Airplane wing and airplane

Abstract

The application discloses an aircraft wing, relates to the technical field of flight equipment, and comprises fixed wing assemblies, rotor assemblies and a first driving device, the fixed wing assemblies are two, the rotor assemblies are two, each rotor assembly comprises a connecting piece and a rotor body, one end of each connecting piece is connected with one rotor body, and the other end of each connecting piece is used for being connected with a fuselage; the first driving device is used for being connected with the fuselage, each fixed wing assembly is fixedly connected with the first driving device, the first driving device can drive each fixed wing assembly to rotate around a vertical shaft of the fuselage, and the first driving device can drive each fixed wing assembly to move to overlap with one rotor assembly. The application further discloses an aircraft comprising a fuselage and the aircraft wing, one end of each connecting piece away from each rotor body is connected with the fuselage, and the first driving device is connected with the fuselage. The application can increase the maneuverability of the aircraft, and high-speed flight can be realized.

Description

Technical Field

[0001] This invention relates to the field of flight equipment technology, and in particular to an aircraft wing and an aircraft. Background Technology

[0002] Aircraft wings consist of fixed wings and rotors. Fixed wings primarily generate lift through aerodynamic principles, while rotors generate lift primarily through rotor rotation. Rotorcraft provide upward thrust through rotor rotation, enabling vertical takeoff and landing (VTOL). Therefore, rotorcraft do not require long runways for takeoff and can operate in most areas. Rotorcraft also possess good hovering capabilities, allowing them to better perform observation or monitoring tasks in specific areas. Fixed-wing aircraft typically have longer flight times and can fly at relatively high speeds, covering larger areas in a single flight. However, fixed-wing aircraft usually require long runways for takeoff and landing, making them susceptible to space constraints; furthermore, they lack hovering capabilities, limiting their flexibility in certain environments.

[0003] Currently, scholars have conducted extensive research on aircraft capable of vertical takeoff and landing, hovering, and high-speed flight. Among these, hybrid aircraft, such as compound helicopters, combine the advantages of both rotorcraft and fixed-wing aircraft by installing fixed wings and thrust devices on rotorcraft. For example, Chinese patent CN109178301A provides a fixed-wing / rotorcraft hybrid UAV, which includes a first wing, a second wing, a first rotor assembly, a second rotor assembly, a third rotor assembly, and a fourth rotor assembly. The first and third rotor assemblies are connected to the first rotor arm via motor mounts, and the second and fourth rotor assemblies are connected to the second rotor arm via motor mounts. The first rotor arm is externally mounted on the lower surface of the first wing and fixed with bolts, and the second rotor arm is externally mounted on the lower surface of the second wing and fixed with bolts. In hybrid aircraft such as fixed-wing and rotor-rotor UAVs, the aerodynamic interference between the rotor and fixed wing has a significant impact on the overall aircraft trim and flight performance. The aerodynamic interference between the rotor and fixed wing of the hybrid aircraft can increase the equivalent drag of the rotor-fixed wing combination by up to 20%, resulting in lower flight efficiency. Summary of the Invention

[0004] The purpose of this invention is to provide an aircraft wing and an aircraft to solve the problems existing in the prior art, thereby increasing the maneuverability of the aircraft, improving its aerodynamic performance, reducing drag and noise, and achieving higher speed flight.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] This invention provides an aircraft wing, comprising a fixed wing assembly, a rotor assembly, and a first drive device, wherein:

[0007] The fixed-wing assembly consists of two components;

[0008] The rotor assembly comprises two rotor components, each rotor component including a connector and a rotor body. Each rotor body includes a first fixing component, a blade assembly, a first duct, and a second drive device. One end of each connector is connected to one of the first fixing components, and the other end of each connector is used to connect to the fuselage. Each blade assembly is rotatably connected to each of the first fixing components. Each of the second drive devices is connected to each of the first fixing components. Each of the first ducts is connected to each of the second drive devices. The upper surface of each of the first fixing components is provided with a first storage cavity. One end of each of the first ducts is disposed in each of the first storage cavities. Each of the second drive devices can drive each of the first ducts to move in a direction parallel to the vertical axis of the aircraft. Furthermore, by driving each of the first ducts to move in a direction parallel to the vertical axis of the aircraft, each of the second drive devices can cause each of the first ducts to extend out of each of the first storage cavities or be hidden inside each of the first storage cavities.

[0009] The first drive device is used to connect to the fuselage, and each of the fixed wing assemblies is fixedly connected to the first drive device. The first drive device can drive each of the fixed wing assemblies to rotate around the vertical axis of the fuselage, and the first drive device can drive each of the fixed wing assemblies to move to overlap with one of the rotor assemblies.

[0010] Preferably, each fixed wing assembly includes a fixed wing body, a second fixing member, a second duct, and a third driving device. Each second fixing member and each second duct is arc-shaped. One end of each fixed wing body is fixedly connected to the first driving device, and the other end of each fixed wing body is fixedly connected to the second fixing member. Each third driving device is connected to each second fixing member. A second receiving cavity extending along the length direction of the second fixing member is provided on one end face of each second fixing member. One end of each second duct is disposed in the second receiving cavity. Each third driving device can drive each second duct to extend and retract along each second receiving cavity. By driving each second duct to extend and retract along each second receiving cavity, each third driving device can cause each second duct to extend out of or be hidden in each second receiving cavity. When each second duct extends out of each second receiving cavity, each second duct and each second fixing member can form a ring structure.

[0011] Preferably, each of the first fixing members and each of the first ducts are annular. When each of the first ducts extends out of each of the first receiving cavities and each of the second ducts extends out of each of the second receiving cavities, the end of each of the first ducts away from the first fixing member can contact the outer wall of each of the annular structures.

[0012] Preferably, each of the connecting members is arranged along the longitudinal axis of the fuselage, and each of the rotor bodies and each of the connecting members can form a rotational connection around a first axis, and each of the first axes is parallel to the transverse axis of the fuselage.

[0013] Preferably, at least one of the connecting members is rotatably connected to the fuselage about a second axis, and each of the second axes is parallel to the longitudinal axis of the fuselage.

[0014] Preferably, the first driving device includes a rotating shaft, a fixed block, and a limiting member. The rotating shaft is rotatably connected to the machine body, the fixed block is threadedly connected to the rotating shaft, and the limiting member is fixedly connected to the machine body. The limiting member can contact the fixed block and restrict the rotation of the fixed block around the axis of the rotating shaft.

[0015] Preferably, each of the second driving devices includes a first elastic element and at least one first driving assembly. Each first driving assembly includes a first driving body, a first pulley, and a first connecting rope. One end of each first connecting rope of each rotor body is fixedly connected to the first duct of each rotor body, and the other end of each first connecting rope of each rotor body is fixedly connected to one of the first pulleys of each rotor body. Each first pulley is fixedly connected to the output end of one of the first driving bodies. Each first elastic element is disposed within each first receiving cavity, and each first elastic element of each rotor body can... Each first drive body abuts against the first duct of each rotor body, and each first drive body can drive the corresponding first groove wheel to rotate clockwise or counterclockwise around the axis of the corresponding first groove wheel. Each first groove wheel can cause the corresponding first connecting rope to be wound around the first groove wheel by rotating clockwise or counterclockwise around its own axis. Each first groove wheel can cause the corresponding first duct to be hidden in the corresponding first storage cavity by rotating clockwise or counterclockwise around its own axis. When each first groove wheel rotates counterclockwise or clockwise around its own axis, the corresponding first elastic element can push the corresponding first duct to extend out of the corresponding first storage cavity.

[0016] Preferably, each third drive device includes a second elastic element and at least one second drive assembly. Each second drive assembly includes a second drive body, a second pulley, and a second connecting rope. One end of each second connecting rope of each fixed wing assembly is fixedly connected to the second duct of each fixed wing assembly, and the other end of each second connecting rope of each fixed wing assembly is fixedly connected to one of the second pulleys of each fixed wing assembly. Each second pulley is fixedly connected to the output end of one of the second drive bodies. Each second elastic element is disposed within each second receiving cavity, and each second elastic element of each fixed wing assembly can... Each second drive body abuts against the second duct of each fixed wing assembly, and can drive the corresponding second grooved wheel to rotate clockwise or counterclockwise around the axis of the corresponding second grooved wheel. Each second grooved wheel can cause the corresponding second connecting rope to be wound around the corresponding second grooved wheel by rotating clockwise or counterclockwise around its own axis, and each second grooved wheel can cause the corresponding second duct to be hidden in the corresponding second storage cavity by rotating clockwise or counterclockwise around its own axis. When each second grooved wheel rotates counterclockwise or clockwise around its own axis, the corresponding second elastic element can push the corresponding second duct to extend out of the corresponding second storage cavity.

[0017] The present invention provides an aircraft, including the fuselage and the aircraft wings, wherein the ends of each of the connecting members away from the rotor bodies are connected to the fuselage, and the first drive device is connected to the fuselage.

[0018] The present invention achieves the following technical effects compared to the prior art:

[0019] This invention provides an aircraft wing and an aircraft, including a fixed-wing assembly, a rotor assembly, and a first drive device. Each rotor assembly includes a connector and a rotor body. Each fixed-wing assembly is fixedly connected to the first drive device. The first drive device can drive each fixed-wing assembly to rotate around the vertical axis of the fuselage, and can also drive each fixed-wing assembly to overlap with one of the rotor assemblies. By driving the fixed-wing assemblies to rotate around the vertical axis of the fuselage through the first drive device, the fixed-wing assemblies can overlap directly above the corresponding rotor assemblies, putting the wing in rotor mode, enabling vertical takeoff and landing and hovering, increasing the aircraft's maneuverability; and allowing each fixed-wing assembly to deploy to a position between two rotor assemblies, putting the wing in fixed-wing mode. When the wing switches to rotor mode, a second drive device drives a first duct to extend outside a first storage cavity, achieving ducted flight, improving the aerodynamic performance of the rotor assembly, and reducing drag and noise. When the wing switches to fixed-wing mode, the first duct is driven by the second drive device to hide inside the first storage cavity to reduce flight drag and achieve higher speed flight. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the aircraft in rotor mode provided in Example 2;

[0022] Figure 2 This is a schematic diagram of the aircraft in fixed-wing mode provided in Example 2. Figure 1 ;

[0023] Figure 3 This is a schematic diagram of the aircraft in fixed-wing mode provided in Example 2. Figure 2 ;

[0024] Figure 4 This is a structural diagram of the aircraft during yaw flight as provided in Example 2;

[0025] Figure 5 This is a schematic diagram of the structure of the second duct when it is deployed, as provided in Example 1.

[0026] Figure 6 This is a schematic diagram of the structure of the first duct when it is deployed, as provided in Example 1.

[0027] Figure 7 This is a structural schematic diagram of the first and second ducts combined in Embodiment 1.

[0028] In the diagram: 100, aircraft wing; 200, aircraft; 101, fixed wing body; 102, second fixing component; 103, second duct; 104, ring structure; 105, second drive body; 106, second pulley; 107, second connecting rope; 108, rope groove; 2, rotor assembly; 201, connector; 202, rotor body; 203, first fixing component; 204, blade assembly; 205, first duct; 206, first drive body; 207, first pulley; 208, first connecting rope; 209, first rope hole; 301, shaft; 302, fixing block; 303, column; 4, fuselage; 5, servo motor; 6, aileron; 7, connecting shaft. Detailed Implementation

[0029] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] The purpose of this invention is to provide an aircraft wing and an aircraft to solve the problems existing in the prior art, thereby increasing the maneuverability of the aircraft, improving its aerodynamic performance, reducing drag and noise, and enabling higher speed flight.

[0031] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0032] Example 1

[0033] like Figure 1-7 As shown, this embodiment provides an aircraft wing 100, including a fixed wing assembly, a rotor assembly 2, and a first drive device. There are two fixed wing assemblies and two rotor assemblies 2. Each rotor assembly 2 includes a connector 201 and a rotor body 202. Each rotor body 202 includes a first fixing member 203, a blade assembly 204, a first duct 205, and a second drive device. One end of each connector 201 is connected to a first fixing member 203, and the other end of each connector 201 is used to connect to the fuselage 4. Each blade assembly 204 is rotatably connected to each first fixing member 203. Each second drive device is connected to each first fixing member 203. Each first duct 205 is connected to each second drive device. The upper surface of component 203 is provided with a first storage cavity. One end of each first duct 205 is disposed within the first storage cavity. Each second drive device can drive each first duct 205 to move in a direction parallel to the vertical axis of the aircraft 200. Furthermore, by driving each first duct 205 to move in a direction parallel to the vertical axis of the aircraft 200, each second drive device can cause each first duct 205 to extend outside or be hidden within the first storage cavity. The first drive device is used to connect to the fuselage 4. Each fixed wing assembly is fixedly connected to the first drive device. The first drive device can drive each fixed wing assembly to rotate around the vertical axis of the fuselage 4, and can also drive each fixed wing assembly to move until it overlaps with a rotor assembly 2. By driving the fixed wing assembly to rotate around the vertical axis of the fuselage 4 through the first drive device, the fixed wing assembly can overlap directly above the corresponding rotor assembly 2, causing the wing to be in rotor mode, such as... Figure 1 As shown, vertical takeoff and landing and hovering are achieved, increasing the maneuverability of the aircraft 200; and it allows each fixed-wing component to deploy to the position between the two rotor components 2, so that the wings are in fixed-wing mode, as shown. Figure 2 As shown, this configuration enables relatively high-speed flight. When the wing switches to rotor mode, the first duct 205 extends out of the first storage cavity via the second drive device, achieving ducted flight, improving the aerodynamic performance of the rotor assembly 2, and reducing drag and noise. When the wing switches to fixed-wing mode, the first duct 205 retracts into the first storage cavity via the second drive device to reduce flight drag and achieve relatively high-speed flight.

[0034] It should be noted that the longitudinal axis of fuselage 4 is the axis along the length of fuselage 4, the transverse axis of fuselage 4 is a straight line from the left wing (fixed wing) through the center of gravity to the right wing and perpendicular to the longitudinal axis, and the vertical axis of fuselage 4 is perpendicular to both the longitudinal and transverse axes. Preferably, the fixed wing assembly is a component symmetrical about its own length, and the rotor assembly 2 is a component symmetrical about its own length. The overlap of each fixed wing assembly with the corresponding rotor assembly 2 means that the axis of symmetry of each fixed wing assembly is parallel to the axis of symmetry of the corresponding rotor assembly 2. When the fixed wing assembly is deployed to the fixed wing mode, the extension direction of the fixed wing assembly is perpendicular to the extension direction of the rotor assembly 2. The rotor assembly 2 is located at the front and rear ends of fuselage 4, and the fixed wing is formed by... Figure 1 The state has just transitioned to Figure 2 In this state, the main lift is still provided by the rotor assembly 2. In this state, the fuselage 4 can be tilted forward by adjusting the rotation speed of the front and rear rotor assemblies 2, thereby generating forward thrust. This allows the fixed-wing assembly to generate lift so that the aircraft 200 can fly forward at high speed. In this state, the downwash or rotor wake generated by the rotor assembly 2 has little impact on the fuselage and fixed-wing assembly.

[0035] In this embodiment, each fixed wing assembly includes a fixed wing body 101, a second fixing member 102, a second duct 103, and a third driving device. Each second fixing member 102 and each second duct 103 is arc-shaped. One end of each fixed wing body 101 is fixedly connected to a first driving device, and the other end of each fixed wing body 101 is fixedly connected to a second fixing member 102. Each third driving device is connected to each second fixing member 102. A finite element is provided on one end face of each second fixing member 102 along its length direction. The second receiving cavity extends along its length, with one end of each second duct 103 disposed within the second receiving cavity. Each third driving device can drive each second duct 103 to extend and retract along each second receiving cavity. By driving each second duct 103 to extend and retract along each second receiving cavity, the third driving device can cause each second duct 103 to extend out of or be hidden within each second receiving cavity. When each second duct 103 extends out of its second receiving cavity, each second duct 103 and each second fixing member 102 can form a ring structure 104. When the wing switches to rotor mode, the third driving device drives the second duct 103 to extend out of the second receiving cavity. The second duct 103 and the first duct 205 together form the rotor duct, causing the blade assembly 204 to rotate in a deeper duct. This allows most of the airflow generated by the blade assembly 204 to be converted into lift, and the deeper duct can also impede noise propagation, thus reducing the noise generated by the blade assembly 204. When the wing switches to fixed-wing mode, the second duct 103 is driven by the third drive device to hide inside the second storage cavity to reduce flight drag.

[0036] In this embodiment, each first fixing member 203 and each first duct 205 is annular, preferably circular. When each first duct 205 extends outside its first receiving cavity and each second duct 103 extends outside its second receiving cavity, the wing is in rotor mode, and the end of each first duct 205 away from the first fixing member 203 can contact the outer wall of each annular structure 104. As a preferred embodiment, the annular structure 104 is partially conical, and the diameter of the larger end of the annular structure 104 is larger than the diameter of the first duct 205. The conical annular structure 104 has an airflow converging effect, thereby allowing the airflow to flow more smoothly into the duct.

[0037] In this embodiment, each connecting member 201 is arranged along the longitudinal axis of the fuselage 4, and each rotor body 202 and each connecting member 201 can form a rotatable connection around a first axis, which is parallel to the transverse axis of the fuselage 4. In a preferred embodiment, each first fixing member 203 and each connecting member 201 can form a rotatable connection around a first axis. When the wing is in rotor mode, the centerline of the rotor body 202 is parallel to the vertical axis of the fuselage 4; when the wing is in fixed-wing mode, by making the centerline of the rotor body 202 parallel to the vertical axis of the fuselage 4, such as... Figure 2As shown, it can achieve accelerated flight. After acceleration, the rotor body 202 can be rotated around the first axis until it is parallel to the longitudinal axis of the fuselage 4, with the center line of the rotor body 202 parallel to the longitudinal axis of the fuselage 4. Figure 3 As shown.

[0038] In this embodiment, at least one connector 201 is rotatably connected to the fuselage 4 about a second axis, and each second axis is parallel to the longitudinal axis of the fuselage 4. Figure 4 As shown, yaw flight can be achieved by changing the angles of the connector 201 and the rotor body 202. For example, the connector 201 at the front of the flight direction can be rotated to a direction parallel to the vertical axis of the fuselage 4. With the rotor body 202's centerline parallel to the longitudinal axis of the fuselage 4 as the initial position of the rotor, driving the rotor body 202 to turn right from this initial position will cause the aircraft 200 to turn right. Driving the rotor body 202 to turn left from the initial position will cause the aircraft 200 to turn left, thus achieving vector propulsion and increasing the maneuverability of the aircraft 200. It should be noted that left and right turns are defined based on the direction of flight.

[0039] In this embodiment, the first driving device includes a rotating shaft 301, a fixed block 302, and a limiting member. The rotating shaft 301 is rotatably connected to the fuselage 4, the fixed block 302 is threadedly connected to the rotating shaft 301, and the limiting member is fixedly connected to the fuselage 4. The limiting member can contact the fixed block 302 and restrict the rotation of the fixed block 302 around the axis of the rotating shaft 301. By rotating the rotating shaft 301 clockwise and counterclockwise, the fixed block 302 can move up and down under the action of the limiting member, thereby realizing the switching between rotor mode and fixed-wing mode.

[0040] In a preferred embodiment, the rotor body 202 is driven to rotate around the first axis, the connecting member 201 is driven to rotate around the second axis, and the rotating shaft 301 is driven to rotate around its own axis by a motor or servo motor 5.

[0041] In this embodiment, each second driving device includes a first elastic element and at least one first driving assembly. Each driving assembly includes a first driving body 206, a first grooved wheel 207, and a first connecting rope 208. One end of each first connecting rope 208 of each rotor body 202 is fixedly connected to a first duct 205 of each rotor body 202, and the other end of each first connecting rope 208 of each rotor body 202 is fixedly connected to a first grooved wheel 207 of each rotor body 202. Each first grooved wheel 207 is fixedly connected to the output end of a first driving body 206. Each first elastic element is disposed in each first receiving cavity, and each first elastic element of each rotor body 202 can... Each first drive body 206 abuts against the first duct 205 of each rotor body 202, and can drive the corresponding first groove wheel 207 to rotate clockwise or counterclockwise around the axis of the corresponding first groove wheel 207. Each first groove wheel 207 can cause the corresponding first connecting rope 208 to be wound around the first groove wheel 207 by rotating clockwise or counterclockwise around its own axis. Each first groove wheel 207 can also cause the corresponding first duct 205 to be hidden in the corresponding first storage cavity by rotating clockwise or counterclockwise around its own axis. When each first groove wheel 207 rotates counterclockwise or clockwise around its own axis, the corresponding first elastic element can push the corresponding first duct 205 to extend out of the corresponding first storage cavity. The first drive assembly rotates forward or backward, causing the first grooved wheel 207 to rotate forward or backward, thereby causing the first connecting rope 208 to wind around the first grooved wheel 207. The first connecting rope 208 pulls the first duct 205 into the first storage cavity and compresses the first elastic member until the first duct 205 is hidden in the first storage cavity, thus achieving the retraction of the first duct 205. When it is necessary to unfold the first duct 205, the first drive assembly rotates in reverse or forward, causing the first grooved wheel 207 to rotate in reverse or forward, and the first connecting rope 208 is released from the first grooved wheel 207. At this time, the first duct 205 moves out of the first storage cavity under the elastic force of the first elastic member.

[0042] In a preferred embodiment, the first storage cavity is a cavity with an opening at one end. A first rope hole 209 is provided on the bottom wall of the first storage cavity. The first wheel groove and the first drive body 206 are disposed on the outer bottom wall of the first fixing member 203. The first connecting rope 208 extends into the first storage cavity through the first rope hole 209 and is fixedly connected to the first duct 205. The first elastic member includes a plurality of first elastic bodies, the two ends of which can respectively abut or be fixedly connected to the bottom wall of the first storage cavity and the first duct 205. The first connecting rope 208 is a steel wire rope, and the first elastic body is a spring.

[0043] In this embodiment, each third driving device includes a second elastic element and at least one second driving assembly. Each second driving assembly includes a second driving body 105, a second pulley 106, and a second connecting rope 107. One end of each second connecting rope 107 of each fixed wing assembly is fixedly connected to the second duct 103 of each fixed wing assembly, and the other end of each second connecting rope 107 of each fixed wing assembly is fixedly connected to a second pulley 106 of each fixed wing assembly. Each second pulley 106 is fixedly connected to the output end of a second driving body 105. Each second elastic element is disposed in each second receiving cavity, and each second elastic element of each fixed wing assembly can interact with each fixed wing assembly. The second duct 103 of the fixed wing assembly abuts, and each second drive body 105 can drive the corresponding second groove wheel to rotate clockwise or counterclockwise around the axis of the corresponding second groove wheel 106. Each second groove wheel 106 can rotate clockwise or counterclockwise around its own axis to make the corresponding second connecting rope 107 wind around the corresponding second groove wheel 106. Each second groove wheel 106 can rotate clockwise or counterclockwise around its own axis to make the corresponding second duct 103 hide in the corresponding second storage cavity. When each second groove wheel 106 rotates counterclockwise or clockwise around its own axis, the corresponding second elastic member can push the corresponding second duct 103 to extend out of the corresponding second storage cavity.

[0044] The second drive assembly rotates forward or backward, causing the second grooved wheel 106 to rotate forward or backward, thereby causing the second connecting rope 107 to wind around the second grooved wheel 106. The second connecting rope 107 pulls the second duct 103 into the second storage cavity and compresses the second elastic member until the second duct 103 is hidden in the second storage cavity, thus achieving the retraction of the second duct 103. When it is necessary to unfold the second duct 103, the second drive assembly rotates in reverse or forward, causing the second grooved wheel 106 to rotate in reverse or forward, and the second connecting rope 107 is released from the second grooved wheel 106. At this time, the second duct 103 moves out of the second storage cavity under the elastic force of the second elastic member.

[0045] In a preferred embodiment, the second fixing member 102 has a second rope hole communicating with the second receiving cavity on its outer top wall and / or outer bottom wall. The second wheel groove and the second drive body 105 are disposed on the outer top wall and / or outer bottom wall of the second fixing member 102. The second connecting rope 107 extends into the second receiving cavity through the second rope hole and is fixedly connected to the second duct 103. The second elastic member includes a plurality of second elastic bodies, the two ends of which can be fixedly connected to the inner wall of the second receiving cavity and the second duct 103, respectively. The second connecting rope 107 is a steel wire rope, and the second elastic body is a spring.

[0046] In a preferred embodiment, a rope groove 108 is provided on the inner wall of the second storage cavity. The rope groove 108 is a recessed groove within the inner wall of the second storage cavity. The rope groove 108 communicates with the second rope hole, allowing the second connecting rope 107 to be accommodated within the rope groove 108. One end of the second connecting rope 107 extends from the second rope hole, and the other end extends from the opening of the rope groove 108 and is fixedly connected to the second duct 103. The rope groove 108 can limit the movement of the connecting rope, allowing the corresponding portion of the second connecting rope 107 to move along the rope groove 108.

[0047] In a preferred embodiment, the first drive device drives each fixed-wing assembly to rotate within a range of 0-90° around the vertical axis of the fuselage 4. The aircraft 200 can be a drone. Both the first drive body 206 and the second drive body 105 are servo motors 5. Each fixed-wing body 101 is equipped with an aileron 6.

[0048] In a preferred embodiment, the first driving device further includes a column 303, one end of which is fixedly connected to a motor, and the other end of which is fixedly connected to a rotating shaft 301. The motor can drive the column 303 to rotate around the axis of the rotating shaft 301, thereby driving the rotating shaft 301 to rotate around its own axis.

[0049] In a preferred embodiment, each rotor body 202 and each connector 201 are provided with a connecting shaft 7. One end of the connecting shaft 7 is fixedly connected to the rotor body 202, and the other end of the connecting shaft 7 is rotatably connected to the connector 201.

[0050] Example 2

[0051] This embodiment provides an aircraft 200, including a fuselage 4 and an aircraft wing 100 as in Embodiment 1. The end of each connector 201 away from the rotor body 202 is connected to the fuselage 4, and a first drive device is connected to the fuselage 4.

[0052] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. An aircraft wing, characterized in that: It includes a fixed-wing assembly, a rotor assembly, and a first drive unit, wherein: The fixed-wing assembly consists of two components; The rotor assembly comprises two rotor components, each rotor component including a connector and a rotor body. Each rotor body includes a first fixing component, a blade assembly, a first duct, and a second drive device. One end of each connector is connected to one of the first fixing components, and the other end of each connector is used to connect to the fuselage. Each blade assembly is rotatably connected to each of the first fixing components. Each of the second drive devices is connected to each of the first fixing components. Each of the first ducts is connected to each of the second drive devices. The upper surface of each of the first fixing components is provided with a first storage cavity. One end of each of the first ducts is disposed in each of the first storage cavities. Each of the second drive devices can drive each of the first ducts to move in a direction parallel to the vertical axis of the aircraft. Furthermore, by driving each of the first ducts to move in a direction parallel to the vertical axis of the aircraft, each of the second drive devices can cause each of the first ducts to extend out of each of the first storage cavities or be hidden inside each of the first storage cavities. The first drive device is used to connect to the fuselage, and each of the fixed wing assemblies is fixedly connected to the first drive device. The first drive device can drive each of the fixed wing assemblies to rotate around the vertical axis of the fuselage, and the first drive device can drive each of the fixed wing assemblies to move to overlap with one of the rotor assemblies. Each of the fixed wing assemblies includes a fixed wing body, a second fixing member, a second duct, and a third driving device. Each of the second fixing members and each of the second ducts is arc-shaped. One end of each of the fixed wing bodies is fixedly connected to the first driving device, and the other end of each of the fixed wing bodies is fixedly connected to the second fixing member. Each of the third driving devices is connected to each of the second fixing members. A second receiving cavity extending along the length direction of the second fixing member is provided on one end face of each of the second fixing members. One end of each of the second ducts is disposed in the second receiving cavity. Each of the third driving devices can drive each of the second ducts to extend and retract along each of the second receiving cavities. Furthermore, by driving each of the second ducts to extend and retract along each of the second receiving cavities, each of the second driving devices can cause each of the second ducts to extend out of each of the second receiving cavities or be hidden inside each of the second receiving cavities. When each of the second ducts extends out of each of the second receiving cavities, each of the second ducts and each of the second fixing members can form a ring structure. Each of the first fixing members and each of the first ducts are annular. When each of the first ducts extends out of each of the first receiving cavities and each of the second ducts extends out of each of the second receiving cavities, the end of each of the first ducts away from the first fixing member can contact the outer wall of each of the annular structures.

2. The aircraft wing according to claim 1, characterized in that: Each of the connecting members is arranged along the longitudinal axis of the fuselage, and each of the rotor bodies and each of the connecting members can form a rotational connection around a first axis, and each of the first axes is parallel to the transverse axis of the fuselage.

3. The aircraft wing according to claim 1, characterized in that: At least one of the connecting members is rotatably connected to the fuselage about a second axis, each of the second axes being parallel to the longitudinal axis of the fuselage.

4. The aircraft wing according to claim 1, characterized in that: The first driving device includes a rotating shaft, a fixed block, and a limiting member. The rotating shaft is rotatably connected to the machine body, the fixed block is threadedly connected to the rotating shaft, and the limiting member is fixedly connected to the machine body. The limiting member can contact the fixed block and restrict the rotation of the fixed block around the axis of the rotating shaft.

5. The aircraft wing according to claim 1, characterized in that: Each of the second driving devices includes a first elastic element and at least one first driving assembly. Each first driving assembly includes a first driving body, a first grooved wheel, and a first connecting rope. One end of each first connecting rope of each rotor body is fixedly connected to the first duct of each rotor body, and the other end of each first connecting rope of each rotor body is fixedly connected to one of the first grooved wheels of each rotor body. Each first grooved wheel is fixedly connected to the output end of one of the first driving bodies. Each first elastic element is disposed in each of the first receiving cavities. Each first elastic element of each rotor body can abut against the first duct of each rotor body. Each first driving body can drive the corresponding first grooved wheel to rotate clockwise or counterclockwise around the axis of the corresponding first grooved wheel. Each first grooved wheel can cause the corresponding first connecting rope to wind onto the corresponding first grooved wheel by rotating clockwise or counterclockwise around its own axis. Each first grooved wheel can cause the corresponding first duct to be hidden in the corresponding first receiving cavity by rotating clockwise or counterclockwise around its own axis. When each first grooved wheel rotates counterclockwise or clockwise around its own axis, the corresponding first elastic element can push the corresponding first duct to extend out of the corresponding first receiving cavity.

6. The aircraft wing according to claim 1, characterized in that: Each third drive device includes a second elastic element and at least one second drive assembly. Each second drive assembly includes a second drive body, a second pulley, and a second connecting rope. One end of each second connecting rope of each fixed wing assembly is fixedly connected to the second duct of each fixed wing assembly, and the other end of each second connecting rope of each fixed wing assembly is fixedly connected to one of the second pulleys of each fixed wing assembly. Each second pulley is fixedly connected to the output end of one of the second drive bodies. Each second elastic element is disposed within each second receiving cavity, and each second elastic element of each fixed wing assembly is capable of engaging with each… The second duct of the fixed wing assembly abuts, and each second drive body can drive the corresponding second groove wheel to rotate clockwise or counterclockwise around the axis of the corresponding second groove wheel. Each second groove wheel can cause the corresponding second connecting rope to be wound around the corresponding second groove wheel by rotating clockwise or counterclockwise around its own axis. Each second groove wheel can cause the corresponding second duct to be hidden in the corresponding second storage cavity by rotating clockwise or counterclockwise around its own axis. When each second groove wheel rotates counterclockwise or clockwise around its own axis, the corresponding second elastic element can push the corresponding second duct to extend out of the corresponding second storage cavity.

7. An aircraft, characterized in that: The aircraft includes the fuselage and the aircraft wing as described in any one of claims 1-6, wherein the end of each of the connecting members away from the rotor body is connected to the fuselage, and the first drive device is connected to the fuselage.

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