An unmanned aerial vehicle based on integration of pneumatic structure

Abstract

The utility model discloses an unmanned plane based on pneumatic structure integration, including fuselage and fairing, the fairing fixed surface is connected in the lower surface of fuselage, the tail of fuselage is fixed with the canard, the opposite side fixed with lower main wing of fairing outer surface, and the end of lower main wing is fixed with end plate, one group end plate's inboard upper portion is fixed with upper main wing, the end of upper main wing is fixed with wing tip aileron, one group end plate outside one end symmetry fixed with rudder, the both sides symmetry fixed with flap of upper main wing top end middle part. The utility model makes this unmanned plane obvious comprehensive superiority, possesses small size, light weight, big load, high strength, long navigation time, big voyage, positive matching, short takeoff and landing, efficient cruise and so on excellent characteristics, especially its high load coefficient, has great advantage to be applied to transport unmanned plane, makes it be very suitable for carrying out plateau transport improvement, and the overall aerodynamic performance is better.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to an UAV based on integrated aerodynamic structure. Background Technology

[0002] A drone is an aircraft that does not require a human pilot to operate and flies through remote control equipment or autonomous programs.

[0003] Currently, most mainstream UAVs worldwide adopt a high-aspect-ratio straight-wing aerodynamic layout to meet the requirements of high lift and long endurance. In addition, multi-rotor, helicopter, VTOL fixed-wing, and tiltrotor aircraft are also specifically designed for particular missions. High-aspect-ratio fixed-wing UAVs have higher lift, can carry more payload to perform special missions, and the increased fuel capacity means longer loiter time. However, high-aspect-ratio wings place high demands on the structure and have certain limitations regarding airport and highway width. Furthermore, existing fixed-wing transport aircraft have not seen significant breakthroughs in overall layout, exhibiting weak / uncoupled aerodynamic / structural / control designs, making it difficult to improve overall performance. Therefore, there is a need for a UAV based on integrated aerodynamics and structure to improve performance. Utility Model Content

[0004] The purpose of this utility model is to provide an unmanned aerial vehicle (UAV) based on integrated aerodynamic structure to solve the problems mentioned in the background section. To solve the above technical problems, this utility model is achieved through the following technical solution:

[0005] This utility model relates to an unmanned aerial vehicle (UAV) based on an integrated aerodynamic structure, comprising:

[0006] The fuselage and fairing are provided. The fairing is fixedly connected to the lower surface of the fuselage. A canard is fixedly provided at the tail of the fuselage. Lower main wings are fixed on opposite sides of the outer surface of the fairing, and endplates are fixed at the ends of the lower main wings. An upper main wing is fixed on the upper inner side of a set of endplates. A wingtip aileron is fixed at the end of the upper main wing. A rudder is symmetrically fixed at one end of the outer side of a set of endplates. Flaps are symmetrically fixed on both sides of the middle top of the upper main wing.

[0007] Furthermore, it also includes an installation structure, which includes a connecting column and an installation frame. The connecting column is located on one side below the fairing, and one end of the connecting column is fixed to the lower part of one side of the installation frame. One side of the upper end of the installation frame is connected to the central cavity.

[0008] Furthermore, the mounting structure also includes a positioning groove, which is located on one side of the lower end of the outer surface of the fairing, and the inner wall of the positioning groove abuts against the outer side of the upper end of the mounting frame.

[0009] Furthermore, the installation structure also includes a set of symmetrically arranged torsion springs, with a support column fixed to the inner side of the set of torsion springs, and the middle part of the outer surface of the support column engaging and fixing with the other end of the connecting column.

[0010] Furthermore, the installation structure also includes a limiting groove, which is formed on one side of the positioning groove, and the opposite sides of the inner wall of the limiting groove are fixed to the outer side of the torsion spring.

[0011] Furthermore, a movable connecting rod is movably connected to the lower part of the outer surface of the connecting column, and one end of the movable connecting rod is movably connected to the outside of the landing gear bay door.

[0012] This utility model has the following beneficial effects:

[0013] This utility model adopts a canard-connected wing layout, which has obvious comprehensive advantages. It has excellent characteristics such as small size, light weight, large payload, high strength, long endurance, long range, positive trim, short takeoff and landing, and efficient cruise. In particular, its high payload coefficient has great advantages in the application of transport drones, making it very suitable for high-altitude transport. The overall aerodynamic performance is better, and the upper opening of the upper main wing is a flap, while the rear opening of the endplate is a horizontal stabilizer. At the same time, the wingtip of the upper main wing is an all-moving wingtip, which has the same function as the canard, making the aircraft more flexible in handling and more stable in flight. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a perspective view of the present invention;

[0016] Figure 2 This is a front view of the present utility model;

[0017] Figure 3 This is a top view of the present invention;

[0018] Figure 4 Assembly drawing of the installation structure added to this utility model;

[0019] Figure 5 This is a schematic diagram of the installation structure for this utility model.

[0020] The attached diagram lists the components represented by each number as follows:

[0021] 1. Canard; 2. Fuselage; 3. Lower main wing; 4. Upper main wing; 5. Wingtip aileron; 6. Endplate; 7. Flaps; 8. Rudder; 9. Fairing; 10. Limiting slot; 11. Torsion spring; 12. Strut; 13. Connecting post; 14. Mounting frame; 15. Movable link; 16. Positioning slot. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments of this utility model will be described in further detail below with reference to the accompanying drawings.

[0024] Please see Figure 1-5 As shown, this utility model is a drone based on an integrated aerodynamic structure, comprising:

[0025] The fuselage 2 and fairing 9 are fixedly connected to the lower surface of the fuselage 2. A canard 1 is fixedly provided at the tail of the fuselage 2. Lower main wings 3 are fixed on opposite sides of the outer surface of the fairing 9, and end plates 6 are fixed at the ends of the lower main wings 3. An upper main wing 4 is fixed on the upper inner side of a set of end plates 6. A wingtip aileron 5 is fixed at the end of the upper main wing 4. A rudder 8 is symmetrically fixed at one end of the outer side of a set of end plates 6. Flaps 7 are symmetrically fixed on both sides of the middle top of the upper main wing 4.

[0026] The canard 1 is mounted in a hammerhead shark configuration at the tail of the fuselage 2. Compared with the conventional canard 1 configuration, it has better aerodynamic performance. During flight, the angle can be adjusted in real time to balance the flight torque and maximize cruise efficiency. The lower main wing 3 is the main source of lift. The upper main wing 4, lower main wing 3, fuselage 2 and canard 1 form a diamond frame structure, which gives the whole structure the advantages of large lift line slope, low aerodynamic drag, large maximum lift coefficient, good stability and maneuverability. The endplate 6 provides the structural foundation for installation. The wingtip aileron 5 is a fully movable design and has the same function as the canard 1, making the aircraft more flexible to operate and more stable in flight. The rudder 8 is used to adjust the UAV's heading to ensure that the flight trajectory meets expectations.

[0027] Working principle: During the flight of the UAV, the canard 1-connected wing layout is adopted, and the upper opening of the upper main wing 4 is the flap 7, the rear opening of the endplate 6 is the horizontal stabilizer, and the wingtip of the upper main wing 4 is the all-moving wingtip, which has the same function as the canard 1.

[0028] This design gives the UAV a significant overall advantage, featuring excellent characteristics such as small size, light weight, large payload, high strength, long endurance, long range, positive trim, short takeoff and landing, and efficient cruise. In particular, its high payload coefficient is a great advantage when applied to transport UAVs, making it very suitable for improving high-altitude transport capabilities, and its overall aerodynamic performance is better.

[0029] Please see Figure 1-5 As shown, this embodiment is based on the above embodiment:

[0030] It also includes an installation structure, which includes a connecting column 13 and an installation frame 14. The connecting column 13 is located on one side below the fairing 9, and one end of the connecting column 13 is fixed to the lower part of one side of the installation frame 14. One side of the upper end of the installation frame 14 is connected to the central cavity.

[0031] The connecting column 13 is installed and fixed to the mounting frame 14. The mounting frame can be used to install and fix structures such as monitoring sensors and cameras.

[0032] The installation structure also includes a positioning groove 16, which is located on one side of the lower end of the outer surface of the fairing 9, and the inner wall of the positioning groove 16 abuts against the outer side of the upper end of the mounting frame 14.

[0033] The mutual contact between the positioning groove 16 and the upper end of the mounting frame 14 ensures the stability of the mounting frame 14 structure during storage.

[0034] The installation structure also includes a set of torsion springs 11 arranged symmetrically. A support column 12 is fixed to the inner side of the set of torsion springs 11, and the middle part of the outer surface of the support column 12 is fitted and fixed to the other end of the connecting column 13.

[0035] The torsion spring 11 supports the connection column 13 structure via the support column 12, and the elastic force of the torsion spring 11 allows for multi-angle adjustment of the connection column 13, thereby meeting the needs of adding the frame 14 for use and storage.

[0036] The installation structure also includes a limiting groove 10, which is opened on one side of the positioning groove 16, and the opposite sides of the inner wall of the limiting groove 10 are fixed to the outer side of the torsion spring 11.

[0037] The limiting groove 10 provides an installation environment for the torsion spring 11.

[0038] A movable link 15 is movably connected to the lower part of the outer surface of the connecting column 13, and one end of the movable link 15 is movably connected to the outside of the landing gear door.

[0039] The movable linkage 15 connects the landing gear door to the mounting frame 14. When the door is in the open or closed state, it can provide the power required for the mounting frame 14 to unfold and retract without the need for an additional power structure, making it convenient to use.

[0040] Working principle: When adding structures to a drone for different uses, the drone can be directly threaded into the mounting frame 14. During normal drone flight, the cabin door is closed, and the mounting frame 14 is deployed by the action of the movable link 15, so that the added structure can be used normally. When the drone is landing, the cabin door needs to be opened to lower the landing gear. Similarly, the movable link 15 applies an inward pushing force to the mounting frame 14, so that the upper end of the mounting frame 14 extends into the positioning groove 16.

[0041] This solution allows for the conversion between the usage and storage states by adding a frame 14 through the opening and closing of the hatch, eliminating the need for an additional power structure, saving costs, reducing the drone's payload, and further increasing its range.

[0042] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A drone based on integrated aerodynamic structure, characterized in that, include: The fuselage (2) and fairing (9) are fixedly connected to the lower surface of the fuselage (2). A canard (1) is fixedly provided at the tail of the fuselage (2). A lower main wing (3) is fixed on opposite sides of the outer surface of the fairing (9), and an end plate (6) is fixed at the end of the lower main wing (3). An upper main wing (4) is fixed on the upper inner side of a set of end plates (6). A wingtip aileron (5) is fixed at the end of the upper main wing (4). A rudder (8) is symmetrically fixed at one end of the outer side of a set of end plates (6). Flaps (7) are symmetrically fixed on both sides of the middle top of the upper main wing (4).

2. The UAV based on integrated aerodynamic structure according to claim 1, characterized in that: It also includes an installation structure, which includes a connecting column (13) and an installation frame (14). The connecting column (13) is located on one side below the fairing (9), and one end of the connecting column (13) is fixed to the lower part of one side of the installation frame (14). One side of the upper end of the installation frame (14) is connected to the central cavity.

3. The UAV based on integrated aerodynamic structure according to claim 2, characterized in that: The mounting structure also includes a positioning groove (16), which is located on one side of the lower end of the outer surface of the fairing (9), and the inner wall of the positioning groove (16) abuts against the outer side of the upper end of the mounting frame (14).

4. The UAV based on integrated aerodynamic structure according to claim 2, characterized in that: The installation structure also includes a set of torsion springs (11) arranged symmetrically. A support column (12) is fixed on the inner side of the set of torsion springs (11), and the middle part of the outer surface of the support column (12) is fitted and fixed to the other end of the connecting column (13).

5. The UAV based on integrated aerodynamic structure according to claim 2, characterized in that: The installation structure also includes a limiting groove (10), which is opened on one side of the positioning groove (16). The opposite sides of the inner wall of the limiting groove (10) are fixed to the outer side of the torsion spring (11).

6. The UAV based on integrated aerodynamic structure according to claim 2, characterized in that: The lower part of the outer surface of the connecting column (13) is movably connected to a movable link (15), and one end of the movable link (15) is movably connected to the outside of the landing gear door.

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