Vertical take-off and landing fixed-wing unmanned aerial vehicle and wing assembly thereof

Abstract

The utility model provides a vertical take-off and landing fixed wing unmanned aerial vehicle and a wing assembly thereof, the wing assembly comprises a rotor wing structure and a fixed wing structure, the fixed wing structure comprises a first wing spar, a plurality of first wing ribs, a first skin, a first metal plate, a second wing spar, a plurality of second wing ribs, a second skin and a second metal plate, the first wing ribs are arranged on the first wing spar in parallel side by side, the first metal plate is arranged at the second end of the first wing spar, the second wing ribs are arranged on the second wing spar in parallel side by side, the second metal plate is arranged at the first end of the second wing spar, and the second metal plate is detachably connected with the first metal plate. The rotor structure is arranged between the first wing spar and the second wing spar so that the included angle between the first wing spar and the second wing spar can be adjusted. The rotor structure comprises a wing arm, two rotors and two motors. The wing assembly integrates the functions of a rotor wing and a fixed wing, and is high in aspect ratio, ultra-light, high in structural strength, stable and reliable in work and high in universality.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed-wing unmanned aerial vehicle and a wing assembly thereof. Background Art

[0002] The vertical take-off and landing fixed-wing UAV is a rotor-fixed-wing composite UAV with two power systems. The rotor provides vertical lift, and the propulsion engine provides power in fixed-wing mode, thus combining excellent hovering capability with a longer cruising speed and range. Therefore, the wing assembly of the vertical take-off and landing fixed-wing UAV combines the rotor structure and the fixed-wing structure, and the rotor structure is set on the fixed-wing structure.

[0003] In order to stably support the rotor structure, the fixed-wing structure of existing vertical take-off and landing fixed-wing UAVs is heavy, resulting in a heavy wing assembly, which affects the stable and sustained flight capability of the UAV. In addition, the angle of the end of the fixed wing of existing vertical take-off and landing fixed-wing UAVs away from the fuselage cannot be adjusted, which limits the scope of use of the UAV and makes it less versatile. Utility Model Content

[0004] In order to achieve the first purpose of the utility model, the utility model provides a wing assembly with integrated rotor and fixed-wing functions, large aspect ratio, ultra-lightness, high structural strength, stable and reliable operation and strong versatility.

[0005] In order to achieve the second purpose of the utility model, the utility model provides a vertical take-off and landing fixed-wing UAV with the above-mentioned wing assembly, thereby improving stable and sustained flight capabilities.

[0006] In order to achieve the first purpose of the utility model, the utility model provides a wing assembly, including a rotor structure and a fixed wing structure, the fixed wing structure including a first wing spar, a plurality of first wing ribs, a first skin, a first metal plate, a second wing spar, a plurality of second wing ribs, a second skin and a second metal plate, the plurality of first wing ribs are arranged in parallel and side by side on the first wing spar, the first skin is covered between the windward surface of the plurality of first wing ribs and the first wing spar, the first end of the first wing spar is used to be connected to the fuselage, the first metal plate is arranged at the second end of the first wing spar; the plurality of second wing ribs are arranged in parallel and side by side on the second wing spar, and the length of the plurality of second wing ribs is It gradually narrows from the first end of the second wing beam toward the second end of the second wing beam, and the second skin covers between the windward surface of the plurality of second wing ribs and the second wing beam. The second metal plate is arranged at the first end of the second wing beam, and the second metal plate is detachably connected to the first metal plate so that the angle between the first wing beam and the second wing beam can be adjusted; the rotor structure includes a wing arm, two rotors and two motors. The wing arm is arranged on the second metal plate and the first end of the second wing beam in parallel with the first wing rib. The two rotors are rotatably supported at the two ends of the wing arm, respectively. The two motors are respectively arranged at the two ends of the wing arm, and one motor controls the rotation of one rotor.

[0007] It can be seen from the above scheme that the wing assembly of the utility model includes a rotor structure and a fixed-wing structure, and a plurality of first wing ribs of the fixed-wing structure are arranged in parallel and side by side on the first wing beam, and a plurality of second wing ribs are arranged in parallel and side by side on the second wing beam, so that the fixed-wing structure of the utility model is a hollow truss-type large aspect ratio wing structure, which makes it ultra-light and has a strong load capacity, and the wing arm of the rotor structure is arranged on the second metal plate and the first end of the second wing beam, and the two rotors are rotatably supported at the two ends of the wing arm respectively, and the two motors are respectively arranged at the two ends of the wing arm, and one motor controls the rotation of one rotor, so that the wing assembly integrates the rotor fixed-wing function, so that the vertical take-off and landing fixed-wing UAV with the wing assembly of the utility model has both excellent hovering capability and a longer cruising speed and range. At the same time, the second end of the first spar of the fixed-wing structure of the wing assembly of the utility model is provided with a first metal plate, the first end of the second spar of the fixed-wing structure of the wing assembly is provided with a second metal plate, the first end of the second spar of the fixed-wing structure is provided with a second metal plate, and the wing arm supporting the two rotors is provided on the second metal plate and the first end of the second spar. The metal plate can enhance the structural strength of the spar, so that the structural strength of the supporting wing arm is high, ensuring the stability of the wing arm support on the fixed-wing structure, thereby making the operation stable and reliable. In addition, the first metal plate on the first spar of the utility model and the second metal plate on the second spar are detachably connected so that the angle between the first spar and the second spar can be adjusted, so that the angle between the first spar and the second spar of the fixed-wing structure can be adjusted according to the use environment and load requirements, so as to better meet the different use conditions of the drone, with a wider range of use and strong versatility.

[0008] A further solution is that the number of second metal plates is two, the two second metal plates are arranged side by side at the first end of the second wing beam, and a clamping groove is formed between the two second metal plates, and each second metal plate is provided with two second connecting ears at one end close to the first wing beam, and each second connecting ear is penetrated by a second connecting hole; the mounting end of the first metal plate is inserted into the clamping groove, and the mounting end of the first metal plate is provided with two first connecting ears, and each first connecting ear is penetrated by a first connecting hole, and a pin shaft is inserted into a second connecting hole, a first connecting hole and another second connecting hole in sequence.

[0009] A further solution is that the first wing beam includes a first foam plate, a first carbon fiber rib and a second carbon fiber rib, the first carbon fiber rib and the second carbon fiber rib are clamped at both ends of the first foam plate in the height direction of the first wing rib, and part of the first wing rib is arranged in parallel and side by side on the first foam plate; and / or, the second wing beam includes a second foam plate, a third carbon fiber rib and a fourth carbon fiber rib, the third carbon fiber rib and the fourth carbon fiber rib are clamped at both ends of the second foam plate in the height direction of the second wing rib, and part of the second wing rib is arranged in parallel and side by side on the second foam plate.

[0010] A further solution is that the fixed-wing structure also includes a first reinforcing rib, which is connected to the front ends of the multiple first wing ribs; and / or the fixed-wing structure also includes a second reinforcing rib, which is connected to the rear ends of the multiple first wing ribs; and / or the fixed-wing structure also includes a third reinforcing rib, which is connected to the front ends of the multiple second wing ribs; and / or the fixed-wing structure also includes a fourth reinforcing rib, which is connected to the rear ends of the multiple second wing ribs.

[0011] A further solution is that the fixed-wing structure also includes a first support frame, the first support frame is located between the front end of the first wing rib and the first wing spar, and multiple first wing ribs are supported on the first support frame; and / or, the fixed-wing structure also includes a second support frame, the second support frame is located between the rear end of the first wing rib and the first wing spar, and multiple first wing ribs are supported on the second support frame; and / or, the fixed-wing structure also includes a third support frame, the third support frame is located between the front end of the second wing rib and the second wing spar, and multiple second wing ribs are supported on the third support frame; and / or, the fixed-wing structure also includes a fourth support frame, the fourth support frame is located between the rear end of the second wing rib and the second wing spar, and multiple second wing ribs are supported on the fourth support frame.

[0012] A further solution is that the fixed-wing structure also includes a plurality of third ribs, which are arranged in parallel and side by side on the second end of the second spar away from the second rib, one end of the fourth support frame away from the first spar is connected to the rear end of the plurality of third ribs, and the length of the plurality of third ribs gradually decreases from the first end close to the second rib toward the second end away from the second rib, and the second skin is covered between the windward surface of the plurality of third ribs and the second spar.

[0013] A further solution is that the fixed-wing structure also includes a plurality of aileron ribs and aileron beams, the plurality of aileron ribs are arranged in parallel and side by side on the aileron beam, the aileron rib located at the first end of the aileron beam can be selectively glued to the rear end surface of the second wing rib close to the third wing rib, the front end of the aileron rib can be selectively glued to the fourth support frame, one aileron rib is arranged corresponding to one third wing rib, and the length of the plurality of aileron ribs gradually decreases from the first end close to the second wing rib toward the second end away from the second wing rib.

[0014] A further solution is that the fixed-wing structure further includes a fifth reinforcing rib, and the fifth reinforcing rib is connected to the rear ends of the plurality of aileron ribs.

[0015] A further solution is that the first wing rib is made of a material composed of balsa wood and fiberglass sheets adhered to both sides of the balsa wood; and / or, the first wing rib is penetrated by a plurality of first through grooves of the same or different shapes; and / or, the second wing rib is made of a material composed of balsa wood and fiberglass sheets adhered to both sides of the balsa wood; and / or, the second wing rib is penetrated by a plurality of second through grooves of the same or different shapes; and / or, the first metal plate is penetrated by a plurality of third through grooves of the same or different shapes; and / or, the second metal plate is penetrated by a plurality of fourth through grooves of the same or different shapes; and / or, the first skin is made of aviation plywood; and / or, the second skin is made of aviation plywood.

[0016] In order to achieve the second purpose of the utility model, the utility model provides a vertical take-off and landing fixed-wing UAV, including a fuselage and two sets of wing assemblies, the two sets of wing assemblies are respectively arranged on opposite sides of the fuselage, and the two sets of wing assemblies are symmetrically arranged about the fuselage, and each set of wing assemblies is the above-mentioned wing assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural diagram from the first perspective of an embodiment of the wing assembly of the utility model.

[0018] Figure 2 It is a structural diagram from a second viewing angle of an embodiment of the wing assembly of the utility model.

[0019] Figure 3 It is a first partial structural diagram of the fixed wing structure in the wing assembly embodiment of the utility model.

[0020] Figure 4 It is the first partial exploded view of the fixed wing structure in the wing assembly embodiment of the utility model.

[0021] Figure 5 It is a partial structural exploded view of the cooperation between the first wing spar and the first wing rib in the embodiment of the wing assembly of the utility model.

[0022] Figure 6 It is a second partial structural diagram of the fixed wing structure in the wing assembly embodiment of the utility model.

[0023] Figure 7 It is a second partial exploded view of the fixed wing structure in the wing assembly embodiment of the utility model.

[0024] Figure 8 It is a partial structural exploded view of the cooperation between the second wing spar and the second wing rib in the embodiment of the wing assembly of the utility model.

[0025] Fig. 9 It is the third partial structural diagram of the fixed wing structure in the wing assembly embodiment of the utility model.

[0026] Fig.10 It is a structural diagram of the cooperation between the aileron rib and the aileron beam in the embodiment of the wing assembly of the utility model.

[0027] The present invention will be further described below with reference to the accompanying drawings and embodiments. DETAILED DESCRIPTION

[0028] See also Figures 1 to 8 The present embodiment discloses a wing assembly 10 of a vertical take-off and landing fixed-wing UAV. Specifically, the vertical take-off and landing fixed-wing UAV of the present embodiment includes a fuselage and two sets of wing assemblies 10. The two sets of wing assemblies 10 are respectively arranged on opposite sides of the fuselage, and the two sets of wing assemblies 10 are symmetrically arranged with respect to the fuselage.

[0029] The wing assembly 10 of this embodiment includes a rotor structure 13 and a fixed-wing structure 11. The fixed-wing structure 11 includes a first spar 112, a plurality of first wing ribs 111, a first skin 113, a first metal plate 122, a second spar 116, a plurality of second wing ribs 117, a second skin 118 and a second metal plate 125. The plurality of first wing ribs 111 are arranged in parallel and side by side on the first spar 112. The first skin 113 is covered between the windward surface of the plurality of first wing ribs 111 and the first spar 112. The first end of the first spar 112 is used to be connected to the fuselage of the vertical take-off and landing fixed-wing UAV, and the first metal plate 122 is arranged at the second end of the first spar 112. Furthermore, in this embodiment, a plurality of second ribs 117 are arranged in parallel and side by side on the second spar 116, and the length of the plurality of second ribs 117 gradually decreases from the first end of the second spar 116 toward the second end of the second spar 116, the second skin 118 is covered between the windward surface of the plurality of second ribs 117 and the second spar 116, the second metal plate 125 is arranged at the first end of the second spar 116, and the second metal plate 125 is detachably connected to the first metal plate 122, so that the angle between the first spar 112 and the second spar 116 can be adjusted. In addition, the rotor structure 13 of this embodiment includes a wing arm 131, two rotors 132 and two motors, the wing arm 131 is arranged on the second metal plate 125 and the first end of the second spar 116 in parallel with the first rib 111, the two rotors 132 are rotatably supported at the two ends of the wing arm 131, the two motors are arranged at the two ends of the wing arm 131, and one motor controls the rotation of one rotor 132.

[0030] It can be seen that the wing assembly 10 of the present embodiment includes a rotor structure 13 and a fixed-wing structure 11, and a plurality of first wing ribs 111 of the fixed-wing structure 11 are arranged in parallel and side by side on the first wing beam 112, and a plurality of second wing ribs 117 are arranged in parallel and side by side on the second wing beam 116, so that the fixed-wing structure 11 of the present embodiment is a hollow truss-type large aspect ratio wing structure, which makes it ultra-light and has a strong load capacity, and the wing arm 131 of the rotor structure 13 is arranged on the second metal plate 125 and the first end of the second wing beam 116, and the two rotors 132 are rotatably supported at the two ends of the wing arm 131, respectively, and two motors are respectively arranged at the two ends of the wing arm 131, and one motor controls the rotation of one rotor 132, so that the wing assembly 10 integrates the fixed-wing function of the rotor 132, so that the vertical take-off and landing fixed-wing UAV with the wing assembly 10 of the present embodiment has both excellent hovering capability and a longer cruising speed and range. At the same time, a first metal plate 122 is provided at the second end of the first spar 112 of the fixed-wing structure 11 of the wing assembly 10 of the present embodiment, a second metal plate 125 is provided at the first end of the second spar 116 of the fixed-wing structure 11 of the wing assembly 10, a second metal plate 125 is provided at the first end of the second spar 116 of the fixed-wing structure 11, and a second metal plate 125 is provided at the first end of the second spar 116 of the fixed-wing structure 11. A wing arm 131 supporting two rotors 132 is provided on the second metal plate 125 and the first end of the second spar 116. The metal plate can enhance the structural strength of the spar, thereby making the structural strength of the supporting wing arm 131 high, ensuring the stability of the wing arm 131 supported on the fixed-wing structure 11, thereby making the operation stable and reliable. In addition, in this embodiment, the first metal plate 122 on the first wing beam 112 and the second metal plate 125 on the second wing beam 116 can be detachably connected so that the angle between the first wing beam 112 and the second wing beam 116 can be adjusted. Therefore, the angle between the first wing beam 112 and the second wing beam 116 of the fixed-wing structure 11 can be adjusted according to the use environment and load requirements, so as to better meet the different use conditions of the UAV, with a wider range of use and strong versatility.

[0031] Specifically, in this embodiment, the number of the second metal plates 125 on the second wing beam 116 is two, the two second metal plates 125 are arranged side by side at the first end of the second wing beam 116, and a clamping groove 1253 is formed between the two second metal plates 125, and each second metal plate 125 is provided with two second connecting ears 1251 at one end close to the first wing beam 112, and each second connecting ear 1251 is penetrated by a second connecting hole 1252, and the mounting end of the first metal plate 122 is inserted into the clamping groove 1253, and the mounting end of the first metal plate 122 on the first wing beam 112 is provided with two first connecting ears 1221, and each first connecting ear 1221 is penetrated by a first connecting hole 1222, and a pin shaft is inserted into a second connecting hole 1252, a first connecting hole 1222 and another second connecting hole 1252 in sequence. When it is necessary to disassemble and adjust the angle, knock the pin out from one second connection hole 1252, one first connection hole 1222 and another second connection hole 1252, then the angle between the first wing beam 112 and the second wing beam 116 can be adjusted to the desired angle value, and then the pin is inserted into one second connection hole 1252, one first connection hole 1222 and another second connection hole 1252 in sequence for connection and installation, so that the second metal plate 125 and the first metal plate 122 can be detachably connected. In addition, the means for detachably connecting the second metal plate 125 and the first metal plate 122 is optionally that the second metal plate 125 and the first metal plate 122 are connected by screws or bolts. Specifically, in this embodiment, the second metal plate 125 and the first metal plate 122 are both aviation aluminum plates, so they are light in weight while ensuring structural strength.

[0032] In order to further reduce the weight while ensuring high structural strength and structural stability, the first wing spar 112 of the present embodiment includes a first foam plate 1121, a first carbon fiber rib 1122 and a second carbon fiber rib 1123, the first carbon fiber rib 1122 and the second carbon fiber rib 1123 are clamped at both ends of the first foam plate 1121 in the height direction of the first wing rib 111, and part of the first wing rib 111 is arranged in parallel and side by side on the first foam plate 1121, and the second wing spar 116 of the present embodiment includes a second foam plate 1161, a third carbon fiber rib 1162 and a fourth carbon fiber rib 1163, the third carbon fiber rib 1162 and the fourth carbon fiber rib 1163 are clamped at both ends of the second foam plate 1161 in the height direction of the second wing rib 117, and part of the second wing rib 117 is arranged in parallel and side by side on the second foam plate 1161. Specifically, the first foam board 1121 of the present embodiment is penetrated by a plurality of first mounting grooves 11211, a portion of the first wing rib 111 includes a first front wing 1111 and a first rear wing 1112, the front end of the first rear wing 1112 is protrudingly provided with two first plug-in portions 11121, the two first plug-in portions 11121 of a first rear wing 1112 are plugged into a first mounting groove 11211, a rear end of the first front wing 1111 is protrudingly provided with a second plug-in portion 11111, the second plug-in portion 11111 is plugged into the first plug-in groove 11122 between the two first plug-in portions 11121, thereby a portion of the first wing rib 111 is installed on the first foam board 1121 by splicing. In addition, the second foam board 1161 of the present embodiment is penetrated with a plurality of second mounting grooves 11611, and a portion of the second wing rib 117 includes a second front wing 1171 and a second rear wing 1172. The rear end of the second front wing 1171 is protrudingly provided with two third plug-in portions 11711, and the two third plug-in portions 11711 of a second front wing 1171 are plugged into a second mounting groove 11611, and the front end of the second rear wing 1172 is protrudingly provided with a fourth plug-in portion 11721, and the fourth plug-in portion 11721 is plugged into the second plug-in groove 11712 between the two third plug-in portions 11711, thereby mounting a portion of the second wing rib 117 on the second foam board 1161 by splicing.

[0033] In order to enhance the structural strength and stability, the fixed-wing structure 11 of the present embodiment further includes a first reinforcing rib 124, which is connected to the front ends of the plurality of first ribs 111. The fixed-wing structure 11 of the present embodiment further includes a second reinforcing rib 114, which is connected to the rear ends of the plurality of first ribs 111. The fixed-wing structure 11 of the present embodiment further includes a third reinforcing rib 126, which is connected to the front ends of the plurality of second ribs 117. The fixed-wing structure 11 of the present embodiment further includes a fourth reinforcing rib 121, which is connected to the rear ends of the plurality of second ribs 117. In order to reduce weight, the first reinforcing rib 124, the second reinforcing rib 114, the third reinforcing rib 126 and the fourth reinforcing rib 121 of the present embodiment are all carbon fiber tubes.

[0034] In order to further enhance the structural strength and stability, the fixed-wing structure 11 of the present embodiment further includes a first support frame 123, which is located between the front end of the first wing rib 111 and the first wing spar 112, and multiple first wing ribs 111 are supported on the first support frame 123. The fixed-wing structure 11 of the present embodiment further includes a second support frame 115, which is located between the rear end of the first wing rib 111 and the first wing spar 112, and multiple first wing ribs 111 are supported on the second support frame 115. The fixed-wing structure 11 of the present embodiment further includes a third support frame 127, which is located between the front end of the second wing rib 117 and the second wing spar 116, and multiple second wing ribs 117 are supported on the third support frame 127. The fixed-wing structure 11 of the present embodiment further includes a fourth support frame 120, which is located between the rear end of the second wing rib 117 and the second wing spar 116, and multiple second wing ribs 117 are supported on the fourth support frame 120.

[0035] In order to increase the aspect ratio to improve the load capacity, the fixed-wing structure 11 of this embodiment also includes a plurality of third ribs 119, which are arranged in parallel and side by side on the second end of the second spar 116 away from the second rib 117, and the end of the fourth support frame 120 away from the first spar 112 is connected to the rear end of the plurality of third ribs 119, and the length of the plurality of third ribs 119 gradually decreases from the first end close to the second rib 117 toward the second end away from the second rib 117, the second skin 118 is covered between the windward surface of the plurality of third ribs 119 and the second spar 116, and the end of the third reinforcing rib 126 away from the first spar 112 is connected to the front end of the plurality of third ribs 119.

[0036] See also Figures 9 and 10In order to improve working stability and reliability, the fixed-wing structure 11 of this embodiment further includes a plurality of aileron ribs 129 and aileron beams 1210. The plurality of aileron ribs 129 are arranged in parallel on the aileron beams 1210. The aileron ribs 129 at the first end of the aileron beams 1210 can be selectively glued to the rear end side of the second rib 117 close to the third rib 119. The front end of the aileron ribs 129 can be selectively glued to the fourth support frame 120. One aileron rib 129 is arranged corresponding to one third rib 119, and the lengths of the plurality of aileron ribs 129 gradually decrease from the first end close to the second rib 117 toward the second end away from the second rib 117. Specifically, the fixed-wing structure 11 of this embodiment further includes a fifth reinforcing rib 1211, which is connected to the rear ends of the plurality of aileron ribs 129, thereby improving the structural strength and stability of the plurality of ailerons. Among them, the fifth reinforcing rib 1211 of this embodiment is a carbon fiber tube.

[0037] In order to further reduce the weight, the first wing rib 111 of the present embodiment is made of a material composed of balsa wood and glass fiber sheets adhered to both sides of the balsa wood, the second wing rib 117 of the present embodiment is made of a material composed of balsa wood and glass fiber sheets adhered to both sides of the balsa wood, the third wing rib 119 of the present embodiment is made of a material composed of balsa wood and glass fiber sheets adhered to both sides of the balsa wood, the aileron rib 129 of the present embodiment is made of a material composed of balsa wood and glass fiber sheets adhered to both sides of the balsa wood, the first skin 113 of the present embodiment is made of aviation plywood, and the second skin 118 is made of aviation plywood. In addition, the first rib 111 of the present embodiment is penetrated by a plurality of first through slots of the same or different shapes, the second rib 117 of the present embodiment is penetrated by a plurality of second through slots of the same or different shapes, the first metal plate 122 of the present embodiment is penetrated by a plurality of third through slots of the same or different shapes, the second metal plate 125 of the present embodiment is penetrated by a plurality of fourth through slots of the same or different shapes, the third rib 119 of the present embodiment is penetrated by a plurality of fifth through slots of the same or different shapes, the first support frame 123 of the present embodiment is penetrated by a plurality of sixth through slots of the same or different shapes, the second support frame 115 of the present embodiment is penetrated by a plurality of seventh through slots of the same or different shapes, the third support frame 127 of the present embodiment is penetrated by a plurality of eighth through slots of the same or different shapes, and the fourth support frame 120 of the present embodiment is penetrated by a plurality of ninth through slots of the same or different shapes.

[0038] The above embodiments are only preferred examples of the present invention and are not intended to limit the scope of implementation of the present invention. Therefore, any equivalent changes or modifications made based on the structure, features and principles of the present invention should be included in the scope of the present invention patent application.

Claims

1. A wing assembly, comprising a rotor structure and a fixed wing structure, characterized in that: The fixed-wing structure comprises a first spar, a plurality of first ribs, a first skin, a first metal plate, a second spar, a plurality of second ribs, a second skin and a second metal plate, wherein the plurality of first ribs are arranged in parallel and side by side on the first spar, the first skin is covered between the windward surface of the plurality of first ribs and the first spar, the first end of the first spar is used to be connected to the fuselage, and the first metal plate is arranged at the second end of the first spar; A plurality of the second ribs are arranged in parallel on the second spar, and the lengths of the plurality of the second ribs gradually decrease from the first end of the second spar toward the second end of the second spar, the second skin is covered between the windward surface of the plurality of the second ribs and the second spar, the second metal plate is arranged at the first end of the second spar, and the second metal plate is detachably connected to the first metal plate, so that the angle between the first spar and the second spar can be adjusted; The rotor structure includes a wing arm, two rotors and two motors. The wing arm is arranged on the second metal plate and the first end of the second wing beam in parallel with the first wing rib. The two rotors are rotatably supported at both ends of the wing arm, respectively. The two motors are respectively arranged at both ends of the wing arm, and one motor controls the rotation of one rotor.

2. The wing assembly according to claim 1, characterized in that: There are two second metal plates, the two second metal plates are arranged side by side at the first end of the second spar, and a clamping groove is formed between the two second metal plates. Each of the second metal plates is provided with two second connecting ears at one end close to the first spar, and each of the second connecting ears is penetrated by a second connecting hole. The mounting end of the first metal plate is inserted into the clamping groove, and the mounting end of the first metal plate is provided with two first connecting ears, each of the first connecting ears is penetrated by a first connecting hole, and a pin shaft is inserted into one of the second connecting holes, one of the first connecting holes and another of the second connecting holes in sequence.

3. The wing assembly according to claim 1, characterized in that: The first spar includes a first foam plate, a first carbon fiber rib and a second carbon fiber rib, the first carbon fiber rib and the second carbon fiber rib are clamped at two ends of the first foam plate in the height direction of the first rib, and part of the first rib is arranged parallel to the first foam plate; And / or, the second wing beam includes a second foam board, a third carbon fiber rib and a fourth carbon fiber rib, the third carbon fiber rib and the fourth carbon fiber rib are clamped at both ends of the second foam board in the height direction of the second wing rib, and part of the second wing rib is arranged in parallel and side by side on the second foam board.

4. The wing assembly according to claim 1, characterized in that: The fixed wing structure further includes a first reinforcing rib, wherein the first reinforcing rib is connected to the front ends of the plurality of first wing ribs; And / or, the fixed-wing structure further comprises a second reinforcing rib, wherein the second reinforcing rib is connected to the rear ends of the plurality of first wing ribs; And / or, the fixed-wing structure further comprises a third reinforcing rib, wherein the third reinforcing rib is connected to the front ends of the plurality of second wing ribs; And / or, the fixed-wing structure further includes a fourth reinforcing rib, wherein the fourth reinforcing rib is connected to the rear ends of the plurality of second wing ribs.

5. The wing assembly according to claim 1, characterized in that: The fixed-wing structure further includes a first support frame, the first support frame is located between the front end of the first wing rib and the first wing spar, and a plurality of the first wing ribs are supported on the first support frame; And / or, the fixed-wing structure further comprises a second support frame, the second support frame is located between the rear end of the first wing rib and the first wing spar, and a plurality of the first wing ribs are supported on the second support frame; And / or, the fixed-wing structure further comprises a third support frame, the third support frame is located between the front end of the second wing rib and the second wing spar, and a plurality of the second wing ribs are supported on the third support frame; And / or, the fixed-wing structure further includes a fourth support frame, the fourth support frame is located between the rear end of the second wing rib and the second wing beam, and a plurality of the second wing ribs are supported on the fourth support frame.

6. The wing assembly according to claim 5, characterized in that: The fixed-wing structure also includes a plurality of third ribs, which are arranged in parallel and side by side on the second end of the second wing beam away from the second wing rib, and one end of the fourth support frame away from the first wing beam is connected to the rear ends of the plurality of third wing ribs, and the lengths of the plurality of third wing ribs gradually decrease from the first end close to the second wing rib toward the second end away from the second wing rib, and the second skin is covered between the windward surfaces of the plurality of third wing ribs and the second wing beam.

7. The wing assembly according to claim 6, characterized in that: The fixed-wing structure also includes a plurality of aileron ribs and aileron beams, wherein the plurality of aileron ribs are arranged in parallel and side by side on the aileron beam, the aileron rib located at the first end of the aileron beam can be selectively glued to the rear end side of the second wing rib close to the third wing rib, and the front end of the aileron rib can be selectively glued to the fourth support frame, one aileron rib is arranged corresponding to one third wing rib, and the lengths of the plurality of aileron ribs gradually decrease from the first end close to the second wing rib toward the second end away from the second wing rib.

8. The wing assembly according to claim 7, characterized in that: The fixed-wing structure further includes a fifth reinforcing rib connected to rear ends of the plurality of aileron ribs.

9. The wing assembly according to any one of claims 1 to 8, characterized in that: The first wing rib is made of a material formed by stacking balsa wood and glass fiber sheets attached to two sides of the balsa wood; And / or, the first wing rib is penetrated by a plurality of first through grooves of the same or different shapes; And / or, the second wing rib is made of a material formed by stacking balsa wood and glass fiber sheets attached to two sides of the balsa wood; And / or, the second wing rib is penetrated by a plurality of second through grooves of the same or different shapes; And / or, the first metal plate is penetrated by a plurality of third through slots of the same or different shapes; And / or, the second metal plate is penetrated by a plurality of fourth through slots of the same or different shapes; And / or, the first skin is made of aviation ply; And / or, the second skin is made of aviation ply.

10. A vertical take-off and landing fixed-wing UAV, comprising a fuselage and two sets of wing assemblies, wherein the two sets of wing assemblies are respectively arranged on opposite sides of the fuselage, and the two sets of wing assemblies are symmetrically arranged about the fuselage, characterized in that: Each group of wing components is a wing component as claimed in any one of claims 1 to 9.

Images