, when the wing 3 is in the folded position, the wing 3 is in a vertical state, the front edge of the wing 3 faces upward, and the wing surface of the wing 3 is perpendicular to the longitudinal axis of the fuselage 1. At this time, the aircraft is in the form of a multi-rotor aircraft, flies in a multi-rotor aircraft mode, has the flight characteristics of a multi-rotor aircraft, can be used for take-off, landing, hovering of the aircraft, and some situations where it is necessary to fly in a rotor flight mode, the flight is convenient and flexible, and the floor space can be reduced after the aircraft is stopped.

[0044] like Figure 2 As shown, it is the transition position in the process of switching between the unfolded position and the folded position of the aircraft, which is mainly the transition form generated in the process of switching back and forth between the multi-rotor form and the fixed-wing form. It should be noted that if the form is switched in the air, the aircraft needs to have a certain forward flight speed before switching to ensure that the aircraft switches smoothly in the air. And as a preference, when the aircraft has a certain forward flight speed, during the form switching process, the rotor 4 can be stopped, and the aircraft relies on inertia to fly forward to avoid disturbance caused by the change in the direction of the rotor 4 when the wing 3 rotates, affecting the stability of the aircraft during the deformation process. Of course, whether the rotor 4 stops during the deformation process can be determined according to actual needs.

[0045] In one embodiment, if Figures 1 to 13As shown, the deflection axis 53 is inclined towards the fuselage 1. The deflection axis 53 has a first included angle with the coplanar plane of the length and width directions of the wing 3, a second included angle with the coplanar plane of the width and thickness directions of the wing 3, and a third included angle with the coplanar plane of the length and thickness directions of the wing 3. The length of the wing 3 refers to the distance from the wing root to the wing tip, and the width of the wing 3 refers to the distance between the leading edge and the trailing edge. The deflection axis 53 has a fourth included angle with the coplanar plane of the transverse axis and the longitudinal axis of the fuselage 1, a fifth included angle with the coplanar plane of the longitudinal axis and the vertical axis of the fuselage 1, and a sixth included angle with the coplanar plane of the transverse axis and the vertical axis of the fuselage 1. The first included angle is the same as the fourth included angle, the second included angle is the same as the fifth included angle, and the third included angle is the same as the sixth included angle. To ensure that when the wing 3 revolves around the deflection axis 53, it can be switched from the horizontal state to the vertical state, or from the vertical state to the horizontal state. As a preferred value, the first included angle, the second included angle, and the third included angle can be 45°, and of course, they can be adjusted according to the actual situation.

[0046] In one embodiment, as Figures 1 to 13 shown, the rotors 4 are arranged at intervals along the length direction of the wing 3. The number of rotors 4 on each wing 3 is at least two, and at least two of the rotors 4 are respectively close to the wing root and the wing tip of the wing 3. For example, two rotors 4, three rotors 4, or more than three rotors 4 are arranged on each wing 3. The positions of the rotors 4 on the left and right wings 3 are arranged correspondingly. If considering from the cost, it is preferred to arrange two rotors 4 on each wing 3, that is, there are a total of four rotors 4. When the aircraft is in the multi-rotor configuration, by controlling the rotational speeds of the respective rotors 4, complex and flexible flight modes such as forward flight, backward flight, left flight, and right flight of the aircraft can be achieved, achieving a flexible effect that cannot be achieved in the fixed-wing state.

[0047] In one embodiment, as Figures 1 to 13 shown, only one rotor 4 is arranged on each of the left and right wings 3, and the angle of the rotor 4 is variable to change the orientation of the rotor 4. Then, relying on the two rotors 4, complex and flexible flight modes such as forward flight, backward flight, left flight, and right flight can also be achieved. Of course, the flight stability of this mode is worse than that of the mode with more than four rotors 4, and it can be selected whether to set it like this according to the actual needs.

[0048] In one embodiment, as Figures 1 to 13As shown, the blades of the rotor 4 can be folded and unfolded. When the aircraft flies to a certain altitude and has sufficient forward flight speed, during the transition from the multi-rotor configuration to the fixed-wing configuration, the blades of the rotor 4 can be folded to reduce the resistance brought by the air flow, ensure the stability of the aircraft during the transition, and after the transition is completed, the blades of the rotor 4 are unfolded and work again. The way of folding and unfolding the blades of the rotor 4 adopts the current conventional technical methods and will not be elaborated here. Of course, during the transition process, whether folding is specifically required is considered according to the actual situation.

[0049] In one embodiment, as Figures 1 to 13 shown, the fuselage 1 and the wing 3 are rotatably connected by a rotating mechanism 5. The rotating mechanism 5 includes a first connecting rod 51, a second connecting rod 52, and a deflection shaft 53. One end of the first connecting rod 51 is fixedly connected to the wing 3, the other end of the first connecting rod 51 is hinged to the deflection shaft 53, one end of the second connecting rod 52 is fixedly connected to the fuselage 1, and the other end of the second connecting rod 52 is hinged to the deflection shaft 53, so as to realize the rotation of the wing 3 around the deflection shaft 53.

[0050] In one embodiment, as Figures 1 to 13 shown, the end of the first connecting rod 51 hinged to the deflection shaft 53 is provided with a single hinge ear 54, and the end of the second connecting rod 52 hinged to the deflection shaft 53 is provided with a double hinge ear 55. Using a bolt as the deflection shaft 53, after inserting the single hinge ear 54 into the two ear plates of the double hinge ear 55, align the ear plate holes of the single hinge ear 54 and the ear plate holes of the double hinge ear 55, and then insert the deflection shaft 53 into the ear plate holes of the single hinge ear 54 and the double hinge ear 55, and tighten the nut 56 on the deflection shaft 53 to complete the hinging of the first connecting rod 51 and the second connecting rod 52 to the deflection shaft 53. In order to reduce the friction between the ear plate hole and the deflection shaft 53, a brass bushing 57 can be sleeved on the deflection shaft 53 to reduce friction.

[0051] In one embodiment, as Figures 1 to 13 shown, the deflection shaft 53 is biased towards the nose of the fuselage 1 and is close to the wing root of the wing 3. This setting method enables the wing 3 to be rotated upward when switching from the fixed-wing configuration to the multi-rotor configuration, and enables the wing 3 to be rotated downward when switching from the multi-rotor configuration to the fixed-wing configuration.

[0052] In one embodiment, as Figures 1 to 13As shown in the figure, an embedding groove 31 is provided on the upper wing surface of the wing 3, and an embedding block 11 is provided on the side of the fuselage 1. The shape of the embedding block 11 matches that of the embedding groove 31. The first connecting rod 51 and the deflection shaft 53 are located in the embedding groove 31. A first mounting hole is provided on the embedding groove 31 for the first connecting rod 51 to be inserted and fixed. The fixing can be achieved by welding, gluing or other connection methods. A second mounting hole is provided on the embedding block 11 for the second connecting rod 52 to be inserted and fixed. The fixing can be achieved by welding, gluing or other connection methods. The embedding block 11 can be embedded into the embedding groove 31 when the wing 3 rotates towards the deployment position. After the embedding block 11 is embedded into the embedding groove 31, the embedding block 11 can be smoothly transitioned with the upper wing surface of the wing 3.

[0053] In one embodiment, as Figures 1 to 13 shown, the deflection shaft 53 can also be biased towards the tail of the fuselage 1, and at the same time, the deflection shaft 53 is close to the wing root of the wing 3. With this setting method, when the wing 3 switches from the fixed-wing form to the multi-rotor form, the wing 3 can be rotated downward. When the wing 3 switches from the multi-rotor form to the fixed-wing form, the wing 3 can be rotated upward. At this time, the embedding groove 31 needs to be provided on the lower wing surface of the wing 3. After the embedding block 11 is embedded into the embedding groove 31, the embedding block 11 can be smoothly transitioned with the lower wing surface of the wing 3.

[0054] In one embodiment, as Figures 1 to 13 shown, the aircraft further includes a driving mechanism 6 for driving the wing 3 to rotate.

[0055] In one embodiment, as Figures 1 to 13 shown, the driving mechanism 6 includes a rotating motor 61, a ball screw 62, an auxiliary guide rail 63, a driving block 64 and a driving rod 65. The ball screw 62 and the auxiliary guide rail 63 are arranged side by side on the fuselage 1. The axis of the ball screw 62 and the extending direction of the auxiliary guide rail 63 are both parallel to the longitudinal axis of the fuselage 1. The driving block 64 is threadedly connected to the ball screw 62 through a slider, and the slider is slidably connected to the auxiliary guide rail 63. One end of the driving rod 65 is connected to the slider through a ball hinge 66, and the other end of the driving rod 65 is connected to the rear wing edge of the wing root of the wing 3 through a ball hinge 66. The ball screw 62 is driven to rotate by the rotating motor 61. The rotating motor 61 drives the ball screw 62 to rotate. Under the action of the thread, the slider drives the driving block 64 to move along the axial direction of the ball screw 62. The driving block 64 will then push and pull the driving rod 65, thereby driving the left and right wings 3 to rotate around their respective deflection shafts 53, realizing the switching of the wing 3 between the deployment position and the folding position, and completing the switching of the fixed-wing form and the multi-rotor form of the aircraft. Specifically, the number of the auxiliary guide rails 63 is not limited. Preferably, one auxiliary guide rail 63 can be provided on each side of the ball screw 62. Two driving rods 65 are provided at both ends of the driving block 64 respectively to drive the left and right wings 3 respectively.

[0056] In one embodiment, asFigures 1 to 13 As shown in the figure, the driving mechanism 6 is installed inside the fuselage 1. Compared with being installed outside the fuselage 1, it can reduce air resistance and the impact force on the driving mechanism 6 itself during high-speed flight. Strip-shaped guide openings 12 are provided on both sides of the fuselage 1. The strip-shaped guide openings 12 extend along the transverse axis direction of the fuselage 1. The end of the driving block 64 hinged to the driving rod 65 will extend out through the strip-shaped guide opening 12. When the driving block 64 moves, it will move along the extension direction of the strip-shaped guide opening 12.

[0057] In one embodiment, as Figures 1 to 13 shown, the ball screw 62 and the auxiliary guide rail 63 are installed inside the fuselage 1 through the mounting bracket 67, realizing the fixed relationship between the auxiliary guide rail 63 and the fuselage 1 and the rotational relationship between the ball screw 62 and the fuselage 1.

[0058] In one embodiment, as Figures 1 to 13 shown, there are at least two mounting brackets 67. One mounting bracket 67 is close to the tail of the fuselage 1, and the other mounting bracket 67 is close to the rotating motor 61 and is located between the rotating motor 61 and the driving block 64. A travel switch 68 is installed on this mounting bracket 67. The initial position of the rotating motor 61 can be calibrated through the travel switch 68, and the rotating motor 61 is controlled to drive the ball screw 52 with the initial position as the 0 point.

[0059] In one embodiment, as Figures 1 to 13 shown, the fuselage 1 is streamlined.

[0060] In one embodiment, as Figures 1 to 13 shown, a tail wing aileron 21 is provided on the tail wing 2.

[0061] In one embodiment, as Figures 1 to 13 shown, a wing aileron 32 is provided on the wing 3.

[0062] In one embodiment, as Figures 1 to 13 shown, the rotor 4 is installed on the wing 3 through the power cabin 41.

[0063] In one embodiment, as Figures 1 to 13 shown, a driving motor and a power battery are installed in the power cabin 41. The power battery provides power for the driving motor, and the driving motor drives the rotor 4 to rotate.

[0064] In one embodiment, as Figures 1 to 13 shown, the driving motor and the rotating motor can adopt a three-axis servo motor, which has the characteristics of high reliability, high stability and light weight.

[0065] In one embodiment, as Figures 1 to 13 shown, this aircraft has the following advantages:

[0066] First point: Currently, the flight time of multi-rotor drones is relatively short, mostly ranging from 3 minutes to 40 minutes, and there are problems of relatively large size and dead weight. Dead weight refers to the part of the weight that only plays a role during takeoff and landing and has no effect after level flight. Dead weight will occupy the payload of the drone. This aircraft realizes vertical takeoff, landing, and level flight by changing the wing angle. All attitudes share a set of power, and the dead weight is relatively small.

[0067] Second point: When parked on the ground, the wings can be switched to the folded state for storage, occupying less storage space, and more aircraft can be placed side by side.

[0068] Third point: The power batteries are distributed in the power compartment, which can relatively ideally balance the center of gravity of the aircraft in various attitudes.

[0069] In the present invention, specific examples are used to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. An aircraft, characterized in that: The invention comprises a fuselage, wherein a tail wing is arranged at the tail of the fuselage, wings are arranged on both sides of the fuselage, rotors are arranged on the wings, the direction of the rotors is the same as the direction of the front edge of the wing, the wing can rotate around a deflection axis, and the wing has an unfolded position and a folded position during the rotation process; when the wing is in the unfolded position, the wing is in a horizontal state, the front edge of the wing is in the same direction as the nose of the fuselage, and the wing surface of the wing is parallel to the longitudinal axis of the fuselage; when the wing is in the folded position, the wing is in a vertical state, the front edge of the wing is facing upwards, and the wing surface of the wing is perpendicular to the longitudinal axis of the fuselage.

2. The aircraft according to claim 1, characterized in that The deflection axis is tilted toward the fuselage, the deflection axis has a first angle when being coplanar with the length and width directions of the wing, the deflection axis has a second angle when being coplanar with the width and thickness directions of the wing, the deflection axis has a third angle when being coplanar with the length and thickness directions of the wing, the deflection axis has a fourth angle when being coplanar with the transverse axis and the longitudinal axis of the fuselage, the deflection axis has a fifth angle when being coplanar with the longitudinal axis and the vertical axis of the fuselage, the deflection axis has a sixth angle when being coplanar with the transverse axis and the vertical axis of the fuselage, the first angle is the same as the fourth angle, the second angle is the same as the fifth angle, and the third angle is the same as the sixth angle.

3. The aircraft according to claim 2, characterized in that: The rotors are spaced apart along the length direction of the wing, and at least two of the rotors are respectively close to the wing root and the wing tip of the wing.

4. The aircraft according to claim 2 or 3, characterized in that The fuselage and the wing are rotatably connected via a rotating mechanism, which includes a first connecting rod, a second connecting rod and the deflection axis, one end of the first connecting rod is fixedly connected to the wing, the other end of the first connecting rod is hinged to the deflection axis, one end of the second connecting rod is fixedly connected to the fuselage, and the other end of the second connecting rod is hinged to the deflection axis.

5. The aircraft according to claim 4, characterized in that The yaw axis is biased toward the nose of the fuselage, and the yaw axis is close to the root of the wing.

6. The aircraft according to claim 5, characterized in that The upper wing surface of the wing is provided with an embedding groove, and the side of the fuselage is provided with an embedding block, the embedding block matches the shape of the embedding groove, the first connecting rod and the deflection shaft are located in the embedding groove, the embedding groove is provided with a first mounting hole for the first connecting rod to be inserted and fixed, and the embedding block is provided with a second mounting hole for the second connecting rod to be inserted and fixed, the embedding block can be embedded in the embedding groove when the wing rotates to the deployed position, and after the embedding block is embedded in the embedding groove, the embedding block can smoothly transition with the upper wing surface of the wing.

7. The aircraft according to claim 6, characterized in that It also includes a driving mechanism for driving the wing to rotate.

8. The aircraft according to claim 7, characterized in that The driving mechanism includes a rotating motor, a ball screw, an auxiliary guide rail, a driving block and a driving rod. The ball screw and the auxiliary guide rail are installed side by side on the fuselage. The axis of the ball screw and the extension direction of the auxiliary guide rail are parallel to the longitudinal axis of the fuselage. The driving block is threadedly connected to the ball screw through a slider. The slider is slidably connected to the auxiliary guide rail. One end of the driving rod is connected to the slider through a ball joint, and the other end of the driving rod is connected to the rear edge of the wing root of the wing through a ball joint. The ball screw is driven to rotate by the rotating motor.

9. The aircraft according to claim 8, characterized in that The driving mechanism is installed in the fuselage. Both sides of the fuselage are provided with strip guide openings for the ends of the driving block hinged with the driving rod to extend out. The strip guide openings extend along the horizontal axis direction of the fuselage.

10. The aircraft according to claim 1, characterized in that: The fuselage is streamlined.

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