Wing body structure of unmanned aerial vehicle

Abstract

The utility model relates to a wing body structure of an unmanned aerial vehicle. The wing body structure comprises a fuselage, a coaxial double-propeller structure and a posture adjusting structure, the coaxial double-paddle structure comprises a shaft core installed on the machine body, a forward paddle and a backward paddle, wherein the forward paddle and the backward paddle are installed on the shaft core. The posture adjusting structure comprises a first paddle balancer, a second paddle balancer, a first connecting rod and a second connecting rod which are mounted on the shaft core; the first paddle balancer is fixedly connected with the forward paddle through the first connecting rod, and the second paddle balancer is fixedly connected with the backward paddle through the second connecting rod; when the paddles are unbalanced, the first paddle balancer and the second paddle balancer can quickly adjust the forward paddle and the backward paddle through the first connecting rod and the second connecting rod; a real-time attitude adjustment mechanism can quickly respond to various changes in flight; accurate attitude adjustment helps to improve the safety and reliability of flight and reduce the occurrence of accidents.

Description

TECHNICAL FIELD

[0001] The utility model relates to an unmanned plane, specifically to a wing-body structure of unmanned plane. BACKGROUND

[0002] With the continuous development of science and technology, the unmanned plane structure is more and more widely used in various fields; for the civil field, people have strong demand for convenient and efficient air traffic mode; small unmanned plane can provide fast travel choice under the condition of urban traffic congestion, and can also be used in the fields of logistics distribution, sightseeing tourism and the like; in addition, for some remote areas or complex terrain areas, unmanned plane can become an important traffic tool and rescue tool; in the flight process of unmanned plane, imbalance of paddle is a common problem, which can cause unmanned plane vibration, control difficulty and even accident. SUMMARY

[0003] Therefore, the utility model aims at providing a reliable wing-body structure of unmanned plane.

[0004] The utility model adopts the following technical scheme:

[0005] A wing-body structure of unmanned plane, including fuselage, coaxial double paddle structure and attitude adjustment structure, the coaxial double paddle structure includes the axle core installed on the fuselage, the positive paddle and the counter paddle installed on the axle core, the attitude adjustment structure includes the first paddle balancer, the second paddle balancer, the first connecting rod and the second connecting rod installed on the axle core, the first paddle balancer is connected and fixed with the positive paddle through the first connecting rod, and the second paddle balancer is connected and fixed with the counter paddle through the second connecting rod.

[0006] Further, the drive assembly includes a lifting cylinder, a fixed support and a rotating motor, the lifting cylinder includes a piston rod, the piston rod is connected with the fixed support, and the rotating motor is installed on the fixed support, the rotating motor includes a rotating shaft, and the rotating shaft is connected with the grabbing assembly.

[0007] Further, the grabbing assembly is a suction cup and a vacuum pump, the suction cup is connected with the vacuum pump, and the vacuum pump is fixedly installed on the fixed support.

[0008] Further, a shaft coupling is arranged between the rotating shaft and the suction cup.

[0009] Further, the wing-body structure of unmanned plane further includes a feeding conveyor belt, and the grabbing assembly is installed on the feeding conveyor belt through the drive assembly.

[0010] Further, the wing-body structure of the unmanned aerial vehicle further comprises an outfeed conveyor belt; the outfeed conveyor belt is provided with a conveying guide rail for conveying the cotton swab box; the conveying direction of the outfeed conveyor belt is perpendicular to the conveying direction of the infeed conveyor belt.

[0011] Further, the infeed conveyor belt near the side of the outfeed conveyor belt is provided with a limiting member.

[0012] Further, the angle positioning mechanism is a code scanner; the code scanner is installed on the outfeed conveyor belt at the side of the limiting member.

[0013] Further, the wing-body structure of the unmanned aerial vehicle further comprises a Y-axis driving mechanism and an X-axis driving mechanism; the Y-axis driving mechanism comprises a Y-axis linear motor installed on the infeed conveyor belt and a Y-axis sliding block movably installed on a screw rod of the Y-axis linear motor; the driving assembly is installed on the Y-axis sliding block through the X-axis driving mechanism.

[0014] Further, the X-axis driving mechanism comprises an X-axis linear motor installed on the Y-axis sliding block, an X-axis sliding block installed on a screw rod of the X-axis linear motor, and the lifting cylinder is fixedly installed on the X-axis sliding block.

[0015] The wing-body structure of the unmanned aerial vehicle has the advantages that:

[0016] The wing-body structure of the unmanned aerial vehicle has the advantages that: when the blades are unbalanced, the first blade balancer and the second blade balancer can quickly adjust the pro-rotor and the anti-rotor through the first connecting rod and the second connecting rod; the real-time attitude adjustment mechanism can quickly respond to various changes in flight; the accurate attitude adjustment helps to improve the safety and reliability of flight and reduce the occurrence of accidents; the coaxial dual-blade structure and the attitude adjustment structure are integrated on the fuselage and the shaft core, so that the wing-body structure of the unmanned aerial vehicle is more compact; the compact design reduces the volume and floor area of the wing-body structure of the unmanned aerial vehicle, facilitating carrying and storage. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is an exploded view of the wing-body structure of the unmanned aerial vehicle of an embodiment of the present application;

[0018] Figure 2 It is an exploded view of the coaxial dual-blade structure and the attitude adjustment structure of the wing-body structure of the unmanned aerial vehicle of an embodiment of the present application;

[0019] Figure 3 It is Figure 1 It is an exploded view of the shell, the decorative cover and the decorative rod of the wing-body structure of the unmanned aerial vehicle after the dashed line processing. DETAILED DESCRIPTION

[0020] With reference to the accompanying drawings, the technical solutions in the embodiments of the present application will be clearly and completely described below. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all the other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0021] In the description of the present application, it should be noted that the directions or position relationships indicated by the terms "vertical direction", "upper", "lower", "horizontal" and the like are based on the directions or position relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, "first", "second", "third", "fourth" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0022] In the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "arrangement", "installation", "connection", "connection" should be broadly understood, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrally connected, it can be mechanically connected, or it can be electrically connected, it can be directly connected, or it can be connected through an intermediate medium, it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0023] Please refer to Figures 1 to 3 , the wing-body structure of the unmanned aerial vehicle of an embodiment of the present application, comprising a fuselage 10, a coaxial double propeller structure and an attitude adjusting structure; in the present embodiment, the fuselage 10 is a monkey-shaped structure. The shell 10 is buckled with a decorative cover 70 on the top; the shell 10 is also provided with a decorative rod 80; the coaxial double propeller structure comprises a shaft core 21 mounted on the fuselage 10, a forward propeller 22 and a reverse propeller 23 mounted on the shaft core 21; the attitude adjusting structure comprises a first propeller balancer 31, a second propeller balancer 32, a first connecting rod 33 and a second connecting rod 34 mounted on the shaft core 21; the first propeller balancer 31 is connected and fixed with the forward propeller 22 through the first connecting rod 33, and the second propeller balancer 32 is connected and fixed with the reverse propeller 23 through the second connecting rod 34.

[0024] The working principle of the wing-body structure of the unmanned aerial vehicle is as follows: when the wing-body structure of the unmanned aerial vehicle needs to fly, the shaft core 21 is rotated to drive the forward propeller 22 and the reverse propeller 23 to rotate at a high speed to generate lift; the forward propeller 22 and the reverse propeller 23 rotate in opposite directions to offset the torque generated during rotation; when the propeller blades are unbalanced during rotation, the first propeller blade balancer 31 and the second propeller blade balancer 32 are matched through the first connecting rod 33 and the second connecting rod 34, respectively, to adjust the flight attitude of the forward propeller 22 and the reverse propeller 23.

[0025] Compared with the prior art, the wing-body structure of the unmanned aerial vehicle of the utility model, when the propeller blades are unbalanced, the first propeller blade balancer 31 and the second propeller blade balancer 32 can quickly adjust the forward propeller 22 and the reverse propeller 23 through the first connecting rod 33 and the second connecting rod 34; the real-time attitude adjustment mechanism can quickly respond to various changes in flight; accurate attitude adjustment helps to improve the safety and reliability of flight and reduce the occurrence of accidents; the coaxial dual-propeller structure and the attitude adjustment structure are integrated on the fuselage 10 and the shaft core 21, so that the structure of the wing-body structure of the unmanned aerial vehicle is more compact; the compact design reduces the volume and floor area of the wing-body structure of the unmanned aerial vehicle, facilitating carrying and storage.

[0026] The wing-body structure of the unmanned aerial vehicle further comprises a motor 40 mounted on the fuselage 10, the motor 40 comprising a driving shaft, a driving wheel 41 being sleeved on the driving shaft, and the driving wheel 41 being engaged with the shaft core 21. When the wing-body structure of the unmanned aerial vehicle needs to start flying, the motor 40 mounted on the fuselage 10 starts working; the electromagnetic action inside the motor 40 makes the driving shaft start rotating; the driving wheel 41 sleeved on the driving shaft rotates together with the driving shaft; since the driving wheel 41 is engaged with the shaft core 21, the rotation of the driving wheel 41 drives the shaft core 21 to rotate; the rotation of the shaft core 21 further drives the forward propeller 22 and the reverse propeller 23 mounted thereon to rotate at a high speed; the rotation of the forward propeller 22 and the reverse propeller 23 generates lift, so that the wing-body structure of the unmanned aerial vehicle can overcome gravity and take off; during flight, the motor 40 can control the rotation speed of the driving wheel 41 by adjusting the rotation speed of the driving shaft, so as to adjust the rotation speed of the shaft core 21 and the forward propeller 22 and the reverse propeller 23, thereby controlling the lift of the wing-body structure of the unmanned aerial vehicle to meet the requirements in different flight states, such as ascending, descending, hovering, forward and backward, left and right, and various flight states.

[0027] The body 10 is further provided with a mounting seat 50, and the mounting seat 50 is provided with a first socket 51; the motor 40 is provided with a first plug 42 matched with the first socket 51, and the first plug 42 is electrically connected with the motor 40. The mounting seat 50 is fixed on the body 10 to provide a mounting position for the motor 40; the mounting seat 50 is provided with the first socket 51, and the motor 40 is provided with the first plug 42 matched with the first socket 51; when the motor 40 needs to be mounted on the body 10, the first plug 42 of the motor 40 is inserted into the first socket 51 of the mounting seat 50 to realize mechanical connection and establish electrical connection at the same time; since the first plug 42 is electrically connected with the motor 40, when the first plug 42 is inserted into the first socket 51, power can be transmitted from the first socket 51 to the motor 40 through the first plug 42; after the motor 40 receives the power, the electromagnetic structure inside the motor 40 starts to work, the driving shaft starts to rotate, and then drives the driving wheel 41 to rotate, so as to finally realize the rotation of the shaft core 21 and the positive paddle 22 and the negative paddle 23, and provide lift and power for the wing-body structure of the unmanned aerial vehicle; the plug-in connection mode facilitates the installation and disassembly of the motor 40, and facilitates the maintenance and replacement. At the same time, the assembly of the wing-body structure of the unmanned aerial vehicle is more flexible, and different specifications of the motor 40 can be replaced according to different needs to adjust the performance of the wing-body structure of the unmanned aerial vehicle.

[0028] Please refer to Figure 1 and Figure 2 The bottom of the mounting seat 50 is provided with a bottom-touch sensor 54, and the mounting seat 50 is provided with a bottom-touch alarm 53 matched with the bottom-touch sensor 54. When the wing-body structure of the unmanned aerial vehicle is in a flight state, the bottom-touch sensor 54 at the bottom of the mounting seat 50 is in a non-triggering state; in this embodiment, the bottom-touch sensor 54 is an proximity sensor; in other embodiments, the bottom-touch sensor 54 is a pressure sensor or other technology. When the wing-body structure of the unmanned aerial vehicle descends and approaches the ground or the surface of other objects, if the bottom of the mounting seat 50 contacts the ground or the object, the bottom-touch sensor 54 can detect the contact; for the bottom-touch sensor 54 of the proximity sensor type, when the bottom of the mounting seat 50 approaches the object to a certain distance, the sensor can detect the existence of the object by sensing the changes of electromagnetic field, infrared rays, etc.; after the bottom-touch sensor 54 detects that the bottom of the mounting seat 50 contacts the object, a signal is transmitted to the bottom-touch alarm 53; the bottom-touch alarm 53 is usually a buzzer, a sound and light alarm or other types of alarm devices; when receiving the signal of the bottom-touch sensor 54, the bottom-touch alarm 53 will alarm; if it is a sound and light alarm, it may emit a loud sound and flashing light to remind the operator of the wing-body structure of the unmanned aerial vehicle that the wing-body structure of the unmanned aerial vehicle has approached the ground or has an accidental bottom-touch situation; the operator can take timely measures according to the alarm, such as adjusting the height of the wing-body structure of the unmanned aerial vehicle, avoiding collision, etc., to ensure the safety of the wing-body structure of the unmanned aerial vehicle.

[0029] The machine body 10 is further provided with an electric core 60, the mounting seat 50 is provided with a second socket 52, the electric core 60 is provided with a second plug 61 matched with the second socket 52, and the second plug 61 is electrically connected with the electric core 60. The machine body 10 is provided with the electric core 60 as the power supply of the wing-body structure of the unmanned aerial vehicle; the mounting seat 50 is provided with the second socket 52, and the electric core 60 is provided with the second plug 61 matched with the second socket 52; when the wing-body structure of the unmanned aerial vehicle is assembled, the second plug 61 of the electric core 60 is inserted into the second socket 52 of the mounting seat 50, so that mechanical connection and electrical connection are realized; the electric core 60 stores electric energy, and when the wing-body structure of the unmanned aerial vehicle needs to work, the electric energy in the electric core 60 is transmitted to the mounting seat 50 through the connection of the second plug 61 and the second socket 52; the mounting seat 50 serves as a power distribution node and further transmits the electric energy to each component of the wing-body structure of the unmanned aerial vehicle needing electric power; the plug-in connection mode facilitates the installation and disassembly of the electric core 60, and is convenient for replacing or charging the electric core 60; meanwhile, the power supply system of the wing-body structure of the unmanned aerial vehicle is more flexible and easy to maintain.

[0030] The first socket 51 is provided with a first mounting column 510 extending upward, and the first plug 42 is provided with a first mounting hole matched with the first mounting column 510. The cooperation of the first mounting column 510 and the first mounting hole provides an additional mechanical connection point; after the first plug 42 is inserted into the first socket 51, the first mounting column 510 is inserted into the first mounting hole, which further fixes the connection of the plug and the socket, prevents the plug from loosening or falling off due to factors such as vibration and acceleration during the flight of the wing-body structure of the unmanned aerial vehicle, and enhances the stability of the connection; the first mounting column 510 and the first mounting hole play a positioning role during installation; when the first plug 42 is inserted into the first socket 51, the mounting column can guide the plug to be accurately inserted into the socket, so that the installation process is faster and more accurate; meanwhile, the separation position can be easily found during disassembly, improving the convenience of operation.

[0031] The first socket 51 is provided with a first recess 511 on both sides, and the first plug 42 is provided with a first boss 420 matched with the first recess 511. The cooperation of the first boss 420 and the first recess 511 forms a mechanical locking structure after the plug is inserted into the socket; the locking can prevent the plug from being accidentally pulled out under the action of external force (such as vibration, pulling, etc.), ensuring the stability and reliability of the power connection; especially during the flight of the wing-body structure of the unmanned aerial vehicle, various bumps and shakes may be encountered, and the design can effectively maintain the connection of the plug and the socket firm; when the plug is inserted, the first boss 420 can slide along the edge of the first recess 511, playing a guiding role; this makes the plug more accurately inserted into the socket, reducing the risk of damage caused by inaccurate insertion, and also improving the efficiency of plug-in operation; the specific shape and position of the first boss 420 and the first recess 511 can play a role in preventing misplug; only when the direction of the plug is correct, the boss can be matched with the recess and inserted, avoiding safety problems such as circuit short circuit, equipment damage, etc. caused by incorrect insertion direction.

[0032] The second socket 52 is provided with a second mounting column 520 extending upward, and the second plug 61 is provided with a second mounting hole matched with the second mounting column 520. The cooperation of the second mounting column 520 and the second mounting hole provides an additional fixing point for the connection between the battery cell 60 and the mounting seat 50; during the operation of the wing-body structure of the unmanned aerial vehicle, it may be affected by various external forces such as vibration and acceleration, in order to prevent the second plug 61 from being accidentally loosened or fallen off from the second socket 52, ensuring the stability and reliability of power transmission; when installing the battery cell 60, the second mounting column 520 can guide the second plug 61 to be accurately inserted into the second socket 52, making the installation process faster and more accurate; the operator does not need to spend too much time to align the plug and the socket, improving the installation efficiency; the mounting column and the mounting hole with specific shape and position can play a certain role in preventing misplug; only the correct direction and position can make the mounting column and the mounting hole match, reducing the possibility of safety risks such as electrical failure, short circuit and even fire caused by incorrect connection.

[0033] The second recess 521 is arranged on two sides of the second socket 52, and the second boss 610 is arranged on two sides of the second plug 61 and matches the second recess 521. The matching of the second boss 610 and the second recess 521 forms a mechanical locking structure after the plug is inserted into the socket, effectively preventing the plug from being accidentally pulled out due to vibration, shaking or external force during the operation of the wing-body structure of the unmanned aerial vehicle, and ensuring that the power connection between the battery 60 and the mounting seat 50 is always stable and reliable. When the second plug 61 is inserted, the second boss 610 can slide along the edge of the second recess 521, providing clear guidance for the insertion of the plug. This enables the operator to more quickly and accurately insert the plug into the socket, reduces the risk of damage caused by inaccurate insertion, and improves the efficiency of the plug-in operation. The specific shape and position of the second boss 610 and the second recess 521 can prevent misinsertion. Only when the direction of the plug is correct, the boss can be matched with the recess and inserted, avoiding safety problems such as circuit short circuit and equipment damage caused by incorrect insertion direction.

[0034] The first propeller balancer 31 comprises a first fixing member 310 mounted on the shaft core 21, first swing arms 311 mounted on both sides of the first fixing member 310, and a first balance weight 312 connected to the free end of the first swing arms 311. The second propeller balancer 32 comprises a second fixing member 320 mounted on the shaft core 21, second swing arms 321 mounted on both sides of the second fixing member 320, and a second balance weight 322 connected to the free end of the second swing arms 321. When the propeller is unbalanced during rotation, the first propeller balancer 31 and the second propeller balancer 32 can quickly respond. Because the balance weight is located at the free end of the swing arm, it is very sensitive to changes in unbalanced force. Even a small imbalance can cause the swing arm to swing, causing the balance weight to displace accordingly to adjust the balance state of the propeller. During the flight of the wing-body structure of the unmanned aerial vehicle, various factors may cause the balance state of the propeller to change, such as airflow disturbance, load change, etc. The structural design can adjust the imbalance in real time to ensure that the wing-body structure of the unmanned aerial vehicle always maintains a stable flight attitude. The rapid response of the balance weight and the flexible movement of the swing arm enable the adjustment process to be completed in an instant, improving the flight stability and safety of the wing-body structure of the unmanned aerial vehicle.

[0035] The above only expresses the preferred technical solutions of the present application, which are described in more detail and in more detail, but cannot be understood as limiting the scope of the utility model patent. It should be noted that for ordinary skilled persons in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, and the present application also intends to include these changes and modifications.

Claims

1. A wing-body structure of a drone, characterized by, The unmanned aerial vehicle comprises a fuselage, a coaxial double propeller structure and an attitude adjusting structure.

2. The wing-body configuration of claim 1, wherein, The wing-body structure of the unmanned aerial vehicle further comprises a motor mounted on the fuselage.

3. The wing-body configuration of claim 2, wherein, The fuselage is further provided with a mounting seat, and the mounting seat is provided with a first socket.

4. The wing-body configuration of claim 3, wherein, The mounting seat is provided with a bottom-touching sensor, and the mounting seat is provided with a bottom-touching alarm matched with the bottom-touching sensor.

5. The wing-body configuration of claim 3, wherein, The fuselage is further provided with an electric core, and the mounting seat is provided with a second socket.

6. The wing-body configuration of claim 3, wherein, The first socket is provided with a first mounting column extending upward, and the first plug is provided with a first mounting hole matched with the first mounting column.

7. The wing-body structure of the drone according to claim 3, wherein, The first socket is provided with a first groove on both sides, and the first plug is provided with a first boss matched with the first groove.

8. The wing-body structure of the drone according to claim 5, wherein, The second socket is provided with a second mounting column extending upward, and the second plug is provided with a second mounting hole matched with the second mounting column.

9. The wing-body structure of the drone according to claim 5, wherein, The second socket is provided with a second groove on both sides, and the second plug is provided with a second boss matched with the second groove.

10. The wing-body configuration of claim 1, wherein, The first blade balancer comprises a first fixing member mounted on the shaft core, first swing arms mounted on both sides of the first fixing member, and a first balance weight connected to free ends of the first swing arms. The second blade balancer comprises a second fixing member mounted on the shaft core, second swing arms mounted on both sides of the second fixing member, and a second balance weight connected to free ends of the second swing arms.

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