Large fixed-wing unmanned aerial vehicle
By abolishing the pilot position of the fixed-wing drone and adopting a structure that combines the upper and lower wings, the problems of low cargo transportation volume and pilot safety hazards in the prior art are solved, and higher cargo carrying capacity and flight stability are achieved.
Patent Information
- Application Number
- CN202421759173.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-24
- Publication Date
- 2025-07-18
- Estimated Expiration
- 2034-07-24
AI Technical Summary
Existing fixed-wing drones require a pilot seat, which reduces the cargo transportation volume, and low-altitude flight requires high technical requirements for pilots and poses safety risks.
Design a drone, cancel the pilot position, adopt a structure that combines upper and lower wings, increases cargo carrying capacity, and achieves stable flight through specific layouts of power components, tail components and wheel sets.
It eliminates pilot safety hazards, reduces operational difficulty, and can carry more cargo, improving the transportation efficiency and safety of drones.
Smart Images
Figure CN223116627U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a large fixed-wing unmanned aerial vehicle. Background Art
[0002] Fixed-wing unmanned aerial vehicles have good low-altitude and low-speed flight characteristics and handling stability, have low takeoff and landing requirements, strong adaptability and applicability, and their application scope is very wide. For example, they are used for material distribution, emergency rescue in sparsely populated areas, special area supervision, medium and short-distance freight transportation in areas with inconvenient ground transportation and rich products, agricultural and forestry plant protection, forest and grassland fire inspection and monitoring, etc. However, the existing fixed-wing unmanned aerial vehicles all need to be provided with a driver's seat, and a pilot needs to operate on the fixed-wing unmanned aerial vehicle. Since the fixed-wing unmanned aerial vehicle is equipped with a driver, the cargo transportation volume is reduced. At the same time, the technical requirements for the pilot during low-altitude flight are high, and there are also certain safety hazards. Content of the Utility Model
[0003] The purpose of the utility model is to overcome the deficiencies of the prior art and provide a large fixed-wing unmanned aerial vehicle.
[0004] The purpose of the utility model is achieved by the following technical solutions:
[0005] A large fixed-wing unmanned aerial vehicle includes a fuselage, a hatch, a front wheel frame, a rear wheel frame, front wheels, rear wheels, a power assembly, a front wing assembly and a tail wing assembly. The power assembly for driving the fuselage to move is fixedly arranged at the front end of the fuselage. The tail wing assembly is fixedly arranged at the tail of the fuselage. The front wing assembly is fixedly arranged at the front of the fuselage. The rear wheels are fixedly arranged at the tail of the fuselage through the rear wheel frame. The front wheel frame is fixedly arranged at the front of the fuselage and is directly below the front wing assembly. Two front wheels are symmetrically arranged under the front wheel frame. The front wheels and the rear wheels are arranged on the same inclined plane, and the included angle θ between the inclined plane and the longitudinal axis of the fuselage is 11-13°.
[0006] Further, the front wing assembly includes an upper wing, an upper inner flap and an upper outer flap. The upper wings are symmetrically arranged on both sides of the upper part of the fuselage. The upper inner flap and the upper outer flap are arranged on the upper wing. The upper inner flap is arranged close to the fuselage side.
[0007] Further, the front wing assembly further includes a lower wing, a lower inner flap and a lower outer flap. The lower wings are symmetrically arranged on both sides of the lower part of the fuselage. The lower wings are arranged directly below the upper wings and the length of the lower wings is less than that of the upper wings. The lower inner flap and the lower outer flap are arranged on the lower wing. The lower inner flap is arranged close to the fuselage side.
[0008] Furthermore, the upper wing and the lower wing are fixedly connected by struts, and a cross-type flight wire is arranged between the upper wing and the lower wing. The flight wire is arranged between the struts and the fuselage.
[0009] Furthermore, the power assembly includes an engine and a power fan. The engine is fixedly arranged at the front end of the fuselage, the power fan is fixedly arranged on the output shaft of the engine, and the longitudinal axis of the fuselage is coaxially arranged with the output shaft of the engine.
[0010] Furthermore, the tail assembly includes a horizontal wing, a vertical wing, an elevator and a rudder. The horizontal wing is symmetrically and horizontally fixedly arranged at the tail of the fuselage, the vertical wing is vertically fixedly arranged at the tail of the fuselage, the elevator is arranged on the horizontal wing, and the rudder is arranged on the vertical wing.
[0011] Furthermore, the total length L1 of the fuselage, the power assembly and the tail assembly is 12600 - 12800 mm, and the height difference L2 between the front wheel and the top of the tail assembly is 6000 - 6200 mm.
[0012] Furthermore, the horizontal distance L3 between the front wheel and the rear wheel is 8000 - 8100 mm, and the horizontal distance L4 between the two front wheels is 3300 - 3400 mm.
[0013] Furthermore, the total length L5 of the two upper wings on the fuselage is 18100 - 18300 mm, and the total length L6 of the two lower wings is 14200 - 14300 mm.
[0014] Furthermore, the total length L7 of the two horizontal wings on the fuselage is 7150 - 7250 mm.
[0015] The beneficial effects of the present utility model are as follows:
[0016] 1) In the present technology, no driver's seat is arranged on the fuselage, and no pilot is required to operate on the aircraft. This not only eliminates the safety hazards of the pilot, but also reduces the operation difficulty. At the same time, more goods can be carried.
[0017] 2) In the present technology, the upper wing and the lower wing are combined, so that heavier goods can be carried. Description of the Drawings
[0018] Figure 1 It is a three-dimensional connection structure diagram of the fixed-wing large unmanned aerial vehicle;
[0019] Figure 2 It is a front view connection structure diagram of the fixed-wing large unmanned aerial vehicle;
[0020] Figure 3 It is the side view connection structure diagram of this large fixed-wing UAV;
[0021] Figure 4 It is the top view connection structure diagram of this large fixed-wing UAV;
[0022] In the figure, 1 - fuselage, 2 - hatch, 3 - front wheel frame, 4 - rear wheel frame, 5 - front wheel, 6 - rear wheel, 7 - upper wing, 8 - upper inner flap, 9 - upper outer flap, 10 - lower wing, 11 - lower inner flap, 12 - lower outer flap, 13 - strut, 14 - flying wire, 15 - engine, 16 - power fan blade, 17 - flat wing, 18 - vertical wing, 19 - elevator, 20 - rudder. Specific implementation manner
[0023] Next, the technical solution of the present utility model will be clearly and completely described in conjunction with the embodiments. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative efforts fall within the protection scope of the present utility model.
[0024] Refer to Figures 1-4 , the present utility model provides a technical solution:
[0025] A large fixed-wing unmanned aerial vehicle includes a fuselage 1, a hatch 2, a front wheel frame 3, a rear wheel frame 4, a front wheel 5, a rear wheel 6, a power assembly, a front wing assembly, and a tail wing assembly. A power assembly for driving the movement of the fuselage 1 is fixedly arranged at the front end of the fuselage 1. The tail wing assembly is fixedly arranged at the tail of the fuselage 1. The front wing assembly is fixedly arranged at the front of the fuselage 1. The rear wheel 6 is fixedly arranged at the tail of the fuselage 1 through the rear wheel frame 4. The front wheel frame 3 is fixedly arranged at the front of the fuselage 1 and is directly below the front wing assembly. Two front wheels 5 are symmetrically arranged under the front wheel frame 3. The front wheel 5 and the rear wheel 6 are arranged on the same inclined plane. The angle θ between the inclined plane and the longitudinal axis of the fuselage 1 is 11° - 13°. The total length L1 of the fuselage 1, the power assembly, and the tail wing assembly is 12,600 - 12,800 mm. The height difference L2 between the front wheel 5 and the top of the tail wing assembly is 6,000 - 6,200 mm. The horizontal distance L3 between the front wheel 5 and the rear wheel 6 is 8,000 - 8,100 mm. The horizontal distance L4 between the two front wheels 5 is 3,300 - 3,400 mm. Among them, no operation room for the pilot is provided inside the fuselage 1. At the same time, a hatch 2 is provided on each side of the fuselage 1, which is convenient for loading and unloading goods. The front wheel frame 3 is used to install two front wheels 5, and the horizontal distance L4 between the two front wheels 5 is 3,360 mm. The rear wheel frame 4 is used to install the rear wheel 6, and the horizontal distance L3 between the front wheel 5 and the rear wheel 6 is 8,060 mm. The total height L2 of the unmanned aerial vehicle is 6,097 mm, and the total length L1 of the unmanned aerial vehicle is 12,688 mm. The angle θ between the inclined plane and the longitudinal axis of the fuselage 1 is 11°50′. The maximum payload of the unmanned aerial vehicle is 1,900 kg, the payload for 500 km is 1,500 kg, and the payload with full fuel is 1,000 kg.
[0026] In some embodiments, the front wing assembly includes an upper wing 7, an upper inner flap 8 and an upper outer flap 9. The upper wings 7 are symmetrically arranged on both sides of the upper part of the fuselage 1. The upper inner flap 8 and the upper outer flap 9 are arranged on the upper wing 7, and the upper inner flap 8 is arranged closer to the fuselage 1. The total length L5 of the two upper wings 7 on the fuselage 1 is 18,100 - 18,300 mm. The front wing assembly further includes a lower wing 10, a lower inner flap 11 and a lower outer flap 12. The lower wings 10 are symmetrically arranged on both sides of the lower part of the fuselage 1. The lower wing 10 is arranged directly below the upper wing 7 and the length of the lower wing 10 is less than that of the upper wing 7. The lower inner flap 11 and the lower outer flap 12 are arranged on the lower wing 10, and the lower inner flap 11 is arranged closer to the fuselage 1. The total length L6 of the two lower wings 10 is 14,200 - 14,300 mm. Among them, the upper wing 7, the upper inner flap 8, the upper outer flap 9, the lower wing 10, the lower inner flap 11 and the lower outer flap 12 are all in the prior art. The upper inner flap 8 and the upper outer flap 9 can swing up and down on the upper wing 7, and the lower inner flap 11 and the lower outer flap 12 can swing on the lower wing 10. Setting the upper wing 7 and the lower wing 10 at the same time can enable the UAV to carry a greater mass and more goods can be loaded into the UAV. Generally, the total length L5 of the two upper wings 7 on the fuselage 1 is 18,176 mm, and the total length L6 of the two lower wings 10 is 14,236 mm.
[0027] In some embodiments, the upper wing 7 and the lower wing 10 are fixedly connected by a strut 13. A cross-type flying wire 14 is arranged between the upper wing 7 and the lower wing 10. The flying wire 14 is arranged between the strut 13 and the fuselage 1. The purpose of setting the strut 13 and the flying wire 14 is to keep the distance between the upper wing 7 and the lower wing 10 fixed when the UAV is flying, and prevent the lower wing 10 or the lower wing 10 from being broken during flight.
[0028] In some embodiments, the power assembly includes an engine 15 and a power fan blade 16. The engine 15 is fixedly arranged at the front end of the fuselage 1, and the power fan blade 16 is fixedly arranged on the output shaft of the engine 15. The longitudinal axis of the fuselage 1 is coaxially arranged with the output shaft of the engine 15. Among them, the engine 15 is a single-cylinder piston engine in the prior art, and the power fan blade 16 is a four-blade metal propeller in the prior art. The engine 15 is fixed on the fuselage 1 and drives the power fan blade 16 to rotate. The rotation of the power fan blade 16 can drive the UAV to fly.
[0029] In some embodiments, the tail assembly includes a horizontal wing 17, a vertical wing 18, an elevator 19 and a rudder 20. The horizontal wing 17 is symmetrically and horizontally fixed to the tail of the fuselage 1, and the vertical wing 18 is vertically fixed to the tail of the fuselage 1. The elevator 19 is provided on the horizontal wing 17, and the rudder 20 is provided on the vertical wing 18. The total length L7 of the two horizontal wings 17 on the fuselage 1 is 7150 - 7250 mm. Among them, the horizontal wing 17, the vertical wing 18, the elevator 19 and the rudder 20 are all prior arts. The elevator 19 can swing up and down on the horizontal wing 17, and the rudder 20 can swing left and right on the vertical wing 18. The horizontal wing 17 and the elevator 19 are provided to bear the weight of the tail of the UAV, and the vertical wing 18 and the rudder 20 are provided to enable the UAV to fly stably and turn. Generally, the total length L7 of the two horizontal wings 17 on the fuselage 1 is 7200 mm.
[0030] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper part", "one end", "top", "middle part", "the other end", "upper", "one side", "inner", "front part", "center", "both ends", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, so it cannot be understood as a limitation to the present invention.
[0031] In the present invention, unless otherwise clearly defined and limited, the terms "installation", "setting", "connection", "fixation", "hinged connection", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. It can be the communication inside two elements or the interaction relationship between two elements. Unless otherwise clearly defined, for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.
[0032] The above is only the preferred embodiment of the present invention. It should be understood that the present invention is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments. Instead, it can be used in various other combinations, modifications and environments, and can be changed within the scope of the concept described herein through the above teachings or the technology or knowledge in related fields. And the changes and modifications made by those skilled in the art without departing from the spirit and scope of the present invention should all be within the protection scope of the appended claims of the present invention.
Claims
1. A fixed-wing large unmanned aerial vehicle, characterized in that: It includes a fuselage (1), a hatch (2), a front wheel frame (3), a rear wheel frame (4), a front wheel (5), a rear wheel (6), a power assembly, a front wing assembly and a tail wing assembly. The power assembly for driving the movement of the fuselage (1) is fixedly arranged at the front end of the fuselage (1). The tail wing assembly is fixedly arranged on the tail of the fuselage (1). The front wing assembly is fixedly arranged on the front part of the fuselage (1). The rear wheel (6) is fixedly arranged on the tail of the fuselage (1) through the rear wheel frame (4). The front wheel frame (3) is fixedly arranged on the front part of the fuselage (1) and is directly below the front wing assembly. Two front wheels (5) are symmetrically arranged under the front wheel frame (3). The front wheel (5) and the rear wheel (6) are arranged on the same inclined plane, and the included angle θ between the inclined plane and the longitudinal axis of the fuselage (1) is 11 to 13°; The front wing assembly includes an upper wing (7), an upper inner flap (8) and an upper outer flap (9). The upper wings (7) are symmetrically arranged on both sides of the upper part of the fuselage (1). The upper inner flap (8) and the upper outer flap (9) are arranged on the upper wing (7). The upper inner flap (8) is arranged closer to the fuselage (1); The front wing assembly further includes a lower wing (10), a lower inner flap (11) and a lower outer flap (12). The lower wings (10) are symmetrically arranged on both sides of the lower part of the fuselage (1). The lower wing (10) is arranged directly below the upper wing (7) and the length of the lower wing (10) is less than that of the upper wing (7). The lower inner flap (11) and the lower outer flap (12) are arranged on the lower wing (10). The lower inner flap (11) is arranged closer to the fuselage (1).
2. The large fixed-wing unmanned aerial vehicle according to claim 1, wherein: The upper wing (7) and the lower wing (10) are fixedly connected by a strut (13). A cross-type flying wire (14) is arranged between the upper wing (7) and the lower wing (10). The flying wire (14) is arranged between the strut (13) and the fuselage (1).
3. A fixed-wing large unmanned aerial vehicle according to claim 1 or 2, characterized in that: The power assembly includes an engine (15) and a power fan blade (16). The engine (15) is fixedly arranged at the front end of the fuselage (1). The power fan blade (16) is fixedly arranged on the output shaft of the engine (15). The longitudinal axis of the fuselage (1) is coaxially arranged with the output shaft of the engine (15).
4. A fixed-wing large UAV according to claim 1 or 2, characterized in that: The tail wing assembly includes a horizontal wing (17), a vertical wing (18), an elevator (19) and a rudder (20). The horizontal wings (17) are symmetrically and horizontally fixedly arranged on the tail of the fuselage (1). The vertical wings (18) are vertically fixedly arranged on the tail of the fuselage (1). The elevator (19) is arranged on the horizontal wing (17). The rudder (20) is arranged on the vertical wing (18).
5. A fixed-wing large unmanned aerial vehicle according to claim 1 or 2, characterized in that: The total length L1 of the fuselage (1), the power assembly and the tail assembly is 12,600 - 12,800 mm, and the height difference L2 between the front wheel (5) and the top of the tail assembly is 6,000 - 6,200 mm.
6. A fixed-wing large unmanned aerial vehicle according to claim 1 or 2, characterized in that: The horizontal distance L3 between the front wheel (5) and the rear wheel (6) is 8,000 - 8,100 mm, and the horizontal distance L4 between the two front wheels (5) is 3,300 - 3,400 mm.
7. A fixed-wing large unmanned aerial vehicle according to claim 2, characterized in that: The total length L5 of the two upper wings (7) on the fuselage (1) is 18,100 - 18,300 mm, and the total length L6 of the two lower wings (10) is 14,200 - 14,300 mm.
8. A fixed-wing large unmanned aerial vehicle according to claim 4, characterized in that: The total length L7 of the two flat wings (17) on the fuselage (1) is 7,150 - 7,250 mm.