A compound wing unmanned aerial vehicle
By designing protrusions, buffer plates, shock-absorbing springs, and deflectors on the compound-wing UAV, the impact force problem during landing was solved, improving the service life and flight stability of the equipment and enhancing its cargo carrying capacity.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- 华启天成(深圳)智能科技有限公司
- Filing Date
- 2025-08-13
- Publication Date
- 2026-07-07
AI Technical Summary
When a compound-wing UAV lands, excessive speed or improper handling can cause excessive impact force at the moment of contact with the ground, leading to deformation or breakage of the landing gear, cracks in the fuselage frame, damage to internal electronic equipment, and a shortened service life.
The system employs protrusions and buffer plates to reduce instantaneous impact force, and shock-absorbing springs inside the outriggers further mitigate the impact force. The support columns further reduce the impact force transmitted to the main wing. Combined with the deflector design, the system reduces flight drag and wind resistance, thereby improving the service life of the equipment.
It effectively reduces the impact force when the compound wing UAV lands, protects internal components, extends the service life of the equipment, and enhances flight stability and cargo carrying capacity.
Smart Images
Figure CN224466135U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a compound wing UAV. Background Technology
[0002] A compound wing UAV is a type of UAV that integrates multiple wing designs or flight modes. Through structural innovation, it achieves switching between different flight states and combines the advantages of multiple aircraft, exhibiting a more balanced performance in terms of endurance, speed, and takeoff and landing capabilities.
[0003] In related technologies, compound flying wings, also known as coupled wings, are a new type of aircraft wing layout with characteristics different from conventional aircraft. Its mainstream shape includes a main wing at the front of the UAV fuselage and a tail fin at the rear. The main fuselage integrates the flight control system, battery, and mission payload (such as mapping cameras and communication modules). The flight control system is the "brain," coordinating the switching between fixed-wing and multi-rotor modes and attitude control. The battery provides power for the entire aircraft. It can carry functional modules such as reconnaissance, logistics, and mapping. The landing gear is located at the bottom of the fuselage, and its landing gear is mostly a symmetrical outward-pointing V-shaped bracket.
[0004] Compound-wing UAVs are generally heavier than multi-rotor UAVs. When they are recovered and landed after completing their mission, if the landing speed is too fast or the handling angle is improper, the impact force when the fuselage contacts the ground will increase, usually resulting in turbulence. This can lead to deformation or breakage of the landing gear brackets, or cracks in the fuselage frame. It can also cause varying degrees of damage to the electronic equipment inside the fuselage, thus shortening the service life of the equipment. To solve the above problems, a compound-wing UAV is proposed. Utility Model Content
[0005] In view of this, the present invention provides a compound wing UAV. The present invention reduces the instantaneous impact force on the support legs through protrusions and buffer plates, and further reduces the instantaneous impact force on the horizontal guide plate through the shock-absorbing springs installed in the support legs. Finally, the impact force is further reduced by the support column and transmitted to the main wing. In this way, the impact force on the internal components of the main fuselage during landing is reduced, thereby improving the service life of the equipment.
[0006] To solve the above-mentioned technical problems, this utility model provides a compound wing unmanned aerial vehicle (UAV), including a main wing arranged laterally at the front of the main fuselage, vertical elevators arranged on the left and right sides of the upper part of the main wing, a tail wing arranged at the upper part of the rear of the main fuselage, a guide plate at the bottom of each vertical elevator, a support column at the bottom of each guide plate, a horizontal guide plate at the bottom of each support column, a buffer component at the front and rear ends of the bottom of each horizontal guide plate, and an auxiliary support component arranged at the lower rear of the main fuselage, which is connected to the tail of the two horizontal guide plates.
[0007] The front and rear ends of the guide plate adopt a flow-guiding design to reduce the flight resistance of the UAV. A connecting plate is fixedly installed on the lower surface of the guide plate. The connecting plate is used to connect the guide plate to the support column, and the lower surface of the connecting plate is connected to the top of the support column.
[0008] The horizontal guide vane is designed at both ends to reduce the flight drag of the drone, and each support column is fixed to the front of the horizontal guide vane on the same side.
[0009] Each buffer component includes a guide shell connected to a horizontal deflector plate. The guide shell protects the shock-absorbing springs. Each guide shell has a foot at its bottom, which increases the contact area between the landing gear and the ground, thus facilitating the landing of the main fuselage. The foot is hollow trapezoidal, narrower at the top and wider at the bottom. Multiple shock-absorbing springs are installed inside the guide shell to reduce the impact force generated during landing and transmit it to the guide shell.
[0010] Each foot has a buffer plate at its bottom, which is used to reduce the instantaneous impact force between the drone and the ground when it lands. Each buffer plate has several protrusions at its bottom, which are used to increase the friction between the buffer plate and the ground.
[0011] The auxiliary support includes a connecting rod fixed to the lower rear of the main fuselage. The connecting rod is used to connect the balance plate to the main fuselage. The balance plate is located at the bottom of the connecting rod and is used to assist the rear balance of the main fuselage during flight. There is a connecting post at both ends of the balance plate. The connecting post is used to connect the balance plate to the horizontal deflector, thereby connecting the rear of the horizontal deflector to the main fuselage. This allows items to be mounted on the middle of the horizontal deflector. Each connecting post is connected to the horizontal deflector on the same side.
[0012] Several air ducts are installed throughout the balance plate. These air ducts are used to reduce wind resistance during flight, and the air intakes of the air ducts face the nose of the main fuselage.
[0013] In summary, compared with the prior art, this application includes at least one of the following beneficial technical effects:
[0014] 1. The instantaneous impact force is reduced to the outriggers by the protrusions and buffer plates. Then, the shock-absorbing springs installed inside the outriggers further reduce the instantaneous impact force to the horizontal guide plate. Finally, the impact force is further reduced by the support column and transmitted to the main wing. This reduces the impact force on the internal components of the main fuselage during landing, thereby improving the service life of the equipment.
[0015] 2. The connecting rod is used to connect the balance plate to the main fuselage. The balance plate is used to assist the main fuselage in maintaining rear balance during flight. The connecting column is used to connect the balance plate to the horizontal deflector, thereby connecting the rear of the horizontal deflector to the main fuselage. This allows items to be mounted on the middle of the horizontal deflector, improving the practicality of the component.
[0016] 3. The air duct is used to reduce wind resistance during the flight of the main fuselage, thereby stabilizing the flight attitude of the compound wing UAV. Attached Figure Description
[0017] Figure 1 This is a schematic diagram of the main structure of this utility model;
[0018] Figure 2 This is a side view of the structure of this utility model;
[0019] Figure 3 This is a front sectional view of the present invention;
[0020] Figure 4 This is a side sectional view of the present invention;
[0021] Figure 5 This utility model Figure 4 A magnified view of part A.
[0022] Explanation of reference numerals in the attached drawings: 100, main fuselage; 101, main wing; 102, vertical lift wing; 103, tail fin; 200, air deflector; 201, support column; 202, horizontal air deflector; 203, connecting plate; 300, buffer component; 301, air deflector shell; 302, support leg; 303, shock absorber spring; 304, buffer plate; 305, protrusion; 400, auxiliary support; 401, connecting rod; 402, balance plate; 403, connecting column; 404, air duct. Detailed Implementation
[0023] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the following will be described in conjunction with the accompanying drawings of the embodiments of this utility model. Figure 1-5 The technical solutions of the embodiments of this utility model are clearly and completely described below. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the described embodiments of this utility model are within the protection scope of this utility model.
[0024] like Figure 1-5As shown: This embodiment provides a compound-wing unmanned aerial vehicle (UAV), including a main wing 101 horizontally arranged at the front of the main fuselage 100, a vertical lift wing 102 respectively arranged on the left and right sides of the upper part of the main wing 101, the vertical lift wing 102 being rotatably fixed to the main wing 101, and a tail wing 103 arranged at the upper rear of the main fuselage 100. Each vertical lift wing 102 has a guide plate 200 at its bottom, the guide plate 200 being detachably connected to the main wing 101, and each guide plate 200 has a support column 201 at its bottom. The support column 201 can be made of a material with high elastic strength. Each support column 201 has a horizontal guide plate 202 at its bottom. The horizontal guide plate 202 can be made of a material with strong shock resistance. Each horizontal guide plate 202 has a buffer component 300 at both the front and rear ends at its bottom. The buffer component 300 is detachably connected to the horizontal guide plate 202. An auxiliary support 400 is provided at the lower rear of the main body 100. The auxiliary support 400 is used to improve the balance of the UAV during flight. The auxiliary support 400 is connected to the tail of the two horizontal guide plates 202.
[0025] During use, the instantaneous impact force is reduced to the support leg 302 by the protrusion 305 and the buffer plate 304, and then further reduced to the horizontal guide plate 202 by the shock-absorbing spring 303 installed in the support leg 302. Finally, the impact force is reduced again by the support column 201 and transmitted to the main wing 101, thereby reducing the impact force on the internal components of the main fuselage 100 during landing and thus improving the service life of the equipment.
[0026] This embodiment provides a compound-wing unmanned aerial vehicle (UAV).
[0027] like Figure 1 , 2 As shown in Figures 4 and 5: The front and rear ends of the guide plate 200 adopt a flow-guiding design to reduce the flight drag of the UAV. A connecting plate 203 is fixedly installed on the lower surface of the guide plate 200. The guide plate 200 and the connecting plate 203 can be fixed by riveting. The connecting plate 203 also adopts a gas flow-guiding design. The connecting plate 203 is used to connect the guide plate 200 to the support column 201. The lower surface of the connecting plate 203 is connected to the top of the support column 201. The front and rear ends of the horizontal guide plate 202 adopt a flow-guiding design to reduce the flight drag of the UAV. The support column 201 can be made of rubber. Each support column 201 is fixed to the front of the horizontal guide plate 202 on the same side. The bottom of the connecting plate 203 can be heat-fused to the upper end of the support column 201. The lower end of the support column 201 is heat-fused to the horizontal guide plate 202.
[0028] Its effect is as follows: the connecting plate 203 is used to connect the guide vertical plate 200 to the support column 201. Both the guide vertical plate 200 and the horizontal guide plate 202 adopt gas guiding design, which can reduce the drag encountered by the UAV during flight.
[0029] like Figure 1 , 2 As shown in Figures 4 and 5: Each buffer component 300 includes a flow guide shell 301 connected to the horizontal flow guide plate 202. The horizontal flow guide plate 202 and the flow guide shell 301 can be fixed by bolts. The surface of the flow guide shell 301 is designed for lightweighting. This shell adopts a gas flow guiding design. The flow guide shell 301 is used to protect the shock absorption spring 303. Each flow guide shell 301 has a support foot 302 at its bottom. The support foot 302 is fixed to the flow guide shell 301 by heat fusion connection. The outrigger 302 is used to increase the contact area between the landing gear and the ground, thereby facilitating the landing of the main fuselage 100 on the ground. The outrigger 302 is hollow trapezoidal, narrow at the top and wide at the bottom. Multiple shock-absorbing springs 303 are installed inside the airflow guide shell 301. The shock-absorbing springs 303 are equipped with damping elements. The upper and lower ends of the shock-absorbing springs 303 are connected and fixed to the inner wall of the airflow guide shell 301. The shock-absorbing springs 303 are used to reduce the impact force generated during landing and transmit it to the airflow guide shell 301.
[0030] Its effects are as follows: the air guide shell 301 is used to protect the shock-absorbing spring 303, the support leg 302 is used to increase the contact area between the landing gear and the ground, thereby making it easier for the main fuselage 100 to land on the ground, and the shock-absorbing spring 303 is used to reduce the impact force generated during landing and transmit it to the air guide shell 301.
[0031] like Figure 1 , 2 As shown in Figures 4 and 5: Each support leg 302 has a buffer plate 304 at its bottom. The buffer plate 304 is preferably made of a rigid inner board material wrapped with an outer adhesive layer. The buffer plate 304 can be made of carbon fiber board with epoxy resin coating. The buffer plate 304 and the support leg 302 can be heat-fused together. The buffer plate 304 is used to reduce the instantaneous impact force between the UAV and the ground when landing. Each buffer plate 304 has several protrusions 305 at its bottom. The protrusions 305 and the buffer plate 304 can be integrally connected. The protrusions 305 are used to increase the friction between the buffer plate 304 and the ground.
[0032] Its effects are as follows: the buffer plate 304 is used to reduce the instantaneous impact force between the drone and the ground when it lands, and the protrusion 305 is used to increase the friction between the buffer plate 304 and the ground.
[0033] like Figure 1 , 2As shown in Figures 3 and 4: The auxiliary support 400 includes a connecting rod 401 fixed to the lower rear of the main fuselage 100. The connecting rod 401 and the main fuselage 100 can be connected by heat fusion. The connecting rod 401 is used to connect the balance plate 402 to the main fuselage 100. The balance plate 402 is provided at the bottom of the connecting rod 401. The balance plate 402 and the connecting rod 401 can be connected by heat fusion. The balance plate 402 is used to assist the balance of the rear of the main fuselage 100 during flight. A connecting post 403 is provided at both ends of the balance plate 402. The balance plate 402 and the connecting post 403 can be connected and fixed by bolts or heat fusion. The connecting post 403 is used to connect the balance plate 402 to the horizontal guide plate 202, thereby connecting the rear of the horizontal guide plate 202 to the main fuselage 100, and allowing items to be hung in the middle of the horizontal guide plate 202. Each connecting post 403 is connected to the horizontal guide plate 202 on the same side.
[0034] Its effects are as follows: the connecting rod 401 is used to connect the balance plate 402 to the main fuselage 100, the balance plate 402 is used to assist the main fuselage 100 in maintaining rear balance during flight, and the connecting column 403 is used to connect the balance plate 402 to the horizontal deflector 202, thereby connecting the rear of the horizontal deflector 202 to the main fuselage 100, and allowing items to be mounted on the middle of the horizontal deflector 202.
[0035] like Figure 1 , 2 As shown in Figure 3: Several air ducts 404 are provided through the balance plate 402. The air ducts 404 are used to reduce the wind resistance of the main fuselage 100 during flight. The air inlet of the air duct 404 faces the nose of the main fuselage 100.
[0036] Its effect is as follows: the air duct 404 is used to reduce the wind resistance of the main fuselage 100 during flight, thereby stabilizing the flight attitude of the compound wing UAV.
[0037] Working principle: When the compound wing UAV makes a vertical landing, the instantaneous impact force is reduced to the support leg 302 by the protrusion 305 and the buffer plate 304. Then, the shock-absorbing spring 303 installed in the support leg 302 further reduces the instantaneous impact force to the horizontal guide plate 202. Finally, the impact force is reduced again by the support column 201 and transmitted to the main wing 101. In this way, the impact force on the internal components of the main fuselage 100 during landing is reduced, and the electronic components inside the main fuselage 100 are protected, thereby improving the service life of the equipment.
[0038] Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.
[0039] The above description is the preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.
Claims
1. A compound-wing unmanned aerial vehicle (UAV), comprising a main wing (101) laterally arranged at the front of a main fuselage (100), vertical elevators (102) respectively arranged on the left and right sides of the upper part of the main wing (101), and a tail wing (103) arranged at the upper rear of the main fuselage (100), characterized in that: Each vertical lift wing (102) has a guide plate (200) at its bottom, each guide plate (200) has a support column (201) at its bottom, each support column (201) has a horizontal guide plate (202) at its bottom, and each horizontal guide plate (202) has a buffer component (300) at both the front and rear ends of its bottom. An auxiliary support (400) is provided below the rear of the main fuselage (100), and the auxiliary support (400) is connected to the tail of the two horizontal guide plates (202).
2. The compound-wing unmanned aerial vehicle as described in claim 1, characterized in that: The front and rear ends of the guide plate (200) adopt a guide design to reduce the flight resistance of the UAV. A connecting plate (203) is fixedly installed on the lower surface of the guide plate (200), and the lower surface of the connecting plate (203) is connected to the top of the support column (201).
3. A compound-wing unmanned aerial vehicle as described in claim 2, characterized in that: The horizontal guide plate (202) adopts a flow-guiding design at both ends to reduce the flight resistance of the UAV, and each of the support columns (201) is fixed to the front of the horizontal guide plate (202) on the same side.
4. A compound-wing unmanned aerial vehicle as described in claim 3, characterized in that: Each of the buffer components (300) includes a flow guide shell (301) connected to the horizontal flow guide plate (202). Each flow guide shell (301) has a support foot (302) at its bottom. The support foot (302) is hollow trapezoidal, narrow at the top and wide at the bottom. Multiple shock-absorbing springs (303) are provided inside the flow guide shell (301).
5. A compound-wing unmanned aerial vehicle as described in claim 4, characterized in that: Each of the legs (302) has a buffer plate (304) at its bottom, and each buffer plate (304) has a plurality of protrusions (305) at its bottom.
6. A compound-wing unmanned aerial vehicle as described in claim 5, characterized in that: The auxiliary support (400) includes a connecting rod (401) fixed to the lower rear of the main body (100). A balance plate (402) is provided at the bottom of the connecting rod (401). A connecting post (403) is provided at both the left and right ends of the balance plate (402). Each connecting post (403) is connected to the horizontal guide plate (202) on the same side.
7. A compound-wing unmanned aerial vehicle as described in claim 6, characterized in that: The balance plate (402) has several ventilation channels (404) running through it, and the ventilation channels (404) are directed toward the head of the main body (100).