Sweepforward wing variable-configuration unmanned aerial vehicle and configuration changing method thereof

Abstract

The invention discloses a forward-swept-wing variable-configuration unmanned aerial vehicle and a configuration changing method thereof, and relates to the technical field of aircrafts, the forward-swept-wing variable-configuration unmanned aerial vehicle comprises a fuselage, two wings are symmetrically arranged on two sides of the fuselage, and the two wings and the fuselage form a forward-swept-wing configuration; the wings can horizontally rotate around the connecting positions of the wings and the fuselage so as to change the size of a sweepforward angle; the rotor wing is arranged at the wingtip position of the wing, and the rotor wing can rotate around the axis of the wing where the rotor wing is located; and the two vertical empennages are symmetrically arranged above the tail part of the fuselage. According to the forward-swept wing variable-configuration unmanned aerial vehicle and the configuration changing method thereof, it is guaranteed that the unmanned aerial vehicle can have good stability and aerodynamic performance under different flight working conditions.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a forward-swept-wing variable-configuration unmanned aircraft and a configuration change method thereof. Background Art

[0002] In the aircraft sector, traditional fixed-wing aircraft have a fixed aerodynamic shape, making it difficult to maintain optimal performance across diverse flight conditions. For example, takeoff and landing require high lift and low speed, while cruising requires an efficient aerodynamic layout to reduce drag and improve fuel efficiency. Fixed-wing aircraft are unable to simultaneously meet these diverse requirements, limiting their application and performance.

[0003] To address these issues, morphing aircraft have emerged. These aircraft can adapt to different flight conditions by changing their aerodynamic shape, thereby balancing multiple performance aspects and improving overall flight capabilities. For example, fixed-wing drones with vertical take-off and landing capabilities combine the performance advantages of rotary-wing drones and conventional fixed-wing drones. Their traditional wing structure allows them to take off and land without being restricted by landing and take-off areas, enabling them to hover in the air. They also possess the characteristics of fixed-wing drones, such as relatively high cruising speeds and ranges. To achieve vertical take-off and landing, fixed-wing aircraft can employ various designs, including hybrid wings and tilt-rotor aircraft. Tilt-rotor aircraft, among others, combine the advantages of both fixed-wing and rotary-wing aircraft, capable of hovering and vertical take-off and landing, while also offering high-speed, long-range flight. However, current tilt-rotor aircraft still face flight control challenges. Switching between vertical take-off and landing modes can lead to instability and a continuous drop in altitude, making it difficult to ensure stable and aerodynamic performance across various flight conditions.

[0004] Therefore, it is urgent to design a technical solution that can ensure good stability and aerodynamic performance under different flight conditions. Summary of the Invention

[0005] The purpose of the present invention is to provide a forward-swept wing variable configuration unmanned aerial vehicle and a configuration change method thereof, so as to solve the problems existing in the above-mentioned prior art and ensure that it can have good stability and aerodynamic performance under different flight conditions.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] The present invention provides a forward-swept wing variable configuration unmanned aerial vehicle, comprising:

[0008] body;

[0009] Wings, wherein the two wings are symmetrically arranged on both sides of the fuselage, and the two wings and the fuselage form a forward-swept wing configuration; the wings can rotate horizontally around the connection position between them and the fuselage to change the magnitude of the forward sweep angle;

[0010] a rotor, disposed at the wingtip of the wing, and capable of rotating around the axis of the wing;

[0011] Two vertical tail fins are symmetrically arranged above the tail of the fuselage.

[0012] Preferably, it also includes canards, two of which are symmetrically arranged on both sides of the fuselage, and the canards are located between the head and wings of the fuselage.

[0013] Preferably, a wingtip tilt module is movably provided at one end of the wing away from the fuselage, the main shaft of the rotor is connected to the wingtip tilt module, and the wing has a built-in tilt power device that can drive the wingtip tilt module to rotate around the axis of the wing.

[0014] Preferably, the wing includes a transition wing and a deformable wing, the transition wing is fixedly connected to the outside of the fuselage, the wing root of the deformable wing is hinged to the wingtip of the transition wing, and a wingspan drive device is provided in the transition wing, and the wingspan drive device can control the deformable wing to rotate horizontally around the hinge point between it and the transition wing to change the forward sweep angle of the wing; the rotor is arranged at the wingtip position of the deformable wing.

[0015] Preferably, during the vertical take-off and landing process of the forward-swept-wing variable-configuration unmanned aerial vehicle, the rotor rotates until the main axis of the rotor is arranged vertically, and the wing rotates until the forward sweep angle is greater than zero, at which time a vertical take-off and landing configuration is formed.

[0016] Preferably, during the cruising process of the forward-swept-wing variable-configuration unmanned aerial vehicle, the forward sweep angle value of the wing is reduced to a value smaller than the forward sweep angle value during the vertical take-off and landing configuration; the rotor rotates until the main axis of the rotor is arranged horizontally, at which time a cruising configuration is formed.

[0017] Preferably, during the maneuvering and circling process of the forward-swept-wing variable-configuration unmanned aerial vehicle, the forward sweep angle value of the wing becomes the initial value, and the forward sweep angle value in the vertical take-off and landing configuration is the initial value; the main axis of the rotor is arranged horizontally, and a maneuvering and circling configuration is formed at this time.

[0018] Preferably, a locking mechanism is provided at the wingtip of the wing, which can lock the main shaft of the rotor to a set angle position relative to the wing.

[0019] Preferably, the wingtip tilt module includes a crank slider mechanism, which is arranged on the wing, and one end of the crank slider mechanism is connected to the main shaft of the rotor, and the other end is connected to an actuator.

[0020] The present invention further provides a method for changing the configuration of the forward-swept wing variable-configuration unmanned aerial vehicle, comprising the following steps:

[0021] During vertical takeoff and landing, the rotor tilts 90 degrees from its initial state and maintains the tilted state;

[0022] After reaching the specified height, the rotor tilts in the opposite direction and returns to the initial position;

[0023] In the low-speed cruising state, the wings rotate horizontally backward to reduce the wing sweep angle and increase the wing aspect ratio;

[0024] When a forward-swept-wing variable-configuration unmanned aerial vehicle is hovering, circling, or tilting its rotor, the wings rotate forward to return to the initial forward sweep angle state.

[0025] Compared with the prior art, the present invention has achieved the following technical effects:

[0026] The forward-swept wing variable configuration unmanned aerial vehicle (UAV) of the present invention utilizes a basic structure with forward-swept wings and no horizontal tail. The forward-swept wings offer excellent low-speed cruising performance and maneuverability, enabling the aircraft to achieve long-range, hovering, and other requirements. Furthermore, the forward-swept wing configuration helps position the aircraft's center of gravity forward, thereby increasing stability during rotor tilt and maneuvering. The vertical tail generates no aerodynamic loads during vertical takeoff and landing (VTOL). Compared to the conventional twin-tilt rotor VTOL wing configurations of prior art, the present invention adopts a design without a horizontal tail, further reducing drag and improving aerodynamic efficiency.

[0027] The present invention's method for changing the configuration of a forward-swept wing variable-configuration unmanned aerial vehicle (UAV) can adapt to different flight phases and mission requirements. During takeoff and landing, rotor tilt is achieved while adjusting the relative position of the center of gravity and aerodynamic center to improve stability. During cruise, the forward sweep angle is reduced to optimize aerodynamic performance and conserve fuel. This multi-mode wing structure optimizes lift-to-drag ratio, improves fuel efficiency, extends flight range, or increases payload capacity. It overcomes the shortcomings of existing folding wingtip mechanisms, improving the adaptability, performance, and safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 A schematic structural diagram of a forward-swept wing variable configuration unmanned aerial vehicle in one or some embodiments of the present invention;

[0030] Figure 2 A front view of a forward-swept-wing variable-configuration unmanned aerial vehicle during vertical takeoff and landing in one or some embodiments of the present invention;

[0031] Figure 3 A top view of a forward-swept-wing variable-configuration unmanned aerial vehicle during vertical takeoff and landing in one or some embodiments of the present invention;

[0032] Figure 4 A side view of a forward-swept-wing variable-configuration unmanned aerial vehicle during vertical takeoff and landing in one or some embodiments of the present invention;

[0033] Figure 5 A front view of a forward-swept-wing variable-configuration unmanned aerial vehicle during cruising in one or some embodiments of the present invention;

[0034] Figure 6 A top view of a forward-swept-wing variable-configuration unmanned aerial vehicle cruising in one or some embodiments of the present invention;

[0035] Figure 7 A side view of a forward-swept wing variable configuration unmanned aerial vehicle during cruising in one or some embodiments of the present invention;

[0036] Figure 8 A front view of a forward-swept-wing variable-configuration unmanned aerial vehicle in hovering according to one or some embodiments of the present invention;

[0037] Figure 9 A top view of a forward-swept-wing variable-configuration unmanned aerial vehicle in hovering according to one or some embodiments of the present invention;

[0038] Figure 10 A side view of a forward-swept-wing variable-configuration unmanned aerial vehicle in hovering according to one or some embodiments of the present invention;

[0039] Figure 11 A schematic diagram of a state of a forward-swept wing variable configuration unmanned aerial vehicle in hovering according to one or some embodiments of the present invention;

[0040] Figure 12 A schematic diagram of a forward-swept-wing variable-configuration unmanned aerial vehicle during vertical takeoff and landing in one or some embodiments of the present invention;

[0041] Figure 13 A schematic diagram of a cruising state of a forward-swept wing variable configuration unmanned aerial vehicle in one or some embodiments of the present invention;

[0042] Figure 14 Schematic diagram of a forward-swept-wing variable-configuration unmanned aerial vehicle hovering from another angle in one or some embodiments of the present invention.

[0043] In the figure: 1-fuselage, 2-wing, 201-transition wing, 202-morphing wing, 3-rotor, 4-vertical tail, 5-wingtip tilt module, 6-canard. DETAILED DESCRIPTION

[0044] 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.

[0045] The purpose of the present invention is to provide a forward-swept wing variable configuration unmanned aerial vehicle and a configuration change method thereof, so as to solve the problems existing in the above-mentioned prior art and ensure that it can have good stability and aerodynamic performance under different flight conditions.

[0046] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0047] The present invention provides a forward-swept wing variable configuration unmanned aerial vehicle, which combines the performance advantages of rotary-wing aircraft and conventional take-off and landing fixed-wing aircraft; thereby combining the characteristics of fixed-wing aircraft such as relatively fast speed, relatively long airborne time, and relatively long range with the characteristics of rotary-wing aircraft that can take off and land vertically and hover. Figures 1 to 14 As shown, its structure includes a fuselage 1, wings 2, rotors 3, canards 6, and a vertical tail 4. The two wings 2 are symmetrically arranged on either side of the fuselage 1, and the two wings 2 and the fuselage 1 form a forward-swept wing configuration. The wings 2 can rotate horizontally about their connection to the fuselage 1 to change the magnitude of the forward sweep angle. The rotors 3 are located at the wingtips of the wings 2 and can rotate about the axis of the wing 2. The two vertical tails 4 are symmetrically arranged above the tail of the fuselage 1. The two canards 6 are symmetrically arranged on either side of the fuselage 1, and the canards 6 are located between the nose of the fuselage 1 and the wings 2. Compared with conventional tilt-rotor 3 aircraft, the present invention can change the forward sweep angle of the wings 2 to meet the requirements of different flight conditions, taking into account the aircraft's take-off and landing performance, cruising performance, and maneuverability. Due to the forward-swept nature of the wings 2, the aircraft's center of gravity shifts forward, improving stability during the transition between fixed-wing and tilt-rotor 3 modes. The wing of the present invention is a forward-swept wing, with the rotor 3 positioned at the tip of the wing 2. This shifts the center of gravity forward and provides greater stability. The variable forward sweep angle of the wing 2 allows the aerodynamic shape of the wing 2 to be actively altered according to changing flight conditions, further improving aircraft performance. The arrangement of a pair of canards 6 increases the maximum lift coefficient of the drone and improves its maneuverability to a certain extent.

[0048] Tilt-rotor aircraft have the advantages of both fixed-wing and rotary-wing aircraft. They can hover and take off and land vertically, and can fly at high speed and over long distances. However, the tilt-rotor aircraft in the prior art adopts a traditional configuration, and the tilt-rotor aircraft still faces difficulties in flight control. When switching between vertical take-off and landing mode and cruise mode, they are prone to problems such as insufficient stability and continuous drop in flight altitude. The forward-swept wing variable configuration unmanned aerial vehicle of the present invention has no horizontal tail, and the wing 2 adopts a forward-swept wing configuration. The wingtip of the wing 2 is provided with a tiltable rotor 3, and the tailless layout is used to achieve better aerodynamic performance. The tailless configuration can eliminate the extra weight and resistance brought by the traditional horizontal tail in vertical take-off and landing, further improving the flight performance. At the same time, based on the characteristics of this layout, the tilting part of the rotor 3 is arranged at the wingtip of the wing 2, thereby achieving the forward shift of the center of gravity of the aircraft and enhancing its stability.

[0049] The flight modes of a vertical takeoff and landing (VTOL) aircraft during a single mission primarily include vertical takeoff, low-speed cruising, hovering, circling, and vertical landing. The forward-swept wing variable-configuration unmanned aerial vehicle of the present invention can exhibit multiple flight modes during a single mission, each corresponding to a different configuration, to achieve higher aerodynamic efficiency and enhance overall flight performance.

[0050] In one embodiment, during vertical takeoff and landing, the rotor 3 of the aircraft of this embodiment remains in a state after being tilted 90 degrees from the initial state. At this time, the main axis of the rotor 3 is arranged vertically and the rotating surface of the rotor 3 is arranged horizontally, so that the lift direction is vertically upward; after reaching the specified altitude, the rotor 3 tilts in the opposite direction and returns to the initial position; in the low-speed cruising state, the forward sweep angle of the wing 2 is reduced to increase the aspect ratio of the wing 2 to provide a higher lift-to-drag ratio, thereby improving the range; and when the rotor 3 tilts and the aircraft is hovering or circling, the wing 2 returns to the initial forward sweep angle state to move the center of gravity of the entire aircraft forward, thereby improving the stability of the entire aircraft. The configuration of the aircraft of this embodiment in different flight modes can be divided into the following three types:

[0051] First, in the vertical takeoff and landing (VTOL) configuration, rotor 3 tilts upward 90 degrees to redirect the aerodynamic force, enabling vertical takeoff and landing (VTOL) while the drone is horizontal. During this process, wings 2 remain swept forward, shifting the center of gravity forward and increasing stability during VTOL and rotor 3 tilting. This configuration is also suitable for hovering.

[0052] Second, the cruise configuration. In this configuration, section 2 of the wing has a smaller forward sweep angle, which can increase the aspect ratio of wing 2 and improve the lift-to-drag ratio in the low-speed cruise state, thereby increasing the range of the aircraft. In addition, since the tip of the forward-swept wing 2 may be twisted, aeroelastic divergence may occur, especially when encountering gusts of wind and other atmospheric disturbances during cruise, the aeroelastic effect will be amplified, causing certain safety hazards. The cruise configuration with a small forward sweep angle can improve the adverse effects of atmospheric disturbances.

[0053] Third, in the maneuvering circling configuration, the forward-swept wing has better stall performance, so it has stronger maneuverability when flying at low speed and large angle of attack. In this configuration, wing 2 maintains the initial forward-swept state, which has better adaptability when the UAV performs low-speed maneuvering circling.

[0054] In one embodiment, to achieve the aforementioned transitions between different configurations, a wingtip tilt module 5 is movably mounted on the end of wing 2 away from fuselage 1. The main shaft of rotor 3 is connected to wingtip tilt module 5. Wing 2 has a built-in tilting power unit capable of driving wingtip tilt module 5 to rotate about the axis of wing 2. Rotation of wingtip tilt module 5 along the spanwise direction alters the lift vector of rotor 3, achieving the multifunctional effects of vertical takeoff and landing and cruise. The main wing portion of wing 2 does not move during rotor 3 tilting, ensuring the stability and controllability of rotor 3 tilting during flight. The wing 2 includes a transition wing 201 and a deformable wing 202. The transition wing 201 is fixedly connected to the outside of the fuselage 1. The wing root of the deformable wing 202 is hinged to the wingtip of the transition wing 201. A wingspan drive device is provided in the transition wing 201. The wingspan drive device can control the deformable wing 202 to rotate horizontally around the hinge point between it and the transition wing 201 to change the forward sweep angle of the wing 2. When the forward sweep angle of the wing 2 decreases, the aspect ratio increases accordingly, and a higher lift-to-drag ratio can be obtained, thereby increasing the cruising performance of the aircraft; the rotor 3 is arranged at the wingtip position of the deformable wing 202.

[0055] The swept-wing and rotor 3 change angles during the aircraft's configuration, creating an unavoidable gap between the wings 2. This gap degrades the aircraft's overall aerodynamic performance. To ensure airtightness, the drive mechanisms for changing the swept-wing 2 angle and the tilting rotor 3 should be designed to be as compact as possible to increase transmission efficiency and minimize gaps and friction between components during configuration changes.

[0056] In order to enable the aircraft of the present invention to maintain various configuration states, in one embodiment, locking mechanisms are provided at the wingtip positions of the wing 2 and the wingtip positions of the transition wing 201. These locking mechanisms are capable of locking the main axis of the rotor 3 to a set angle relative to the wing 2, or locking the morphing wing 202 to the transition wing 201. The specific structure of the locking mechanism is not limited, and an electromagnetic snap may be used. For example, an electromagnetic snap may be provided on one side of the hinge point between the morphing wing 202 and the transition wing 201. When the morphing wing 202 rotates to the set angle, the electromagnetic snap is driven by a remote wireless controller to engage and lock the hinge point between the morphing wing 202 and the transition wing 201, thereby improving the connection stability between the morphing wing 202 and the transition wing 201. The electromagnetic snap on the rotor 3 operates in the same manner. The electromagnetic snap structure belongs to the prior art and will not be described in detail. In addition, other electric locking mechanisms with locking functions in the prior art may also be used.

[0057] There is no limitation on the wingspan drive device. In one embodiment, the deformable wing 202 is hinged to the transition wing 201, and the wingspan drive device includes an actuator or a cylinder arranged in the transition wing 201, and the end of the telescopic rod of the actuator or the cylinder is hinged to the deformable wing 202. By controlling the extension and retraction of the telescopic rod of the actuator or the cylinder, the rotation of the deformable wing 202 relative to the transition wing 201 can be achieved. At the same time, the actuator or the cylinder can also play a certain supporting role for the deformable wing 202. In addition, the wingspan drive device can also adopt a gear set structure or a worm gear structure, and a drive motor is arranged in the transition wing 201. The drive motor is connected to the deformable wing 202 through a gear set or a worm gear structure, which can also achieve the function of driving the deformable wing 202 to rotate.

[0058] Furthermore, in one embodiment, the wingtip tilt module 5 includes a slider-crank mechanism, which is disposed on the wing 2 and connected to the main shaft of the rotor 3 at one end and an actuator at the other end. The actuator's telescopic rod can drive the slider to move forward and backward along the span of the wing 2, thereby driving the first and second connecting rods of the crank to rotate. The cam at the end of the second connecting rod rotates. Since the cam is perpendicular to the span of the wing 2, the rotation of the cam drives the main shaft of the rotor 3 connected to the cam to tilt up and down, thereby driving the rotor 3 to tilt up and down. In addition, the wingtip tilt module 5 can also use a drive motor in conjunction with a gear set structure to achieve the tilt function of the rotor 3.

[0059] In one embodiment, the present invention also provides a configuration change method for the above-mentioned forward-swept-wing variable-configuration unmanned aerial vehicle, comprising the following steps: during vertical take-off and landing, the rotor 3 is tilted 90 degrees compared to the initial state and maintained in the tilted state, the tilt rotor 3 is installed at the wing tip, and during vertical take-off and landing, the center of gravity of the wing 2 and the position of the rotor 3 are adjusted by changing the forward sweep angle of the wing 2 to enhance stability; after reaching the specified height, the rotor 3 is tilted in the opposite direction and returned to the initial position; in the low-speed cruising state, the wing 2 is rotated horizontally backward to reduce the forward sweep angle of the wing 2, so that the aspect ratio of the wing 2 is increased. When cruising, the wing section 2 has a smaller forward sweep angle, which can increase the aspect ratio of the wing 2 and improve the lift-to-drag ratio in the low-speed cruising state, thereby increasing the range of the UAV and alleviating the adverse effects of atmospheric disturbances. During the hovering, hovering or tilting of the rotor 3 of the forward-swept wing variable configuration UAV, the wing 2 rotates forward to return to the initial forward sweep angle state. During hovering, the wing 2 maintains the initial forward sweep state. Due to the better stall performance of the forward-swept wing, it has strong maneuverability when flying at low speeds and high angles of attack, and thus has good adaptability when the UAV performs low-speed maneuvering and hovering. The aircraft of the present invention adopts a forward-swept wing configuration without a horizontal tail. The forward-swept wing has good low-speed cruising performance and maneuverability, which can meet the requirements of the UAV for long-range and aerial hovering operations. In addition, the forward-swept wing configuration helps to move the center of gravity of the aircraft forward, thereby increasing stability during the tilting of the rotor 3 and maneuvering flight.

[0060] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. A forward-swept wing variable configuration unmanned aerial vehicle, characterized by: include: body; Wings, wherein the two wings are symmetrically arranged on both sides of the fuselage, and the two wings and the fuselage form a forward-swept wing configuration; the wings can rotate horizontally around the connection point between them and the fuselage to change the magnitude of the forward sweep angle; a rotor, disposed at the wingtip of the wing, and capable of rotating around the axis of the wing; Two vertical tail fins are symmetrically arranged above the tail of the fuselage.

2. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 1, characterized in that: It also includes canards, two of which are symmetrically arranged on both sides of the fuselage, and the canards are located between the head and wings of the fuselage.

3. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 1, characterized in that: A wingtip tilt module is movably provided at one end of the wing away from the fuselage, the main shaft of the rotor is connected to the wingtip tilt module, and the wing has a built-in tilt power device that can drive the wingtip tilt module to rotate around the axis of the wing.

4. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 1, characterized in that: The wing includes a transition wing and a deformable wing, the transition wing is fixedly connected to the outside of the fuselage, the wing root of the deformable wing is hinged to the wingtip of the transition wing, and a wingspan drive device is provided in the transition wing. The wingspan drive device can control the deformable wing to rotate horizontally around the hinge point between the wing and the transition wing to change the forward sweep angle of the wing; the rotor is arranged at the wingtip position of the deformable wing.

5. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 1, characterized in that: During the vertical take-off and landing process of the forward-swept-wing variable-configuration unmanned aerial vehicle, the rotor rotates until the main axis of the rotor is arranged vertically, and the wing rotates until the forward sweep angle is greater than zero, at which time a vertical take-off and landing configuration is formed.

6. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 5, characterized in that: During the cruise of the forward-swept-wing variable-configuration unmanned aerial vehicle, the forward sweep angle value of the wing is reduced to a value smaller than the forward sweep angle value during the vertical take-off and landing configuration; the rotor rotates until the main axis of the rotor is arranged horizontally, at which time a cruise configuration is formed.

7. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 6, characterized in that: During the maneuvering and circling process of the forward-swept-wing variable-configuration unmanned aerial vehicle, the forward sweep angle value of the wing becomes the initial value, and the forward sweep angle value in the vertical take-off and landing configuration is the initial value; the main axis of the rotor is arranged horizontally, and a maneuvering and circling configuration is formed at this time.

8. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 1, characterized in that: A locking mechanism is provided at the wingtip of the wing, which can lock the main shaft of the rotor to a set angle position with the wing.

9. The forward-swept wing variable configuration unmanned aerial vehicle according to claim 3, characterized in that: The wingtip tilt module includes a crank slider mechanism, which is arranged on the wing, and one end of the crank slider mechanism is connected to the main shaft of the rotor, and the other end is connected to an actuator.

10. A method for changing the configuration of a forward-swept wing variable configuration unmanned aerial vehicle according to any one of claims 1 to 9, characterized in that: The steps include: During vertical takeoff and landing, the rotor tilts 90 degrees from its initial state and maintains the tilted state; After reaching the specified height, the rotor tilts in the opposite direction and returns to the initial position; In the low-speed cruising state, the wings rotate horizontally backward to reduce the wing sweep angle and increase the wing aspect ratio; When a forward-swept-wing variable-configuration unmanned aerial vehicle is hovering, circling, or tilting its rotor, the wings rotate forward to return to the initial forward sweep angle state.

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