Unmanned aerial vehicle device capable of reducing airflow resistance

Abstract

The unmanned aerial vehicle device capable of reducing the airflow resistance comprises a vehicle body, vehicle arms and paddles, the vehicle arms are located on the same horizontal plane and arranged at the four corners of the vehicle body in a pairwise corresponding mode, the ends, away from the vehicle body, of the vehicle arms are connected with propelling blocks, and the paddles are arranged at the tops of the propelling blocks. A storage groove is formed in the inner bottom of the middle of the fuselage, a folding mechanism is arranged in the storage groove and comprises an undercarriage and a rotating motor, two sets of fixing blocks are correspondingly fixed to the top of the storage groove, a fixing rod is fixedly installed between the two sets of fixing blocks, and two sets of connecting rods are rotatably installed on the fixing rod; and the undercarriage is hinged to the end, away from the fixing rods, of the connecting rod, supporting blocks fixed to the top of the storage groove are arranged on the outer side portions of the two fixing blocks correspondingly, and the rotating motors are fixed to the supporting blocks. The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle device capable of reducing airflow resistance.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically referring to a UAV device that can reduce airflow resistance. Background Technology

[0002] Unmanned aerial vehicle (UAV) technology has developed rapidly in recent years and is widely used in fields such as military reconnaissance, logistics transportation, and agricultural plant protection. As the performance requirements for UAVs increase, reducing air resistance has become a key issue in improving flight efficiency and extending endurance.

[0003] Traditional drone designs are typically square. The sharp corners of a square fuselage are prone to airflow separation, generating a large number of vortices and increasing airflow drag. In addition, the landing gear of a drone is usually exposed during flight, and its irregular shape and large frontal area also generate additional airflow drag, affecting the drone's flight performance. Utility Model Content

[0004] To address the aforementioned problems of traditional drone devices having a square shape that increases airflow resistance, and the additional airflow resistance generated by the drone's landing gear, this invention provides a drone device that can reduce airflow resistance.

[0005] To achieve the above functions, the technical solution adopted by this utility model is as follows: A drone device that can reduce airflow resistance includes a fuselage, arms and rotors. The arms are located on the same horizontal plane and are arranged in pairs at the four corners of the fuselage. The ends of the arms away from the fuselage are connected to propulsion blocks. The rotors are arranged on the top of the propulsion blocks. A storage groove is opened in the bottom of the middle of the fuselage, and a folding mechanism is provided in the storage groove.

[0006] The folding mechanism includes a landing gear and a rotary motor. Two sets of fixing blocks are fixedly fixed to the top of the storage slot. A fixing rod is fixedly installed between the two sets of fixing blocks. Two sets of connecting rods at a certain angle are rotatably installed on the fixing rod. The landing gear is hinged to the end of the connecting rod away from the fixing rod. Support blocks fixed to the top of the storage slot are respectively provided on the outer side of the two sets of fixing blocks. The rotary motor is fixed on the support block. The output end of the rotary motor rotates through the support block and is connected to a crank. The free end of the crank is movably mounted on the connecting rod.

[0007] As a preferred technical solution of this utility model, the bottom of the body is provided with an arc-shaped groove that communicates with the storage slot, and the connecting rod is rotatably disposed in the arc-shaped groove.

[0008] As a preferred technical solution of this utility model, a limiting groove is provided on the connecting rod, and a slider is connected to the free end of the rocker handle. The slider is slidably disposed in the limiting groove and forms a sliding pair connection with the limiting groove of the connecting rod.

[0009] As a preferred technical solution of this utility model, the fuselage has corresponding horizontal grooves on both sides, the horizontal grooves are connected to the storage groove and the arc groove respectively, and the landing gear is fitted and stored in the horizontal groove.

[0010] As a preferred embodiment of this utility model, the middle part of the fuselage has a streamlined transition, and the front and rear ends of the fuselage are bullet-shaped.

[0011] As a preferred technical solution of this utility model, the four sets of arms are symmetrically distributed in an X-shape, and the axis of each arm forms a 45° angle with the longitudinal axis of the body.

[0012] Compared with the prior art, the present invention achieves the following beneficial effects by adopting the above structure:

[0013] 1. By combining the streamlined transition in the middle of the fuselage with the bullet-shaped design at the front and rear, the aerodynamic performance is further optimized. The pointed cone shape at the front can effectively pierce the air vortex, and the tapered rear can avoid wake turbulence. Compared with the existing conventional fuselage shape, it can significantly reduce air resistance, making the drone fly more smoothly and consume less energy, thus further improving the overall flight performance.

[0014] 2. Through the coordinated design of the folding mechanism, connecting rod, crank, transverse slot, and storage slot, the landing gear achieves automatic folding and storage functions. During drone flight, the landing gear can be retracted into the transverse slots on both sides of the fuselage, effectively reducing the drone's frontal area, greatly reducing air resistance, improving flight efficiency, and increasing range. During landing, the landing gear can be easily deployed to ensure a smooth and safe landing. The operation process is simple and highly automated, requiring no manual intervention, significantly improving the convenience and reliability of drone use. Attached Figure Description

[0015] Figure 1 This invention provides a schematic diagram of the overall structure of a drone device that can reduce airflow resistance. Figure 1 ;

[0016] Figure 2 This invention provides a schematic diagram of the overall structure of a drone device that can reduce airflow resistance. Figure 2 ;

[0017] Figure 3 This is a partial structural schematic diagram of a drone device that can reduce airflow resistance according to the present invention.

[0018] Figure 4 This is a schematic diagram of the overall structure of the folding component proposed in this utility model;

[0019] Figure 5This is a partial structural schematic diagram of the folding component proposed in this utility model.

[0020] Among them, 1. fuselage, 2. arm, 3. rotor blade, 4. propulsion block, 5. storage slot, 6. folding mechanism, 7. landing gear, 8. rotary motor, 9. fixing block, 10. fixing rod, 11. connecting rod, 12. support block, 13. crank handle, 14. arc groove, 15. limiting groove, 16. transverse groove. Detailed Implementation

[0021] The technical solution of this utility model will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0022] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The utility model will be further described in detail below with reference to the accompanying drawings.

[0023] like Figure 1-5 As shown, this utility model provides a drone device that can reduce airflow resistance, including a fuselage 1, arms 2, and rotors 3. The middle part of the fuselage 1 has a streamlined transition, and the front and rear ends of the fuselage 1 are bullet-shaped. The front end is pointed and conical to pierce air vortices, and the rear end tapers to avoid wake turbulence. This design can reduce air resistance, make the drone fly more smoothly, reduce energy loss, and improve flight efficiency. The arms 2 are located on the same horizontal plane and are arranged in pairs at the four corners of the fuselage 1. The four sets of arms 2 are symmetrically distributed in an X-shape, and the axis of each arm 2 forms a 45° angle with the longitudinal axis of the fuselage 1. This layout can make the force on the drone more uniform in all directions during flight, improve flight stability and maneuverability, and also facilitate the uniform distribution of airflow generated by the rotors 3, reducing airflow interference. The ends of the arms 2 away from the fuselage 1 are connected to propulsion blocks 4, and the rotors 3 are set on top of the propulsion blocks 4 to provide lift and propulsion for the drone. A storage groove 5 is opened in the middle of the bottom of the fuselage 1, and a folding mechanism 6 is set in the storage groove 5.

[0024] The folding mechanism 6 includes a landing gear 7 and a rotary motor 8. Two sets of fixing blocks 9 are fixed to the top of the storage slot 5, and a fixing rod 10 is fixedly installed between the two sets of fixing blocks 9 to provide rotational support for the connecting rod 11. Two sets of connecting rods 11 at a certain angle are rotatably mounted on the fixing rod 10. The landing gear 7 is hinged to the end of the connecting rod 11 away from the fixing rod 10. Support blocks 12, fixed to the top of the storage slot 5, are respectively provided on the outer sides of the two sets of fixing blocks 9. The support blocks 12 are used to fix the rotary motor 8 to ensure its stable operation. The rotary motor 8 is fixed to the support blocks 12, and its output end rotates through the support blocks 12 and is connected to a crank handle 13. The free end of the crank handle 13 is movably mounted on the connecting rod 11. An arc-shaped groove 14 communicating with the storage slot 5 is opened at the bottom of the fuselage 1. The connecting rod 11 is rotatably mounted in the arc-shaped groove 14, providing space for the rotation of the connecting rod 11 and allowing it to move within it. A limiting groove 15 is provided on the connecting rod 11, and a slider is connected to the free end of the crank handle 13. The slider is slidably mounted in the limiting groove 15, forming a sliding pair connection with the limiting groove 15 of the connecting rod 11. When the rotary motor 8 is started, the crank handle 13 rotates, which drives the connecting rod 11 to rotate around the fixed rod 10, thereby driving the landing gear 7 to switch between the storage slot 5, the transverse slot 16, and the deployed position. When the landing gear 7 needs to be stored, the rotary motor 8 drives the crank handle 13 to rotate, causing the connecting rod 11 to rotate and retract the landing gear 7 into the transverse slots 16 on both sides of the fuselage 1. When the landing gear 7 needs to be used, the rotary motor 8 reverses, and the crank handle 13 drives the connecting rod 11 to lower the landing gear 7.

[0025] like Figure 1-3 As shown, horizontal slots 16 are provided on both sides of the fuselage 1. The horizontal slots 16 are connected to the storage slot 5 and the arc-shaped slot 14 respectively, ensuring that the landing gear 7 moves smoothly during the storage and deployment process. The landing gear 7 is neatly stored in the horizontal slots 16.

[0026] In practical use, before takeoff, the rotary motor 8 is started, which drives the crank handle 13 to rotate. The crank handle 13 slides in the limiting groove 15 of the connecting rod 11 through the slider, driving the connecting rod 11 to rotate around the fixed rod 10, thus unfolding the landing gear 7 from the transverse slots 16 on both sides of the fuselage 1 to the working position, ensuring landing safety. During flight, the landing gear 7 is stored in the transverse slots 16. Combined with the streamlined transition in the middle of the fuselage 1 and the bullet-shaped design at the front and rear ends, as well as the X-shaped symmetrical distribution of the arms 2 and the 45° angle between the axis of the arms 2 and the longitudinal axis of the fuselage 1, it effectively reduces airflow resistance and improves flight efficiency and range. During landing, the rotary motor 8 reverses, and the crank handle 13 drives the connecting rod 11 to lower the landing gear 7, ensuring a smooth landing.

[0027] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the inventive spirit of the present invention, such designs should fall within the protection scope of the present invention.

Claims

1. A drone device capable of reducing airflow drag, comprising a fuselage (1), arms (2), and rotor blades (3), characterized in that: The arms (2) are located on the same horizontal plane and are arranged in pairs at the four corners of the fuselage (1). The ends of the arms (2) away from the fuselage (1) are connected to the propulsion blocks (4). The propellers (3) are arranged on the top of the propulsion blocks (4). A storage groove (5) is opened in the bottom of the middle of the fuselage (1). A folding mechanism (6) is provided in the storage groove (5). The folding mechanism (6) includes a landing gear (7) and a rotary motor (8). Two sets of fixing blocks (9) are fixedly fixed to the top of the storage slot (5). A fixing rod (10) is fixedly installed between the two sets of fixing blocks (9). Two sets of connecting rods (11) with a certain inclination angle are rotatably installed on the fixing rods (10). The landing gear (7) is hinged to the end of the connecting rods (11) away from the fixing rods (10). Support blocks (12) fixed to the top of the storage slot (5) are respectively provided on the outer side of the two sets of fixing blocks (9). The rotary motor (8) is fixed on the support block (12). The output end of the rotary motor (8) rotates through the support block (12) and is connected to a crank (13). The free end of the crank (13) is movably arranged on the connecting rod (11).

2. The unmanned aerial vehicle (UAV) device for reducing airflow resistance according to claim 1, characterized in that: The bottom of the body (1) is provided with an arc-shaped groove (14) that communicates with the storage groove (5), and the connecting rod (11) is rotatably disposed in the arc-shaped groove (14).

3. The unmanned aerial vehicle (UAV) device for reducing airflow resistance according to claim 2, characterized in that: A limiting groove (15) is provided on the connecting rod (11), and a slider is connected to the free end of the rocker (13). The slider is slidably disposed in the limiting groove (15) and forms a sliding pair connection with the limiting groove (15) of the connecting rod (11).

4. A drone device for reducing airflow resistance according to any one of claims 1-3, characterized in that: The fuselage (1) has corresponding horizontal grooves (16) on both sides. The horizontal grooves (16) are connected to the storage groove (5) and the arc groove (14) respectively. The landing gear (7) is fitted and stored in the horizontal grooves (16).

5. The unmanned aerial vehicle (UAV) device for reducing airflow resistance according to claim 4, characterized in that: The middle part of the fuselage (1) has a streamlined transition, and the front and rear ends of the fuselage (1) are bullet-shaped.

6. The unmanned aerial vehicle (UAV) device for reducing airflow resistance according to claim 1, characterized in that: The four sets of arms (2) are symmetrically distributed in an X shape, and the axis of each arm (2) forms a 45° angle with the longitudinal axis of the fuselage (1).

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