Deformable wing hair fused annular wing and electric vertical take-off and landing aircraft

Abstract

The invention relates to the technical field of aircraft manufacturing, in particular to a deformable wing hair fused annular wing and an electric vertical take-off and landing aircraft, the wing comprises a front wing (1), an arc-shaped side wing (3) and a rear wing (5); one ends of the two front wings (1) located on the two sides of the fuselage are connected with the fuselage through rotating shafts, the other ends of the two front wings (1) are connected with one ends of the two inclined arc-shaped side wings (3) through rotating structures, the other ends of the two inclined arc-shaped side wings (3) are connected with the rear wing on the upper portion of the fuselage through rotating structures, and the front wings (1), the arc-shaped side wings (3) and the rear wing (5) are mutually connected to form an annular wing. The annular wing ensures uniform lift distribution, efficient airflow utilization, enhanced structural strength and compact design.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft manufacturing, and in particular to a deformable wing-launch fusion annular wing and an electric vertical take-off and landing aircraft. Background Art

[0002] In recent years, electric vertical takeoff and landing (eVTOL) aircraft have attracted widespread attention due to their potential in urban air mobility (UAM) and short-distance transportation. However, existing eVTOL designs still have problems such as low aerodynamic efficiency, high requirements for take-off and landing sites, low lift-thrust conversion efficiency, and insufficient safety. Traditional designs usually adopt fixed-wing or rotary-wing structures, and there is a performance trade-off between vertical take-off and landing and horizontal cruising, resulting in high requirements for take-off and landing sites and increased wing weight. In addition, existing designs still have deficiencies in the balance of lift and thrust, flexibility of take-off and landing sites, and safety redundancy, which limits their widespread application in urban environments. Summary of the invention

[0003] In order to solve the technical problems existing in the above-mentioned prior art, the present invention provides a deformable wing-launched fusion annular wing and an electric vertical take-off and landing aircraft, and the technical solution is as follows:

[0004] On the one hand, a deformable wing-engine fusion annular wing is provided, which is applied to an electric vertical take-off and landing aircraft eVTOL, wherein the wing comprises: a front wing (1), a curved side wing (3) and a rear wing (5);

[0005] One end of two front wings (1) located on both sides of the fuselage is connected to the fuselage through a rotating shaft, the other end of the two front wings (1) is connected to one end of two inclined arc-shaped side wings (3) through a rotating structure, and the other end of the two inclined arc-shaped side wings (3) is connected to the rear wing on the upper part of the fuselage through a rotating structure. The front wings (1), the arc-shaped side wings (3) and the rear wing (5) are connected to each other to form an annular wing, and the annular wing ensures uniform lift distribution, efficient airflow utilization, enhanced structural strength and compact design.

[0006] Optionally, the annular wing also includes a plurality of ducted fans (8) arranged along the extension direction of the wings and arranged on the rear half of the upper surfaces of the two front wings (1) and the rear wing (5). The ducted fans (8) are equivalent to engines and serve as the power source of the aircraft. The wings and the ducted fan shells are tightly integrated through integrated molding or mechanical structure connection. In this wing-engine integrated configuration, the ducted fan is no longer just an independent propulsion unit, but together with the wing, it constitutes a part of the aerodynamic and structural system of the aircraft. When the ducted fan is working, it will draw air from the upper surface of the wing into the duct to provide thrust, while accelerating the air flow rate on the upper surface of the wing, thereby increasing the pressure difference between the upper and lower surfaces of the wing, generating additional lift, and stabilizing the airflow on the wing surface and reducing airflow separation. In addition, this design can utilize the aerodynamic coupling between the wing and the ducted fan to optimize the airflow distribution, reduce resistance, and improve propulsion efficiency. At the same time, through its layout adjustment, it can also reduce noise and improve the overall performance of the aircraft.

[0007] Optionally, the annular wing achieves structural deformation through a connecting rod mechanism, and the front wing (1) and the rear wing (5) of the wing can rotate around a pivot (9) parallel to the extension direction of the wing, driving the ducted fan (8) to rotate. The wing can adjust the vector thrust of the ducted fan according to the flight state of the aircraft, which not only ensures the stability of the flight process, but also further improves the aerodynamic performance of the wing, reduces resistance, and increases flight speed and fuel efficiency. At the same time, this adjustable vector thrust deformation structure enables the wing to be quickly adjusted to an optimal state under different flight states, ensuring the stability and maneuverability of the aircraft, wherein the front wing (1) rotates independently, and the rear wing (5) is driven to rotate by a hydraulic rod (6). The two ends of the arc-shaped side wing (3) are respectively connected to the front wing (1) and the rear wing (5), which is equivalent to a connecting rod. During the rotation of the front and rear wings, the arc-shaped side wings will also deform. The front wing (1) is equipped with a front flap (2), the rear wing (5) is equipped with a rear flap (7), and the arc-shaped side wings (3) are equipped with side flaps (4). By controlling the rotation of the front flap (2), the rear flap (7) and the side flap (4), the flight attitude control is achieved. In addition, the unique annular tiltable wing design makes the airflow on the wing surface more stable, reduces airflow separation and vortex generation. During the vertical take-off and landing stage, the annular wing can more effectively utilize the airflow generated by the ducted fan, enhance the downward thrust, and improve the efficiency and stability of vertical take-off and landing; during horizontal flight, it can optimize the flow path of the airflow on the wing surface, further improve the aerodynamic performance of the wing, reduce resistance, and increase flight speed and fuel efficiency.

[0008] Optionally, during horizontal flight, the wing presents a normal annular wing shape, and the ducted fan provides horizontal thrust. Compared with a single wing, such an airfoil can reduce the wingspan while providing greater lift, and has better performance during low-speed flight. At the same time, the flaps on the front and rear wings and side wings can ensure that the aircraft can achieve flexible turning and rolling during flight, ensuring that the aircraft has a certain obstacle avoidance capability when flying at low altitudes in cities.

[0009] Optionally, when the aircraft is in the process of vertical take-off and landing, the annular wing gradually transitions from a cruising state to a vertical take-off and landing state, and the normal annular wing shape will also be deformed. The front and rear wings drive the ducted fans to tilt to a vertical state, and the two arc-shaped side wings rotate clockwise around the rotation center of the front wing to a horizontal state. After the rotation, all the wing chords are in a vertical state, and multiple ducted fans are connected at the same horizontal height. At this time, the ducted fans provide vertical thrust. The advantage of such deformation is that during vertical take-off and landing, the ducted fans generate vertical thrust while the wings remain vertical, and the downward airflow generated by the fans will not accumulate on the wing surface, thereby reducing the lift loss of the aircraft due to ground effect.

[0010] On the other hand, an electric vertical take-off and landing aircraft eVTOL is provided, comprising a fuselage and the annular wing as described above.

[0011] The beneficial effects brought about by the technical solution provided by the present invention include at least:

[0012] 1) Improve the service life and reliability of the wing.

[0013] The unique shape of the annular wing allows the airflow around it to flow more evenly, and compared to traditional wings, it can produce a more even pressure distribution on the wing surface, thereby providing a more stable and even lift. During the flight of the aircraft, this even lift distribution helps to reduce the uneven force on the various parts of the wing, reduce fatigue damage to the wing structure, and improve the service life and reliability of the wing.

[0014] 2) Enhance structural strength and compactness.

[0015] The structure of the annular wing gives it high structural strength and rigidity. Under the same external force, the annular structure can more effectively disperse stress and reduce local stress concentration, thereby improving the wing's load-bearing capacity. At the same time, the compact design of the annular wing can more effectively utilize the aircraft space, facilitate the reasonable arrangement of the wings, propulsion devices and other equipment within the limited fuselage space, and optimize the overall layout of the aircraft.

[0016] 3) Simplify structure and reduce costs.

[0017] The wing of the present invention tightly connects the ducted fan and the wing into an integrated structure to form a wing-engine fusion configuration. This design reduces the complex connection structure and mounting components between the wing and the engine in the traditional design, and simplifies the production process. During the manufacturing process, there is no need to manufacture independent wing and engine mounting components separately, which reduces the processing difficulty and material cost. At the same time, due to the reduction in the number of parts, the assembly process is simpler, the production cycle is shortened, and the manufacturing cost is further reduced. From the perspective of long-term use, the wing-engine fusion structure reduces the connection points between components, reduces the probability of failure, reduces the cost of maintenance and replacement of parts, and improves the economy of the aircraft.

[0018] 4) Enhance aerodynamic performance.

[0019] By placing the ducted fan in the rear half of the upper surface of the wing, the lift of the wing is greatly improved during vertical takeoff and landing and horizontal flight. In addition, the unique annular tilting wing design makes the airflow on the wing surface more stable, reducing airflow separation and vortex generation. During the vertical takeoff and landing phase, the annular wing can more effectively utilize the airflow generated by the ducted fan, enhance the downward thrust, and improve the efficiency and stability of vertical takeoff and landing; during horizontal flight, it can optimize the flow path of the airflow on the wing surface, further improve the aerodynamic performance of the wing, reduce resistance, and increase flight speed and fuel efficiency.

[0020] 5) Improve flight stability and adaptability.

[0021] The deformable wing structure can be freely adjusted according to the flight state of the aircraft, and can maintain good stability and controllability in various flight states. In complex meteorological conditions, such as strong winds, the wing deformation structure can adjust the wing shape in time to ensure safe flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of 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 creative work.

[0023] Figure 1 This is a structural diagram of a deformable wing-engine fusion annular wing provided by an embodiment of the present invention;

[0024] Figure 2 is a wing state diagram in a horizontal flight cruising state (side view in direction A) provided by an embodiment of the present invention; Figure 3 is a wing state diagram in a vertical take-off and landing state provided by an embodiment of the present invention (side view in direction A);

[0025] Figure 4 1 is a diagram of the complete process of wing deformation provided by an embodiment of the present invention (from top to bottom, cruise state - deformation - vertical take-off and landing state);

[0026] Figure 5 It is a structural diagram of an electric vertical take-off and landing aircraft eVTOL provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0027] In order to make the technical problems, technical solutions and advantages to be solved by the present invention more clear, a detailed description will be given below with reference to the accompanying drawings and specific embodiments.

[0028] like Figure 1-4 As shown, an embodiment of the present invention provides a deformable wing-launch fusion annular wing, which is applied to an electric vertical take-off and landing aircraft eVTOL, wherein the wing comprises: a front wing (1), a curved side wing (3) and a rear wing (5);

[0029] One end of the two front wings (1) located on both sides of the fuselage is connected to the fuselage through a rotating shaft, the other end of the two front wings (1) is connected to one end of the two inclined arc-shaped side wings (3) through a rotating structure, and the other end of the two inclined arc-shaped side wings (3) is connected to the rear wing on the upper part of the fuselage through a rotating structure. The front wings (1), the arc-shaped side wings (3) and the rear wing (5) are connected to each other to form an annular wing. The annular wing ensures uniform lift distribution, efficient airflow utilization, enhanced structural strength and compact design (the uniform lift distribution characteristics of the annular wing are utilized to reduce uneven force on various parts of the wing, reduce fatigue damage, and improve the service life and reliability of the wing. The annular structure efficiently guides and constrains the airflow, optimizes the airflow utilization in the vertical take-off and landing and horizontal flight stages, improves the vertical take-off and landing efficiency and the aerodynamic performance of the horizontal flight, reduces the resistance, and improves the flight speed and fuel efficiency. At the same time, with the help of the higher structural strength and rigidity of the annular wing, the stress is effectively dispersed, the local stress concentration is reduced, the load-bearing capacity is improved, and the compact design is used to optimize the internal space layout of the aircraft).

[0030] Optionally, the annular wing also includes a plurality of ducted fans (8) arranged along the extension direction of the wings and arranged on the rear half of the upper surfaces of the two front wings (1) and the rear wing (5). The ducted fans (8) are equivalent to engines and serve as the power source of the aircraft. The wings and the ducted fan shells are tightly integrated through integrated molding or mechanical structure connection. In this wing-engine integrated configuration, the ducted fan is no longer just an independent propulsion unit, but together with the wing, it constitutes a part of the aerodynamic and structural system of the aircraft. When the ducted fan is working, it will draw air from the upper surface of the wing into the duct to provide thrust, while accelerating the air flow rate on the upper surface of the wing, thereby increasing the pressure difference between the upper and lower surfaces of the wing, generating additional lift, and stabilizing the airflow on the wing surface and reducing airflow separation. In addition, this design can utilize the aerodynamic coupling between the wing and the ducted fan to optimize the airflow distribution, reduce resistance, and improve propulsion efficiency. At the same time, through its layout adjustment, it can also reduce noise and improve the overall performance of the aircraft.

[0031] Optionally, the annular wing achieves structural deformation through a connecting rod mechanism. The front wing (1) and the rear wing (5) of the wing can rotate around a pivot (9) parallel to the extension direction of the wing, driving the ducted fan (8) to rotate. The wing can adjust the vector thrust of the ducted fan according to the flight state of the aircraft (such as vertical take-off and landing, hovering, horizontal flight, etc.), which not only ensures the stability of the flight process, but also further improves the aerodynamic performance of the wing, reduces resistance, and increases flight speed and fuel efficiency. At the same time, this adjustable vector thrust deformation structure enables the wing to be quickly adjusted to an optimal state under different flight states, ensuring the stability and maneuverability of the aircraft. The front wing (1) rotates independently, and the rear wing (5) is driven to rotate by a hydraulic rod (6). The two ends of the arc-shaped side wing (3) are respectively connected to the front wing (1) and the rear wing (5). It is equivalent to a connecting rod. When the front and rear wings rotate, the arc-shaped side wings will also deform. The front wing (1) is equipped with a front flap (2), the rear wing (5) is equipped with a rear flap (7), and the arc-shaped side wing (3) is equipped with a side flap (4). By controlling the rotation of the front flap (2), the rear flap (7) and the side flap (4), the flight attitude control is achieved. In addition, the unique annular tiltable wing design makes the airflow on the wing surface more stable, reduces airflow separation and vortex generation. In the vertical take-off and landing stage, the annular wing can more effectively utilize the airflow generated by the ducted fan, enhance the downward thrust, and improve the efficiency and stability of vertical take-off and landing; in horizontal flight, it can optimize the flow path of the airflow on the wing surface, further improve the aerodynamic performance of the wing, reduce resistance, and increase flight speed and fuel efficiency.

[0032] Optionally, during horizontal flight, the wing presents a normal annular wing shape, and the ducted fan provides horizontal thrust. Compared with a single wing, such an airfoil can reduce the wingspan while providing greater lift, and has better performance during low-speed flight. At the same time, the flaps on the front and rear wings and side wings can ensure that the aircraft can achieve flexible turning and rolling during flight, ensuring that the aircraft has a certain obstacle avoidance capability when flying at low altitudes in cities.

[0033] Optionally, when the aircraft is in the process of vertical take-off and landing, the annular wing gradually transitions from a cruising state to a vertical take-off and landing state, and the normal annular wing shape will also be deformed. The front and rear wings drive the ducted fans to tilt to a vertical state, and the two arc-shaped side wings rotate clockwise around the rotation center of the front wing to a horizontal state. After the rotation, all the wing chords are in a vertical state, and multiple ducted fans are connected at the same horizontal height. At this time, the ducted fans provide vertical thrust. The advantage of such deformation is that during vertical take-off and landing, the ducted fans generate vertical thrust while the wings remain vertical, and the downward airflow generated by the fans will not accumulate on the wing surface, thereby reducing the lift loss of the aircraft due to ground effect.

[0034] like Figure 5 As shown, an embodiment of the present invention further provides an electric vertical take-off and landing aircraft eVTOL, comprising a fuselage and the annular wing as described above.

[0035] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A deformable wing-engine fusion annular wing, applied to an electric vertical take-off and landing aircraft eVTOL, characterized in that: The wing comprises: a front wing (1), a curved side wing (3) and a rear wing (5); One end of two front wings (1) located on both sides of the fuselage is connected to the fuselage through a rotating shaft, the other end of the two front wings (1) is connected to one end of two inclined arc-shaped side wings (3) through a rotating structure, and the other end of the two inclined arc-shaped side wings (3) is connected to the rear wing on the upper part of the fuselage through a rotating structure. The front wings (1), the arc-shaped side wings (3) and the rear wing (5) are connected to each other to form an annular wing, and the annular wing ensures uniform lift distribution, efficient airflow utilization, enhanced structural strength and compact design.

2. The annular wing according to claim 1, characterized in that: The annular wing also includes a plurality of ducted fans (8) arranged along the extension direction of the wings and arranged on the rear half of the upper surfaces of the two front wings (1) and the rear wing (5). The ducted fans (8) are equivalent to engines and serve as the power source of the aircraft. The wings and the ducted fan shells are tightly integrated through integrated molding or mechanical structure connection. In this wing-engine integrated configuration, the ducted fan is no longer just an independent propulsion unit, but together with the wing, it constitutes a part of the aerodynamic and structural system of the aircraft. When the ducted fan is working, it will draw air on the upper surface of the wing into the duct to provide thrust, while accelerating the air flow rate on the upper surface of the wing, thereby increasing the pressure difference between the upper and lower surfaces of the wing, generating additional lift, and stabilizing the airflow on the wing surface and reducing airflow separation. In addition, this design can utilize the aerodynamic coupling between the wing and the ducted fan to optimize the airflow distribution, reduce resistance, and improve propulsion efficiency. At the same time, through its layout adjustment, it can also reduce noise and improve the overall performance of the aircraft.

3. The annular wing according to claim 2, characterized in that: The annular wing achieves structural deformation through a connecting rod mechanism. The front wing (1) and the rear wing (5) of the wing can rotate around a pivot (9) parallel to the extension direction of the wing, driving the ducted fan (8) to rotate. The wing can adjust the vector thrust of the ducted fan according to the flight state of the aircraft, which not only ensures the stability of the flight process, but also further improves the aerodynamic performance of the wing, reduces resistance, and increases flight speed and fuel efficiency. At the same time, this adjustable vector thrust deformation structure enables the wing to be quickly adjusted to an optimal state under different flight states, ensuring the stability and maneuverability of the aircraft. The front wing (1) rotates independently, and the rear wing (5) is driven to rotate by a hydraulic rod (6). The two ends of the arc-shaped side wing (3) are respectively connected to the front wing (1) and the rear wing (5), which is equivalent to a connecting rod. During the rotation of the rear wing, the arc-shaped side wing will also deform. The front wing (1) is equipped with a front flap (2), the rear wing (5) is equipped with a rear flap (7), and the arc-shaped side wing (3) is equipped with a side flap (4). By controlling the rotation of the front flap (2), the rear flap (7) and the side flap (4), the flight attitude control is achieved. In addition, the unique annular tiltable wing design makes the airflow on the wing surface more stable, reduces airflow separation and vortex generation. During the vertical take-off and landing stage, the annular wing can more effectively utilize the airflow generated by the ducted fan, enhance the downward thrust, and improve the efficiency and stability of vertical take-off and landing; during horizontal flight, it can optimize the flow path of the airflow on the wing surface, further improve the aerodynamic performance of the wing, reduce resistance, and increase flight speed and fuel efficiency.

4. The annular wing according to claim 3, characterized in that: During horizontal flight, the wing presents a normal annular wing shape, and the ducted fan provides horizontal thrust. Compared with a single wing, this airfoil can reduce the wingspan while providing greater lift, and has better performance during low-speed flight. At the same time, the flaps on the front and rear wings and side wings can ensure that the aircraft can achieve flexible turning and rolling during flight, ensuring that the aircraft has a certain obstacle avoidance capability when flying at low altitudes in cities.

5. The annular wing according to claim 4, characterized in that: When the aircraft is in the process of vertical take-off and landing, the annular wing gradually transitions from a cruising state to a vertical take-off and landing state, and the normal annular wing shape will also be deformed. The front and rear wings drive the ducted fans to tilt to a vertical state, and the two arc-shaped side wings rotate clockwise around the rotation center of the front wing to a horizontal state. After the rotation, all the wing chords are in a vertical state, and multiple ducted fans are connected at the same horizontal height. At this time, the ducted fans provide vertical thrust. The advantage of such deformation is that during vertical take-off and landing, the ducted fans generate vertical thrust while the wings remain vertical, and the downward airflow generated by the fans will not accumulate on the wing surface, thereby reducing the lift loss of the aircraft due to ground effect.

6. An electric vertical take-off and landing aircraft (eVTOL), comprising a fuselage and the annular wing according to any one of claims 1 to 5.

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