Airbody structure of ducted unmanned aerial vehicle

Abstract

The utility model discloses an airframe structure of a ducted unmanned aerial vehicle. The device comprises a main beam, a flight control module mounting table is fixed to the upper end face of the main beam, a flight control module is fixed to the flight control module mounting table, the flight control module mounting table comprises an upper fixing plate and a lower fixing plate, the lower fixing plate is fixed to the top face of the main beam, the upper fixing plate is arranged above the lower fixing plate, and a lower damping seat is fixed between the upper fixing plate and the lower fixing plate; an upper damping base is fixed to the top face of the upper fixing plate, and the flight control module is fixed to the upper damping base. The utility model has the beneficial effects that the connection mode is simple and convenient, and the system is convenient to install and maintain; the influence of vibration on the flight control module can be reduced in the flight process, so that the effect of protecting the flight control module is achieved, and the flight stability and precision are improved; it is ensured that the flight control system is not affected by vibration of the unmanned aerial vehicle, and signal accuracy of the flight control system is ensured; the ground contact bounce amplitude of the undercarriage is reduced, and the automatic landing point precision is improved.

Description

Technical Field

[0001] The utility model relates to the technical field related to the body of an unmanned aerial vehicle (UAV), and in particular to a body structure of a ducted UAV. Background Art

[0002] Unmanned aerial vehicle (UAV) is an unmanned aircraft that is controlled by a radio remote control device and a self-contained program control device, or is operated completely or intermittently autonomously by an onboard computer.

[0003] Compared with rotor-type UAVs, ducted UAVs have many advantages, such as small size, regular external shape, easy to carry, store and transport, and suitable for cluster operations, because the lift fan is embedded inside the fuselage.

[0004] During the flight of existing ducted UAVs, the flight control module is easily affected by the vibration of the UAV, resulting in a decrease in its ability to control flight stability and accuracy.

[0005] In summary, there is a need for a ducted UAV body structure that can improve flight stability and accuracy. Utility Model Content

[0006] The utility model aims to overcome the deficiency that the flight control module is easily affected by the vibration of the UAV during flight, which leads to a reduction in its control ability of flight stability and accuracy, and provides a body structure of a ducted UAV that can improve flight stability and accuracy.

[0007] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0008] A body structure of a ducted unmanned aerial vehicle includes a main beam, a flight control module mounting platform is fixed to the upper end surface of the main beam, a flight control module is fixed on the flight control module mounting platform, the flight control module mounting platform includes an upper fixing plate and a lower fixing plate, the lower fixing plate is fixed to the top surface of the main beam, the upper fixing plate is placed above the lower fixing plate with a lower shock absorber seat fixed therebetween, an upper shock absorber seat is fixed to the top surface of the upper fixing plate, and the flight control module is fixed on the upper shock absorber seat.

[0009] The flight control module is mounted on the upper shock mount of the flight control module mounting platform. This simple and convenient connection facilitates system installation and maintenance. Vibration from the main beam is transmitted to the flight control module through the lower mounting plate, lower shock mount, upper mounting plate, and upper shock mount. The design of the lower and upper shock mounts reduces the impact of vibration on the flight control module during flight, thereby protecting the module and improving flight stability and accuracy.

[0010] Preferably, the flight control module is located at the center of the upper mounting plate, with the upper shock absorbers symmetrically located at the four corners of the bottom surface of the flight control module, and the lower shock absorbers symmetrically located at the four corners of the bottom surface of the upper mounting plate. By symmetrically positioning the upper and lower shock absorbers to support the flight control module, the flight control module's stability can be effectively improved during flight, while also reducing the module's bounce upon touchdown, thereby protecting the flight control module and enhancing the drone's flight stability and accuracy.

[0011] Preferably, the upper shock absorber seat includes a support rod 1, and a cylindrical base 1 is fixed to both the upper and lower ends of the support rod 1, the cylindrical base 1 at the lower end of the support rod is fixed to the top surface of the upper fixed plate, and the cylindrical base 1 at the upper end of the support rod 1 is fixed to the bottom surface of the flight control module, and the lower shock absorber seat includes a support rod 2, and a cylindrical base 2 is fixed to both the upper and lower ends of the support rod 2, the cylindrical base 2 at the lower end of the support rod 2 is fixed to the top surface of the lower fixed plate, and the cylindrical base 2 at the upper end of the support rod 2 is fixed to the bottom surface of the upper fixed plate. The upper shock absorber seat and the lower shock absorber seat are both made of elastic materials such as rubber and tetrafluoroethylene. The support rod height and cylindrical base size of the upper shock absorber seat and the support rod height and cylindrical base size of the lower shock absorber seat are calculated according to the natural frequency formula: Calculated using the formula (π), where π is the circumference of the circle, k is the stiffness, and m is the mass. By adjusting the strut height and cylindrical base size of the upper and lower shock absorbers, the mass m, which determines the natural frequency of the shock absorber, can be adjusted. By choosing different materials, such as rubber or Teflon, the stiffness k of the shock absorber can be varied. Designers can calculate how the upper and lower shock absorbers can filter out vibrations of varying frequencies, ensuring that the flight control system is unaffected by drone vibrations and ensuring accurate flight control system signals.

[0012] Preferably, the main beam is provided with a landing gear, which is fixed to the lower end surface of the main beam and symmetrically arranged on the front and rear sides of the flight control module. The symmetrical arrangement of the front and rear landing gears provides support for the drone, effectively improving the stability of the drone's posture during automatic landing, while also reducing the landing gear's ground bounce and improving the accuracy of the automatic landing point.

[0013] Preferably, a fixed bracket and a telescopic bracket are mounted on both the left and right side walls of the main beam. The fixed brackets are positioned on either side of the telescopic bracket, located in the same horizontal plane, and symmetrically positioned on the left and right sides of the flight control module. This symmetrical design of the fixed brackets and the telescopic brackets effectively improves the stability of the flight control module during flight, reduces the module's bounce upon touchdown, protects the module, and enhances the drone's flight stability and accuracy.

[0014] Preferably, the material of the main beam and the material of the landing gear are both carbon fiber materials, which reduce the weight of the fuselage structure and carry a certain weight load. The material of the fixed frame and the material of the telescopic frame are both aviation aluminum 7075, which play a role in structural strengthening and reinforcement, and have high strength, good mechanical properties, excellent wear resistance and corrosion resistance.

[0015] The beneficial effects of the present invention are: the connection method is simple and convenient, which is convenient for system installation and maintenance; it can reduce the impact of vibration on the flight control module during flight, thereby protecting the flight control module and improving the stability and accuracy of flight; it ensures that the flight control system is not affected by the vibration of the drone and ensures the accuracy of the signal of the flight control system; it reduces the bounce amplitude of the landing gear touching the ground and improves the accuracy of the automatic landing point; it reduces the weight of the fuselage structure and bears a certain weight load; it has high strength, good mechanical properties, excellent wear resistance and corrosion resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a three-dimensional diagram of the utility model;

[0017] Figure 2 yes Figure 1 Enlarged view of point A in the middle;

[0018] Figure 3 It is a top view of the present utility model.

[0019] Figure: 1. Main beam, 2. Flight control module, 3. Upper fixing plate, 4. Lower fixing plate, 5. Support rod 1, 6. Cylindrical base 1, 7. Support rod 2, 8. Cylindrical base 2, 9. Landing gear, 10. Fixed frame, 11. Telescopic frame. DETAILED DESCRIPTION

[0020] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0021] like Figure 1 、 Figure 2 and Figure 3 In the described embodiment, a body structure of a ducted UAV includes a main beam 1, a flight control module mounting platform is fixed to the upper end surface of the main beam 1, a flight control module 2 is fixed on the flight control module mounting platform, the flight control module mounting platform includes an upper fixing plate 3 and a lower fixing plate 4, the lower fixing plate 4 is fixed on the top surface of the main beam 1, the upper fixing plate 3 is placed above the lower fixing plate 4 and a lower shock absorber seat is fixed between the two, an upper shock absorber seat is fixed on the top surface of the upper fixing plate 3, and the flight control module 2 is fixed on the upper shock absorber seat.

[0022] The flight control module 2 is located at the center of the upper fixing plate 3 , the upper shock absorbers are symmetrically distributed at the four corners of the bottom surface of the flight control module 2 , and the lower shock absorbers are symmetrically distributed at the four corners of the bottom surface of the upper fixing plate 3 .

[0023] The upper shock absorber seat includes a support rod 1 5, and a cylindrical base 1 6 is fixed to the upper and lower ends of the support rod 1 5. The cylindrical base 1 6 at the lower end of the support rod 1 5 is fixed to the top surface of the upper fixed plate 3, and the cylindrical base 1 6 at the upper end of the support rod 1 5 is fixed to the bottom surface of the flight control module 2. The lower shock absorber seat includes a support rod 2 7, and a cylindrical base 2 8 is fixed to the upper and lower ends of the support rod 2 7. The cylindrical base 2 8 at the lower end of the support rod 2 7 is fixed to the top surface of the lower fixed plate 4, and the cylindrical base 2 8 at the upper end of the support rod 2 7 is fixed to the bottom surface of the upper fixed plate 3.

[0024] The main beam 1 is provided with a landing gear 9 , which is fixed on the lower end surface of the main beam 1 . The landing gear 9 is symmetrically arranged on the front and rear sides of the flight control module 2 .

[0025] A fixed frame 10 and a telescopic frame 11 are installed on the left and right side walls of the main beam 1. The fixed frame 10 is placed on the front and rear sides of the telescopic frame 11. The fixed frame 10 and the telescopic frame 11 are located in the same horizontal plane. The fixed frame 10 and the telescopic frame 11 are symmetrically arranged on the left and right sides of the flight control module 2.

[0026] The main beam 1 and the landing gear 9 are both made of carbon fiber, and the fixing frame 10 and the telescopic frame 11 are both made of aviation aluminum 7075.

[0027] The vibration on the main beam 1 is transmitted to the flight control module 2 through the lower fixing plate 4, the lower shock absorber seat, the upper fixing plate 3 and the upper shock absorber seat in sequence. Through the design of the lower shock absorber seat and the upper shock absorber seat, the impact of vibration on the flight control module 2 can be reduced during flight.

[0028] The upper and lower shock absorber seats are both made of elastic materials such as rubber and tetrafluoroethylene. The height of the upper shock absorber's support rod 5 and the size of the cylindrical base 6, and the height of the lower shock absorber's support rod 27 and the size of the cylindrical base 28 are calculated based on the natural frequency formula: Calculated as follows: π is pi, k is stiffness, and m is mass. By adjusting the height of the upper shock absorber's support rod 15 and the size of the cylindrical base 16, and the height of the lower shock absorber's support rod 27 and the size of the cylindrical base 28, the natural frequency of the shock absorber, mass m, can be adjusted. By choosing different materials, such as rubber or tetrafluoroethylene, the stiffness k of the shock absorber can be changed. According to the designers' calculations, the upper and lower shock absorbers can filter out vibrations of different frequencies, ensuring that the flight control system is not affected by drone vibrations.

[0029] The flight control module 2 is supported by the mutually symmetrical upper and lower shock absorber seats, the UAV is supported by the mutually symmetrical landing gear 9 on the front and rear sides, and the mutually symmetrical fixed frames 10 and telescopic frames 11 are designed to effectively improve the stability of the flight control module 2 during flight, while reducing the bounce amplitude of the flight control module 2 when touching the ground, thereby protecting the flight control module 2 and improving the flight stability and accuracy of the UAV.

Claims

1. A ducted UAV body structure, characterized by: The invention comprises a main beam (1), wherein a flight control module mounting platform is fixed on the upper end surface of the main beam (1), a flight control module (2) is fixed on the flight control module mounting platform, and the flight control module mounting platform comprises an upper fixing plate (3) and a lower fixing plate (4), wherein the lower fixing plate (4) is fixed on the top surface of the main beam (1), the upper fixing plate (3) is placed above the lower fixing plate (4) and a lower shock-absorbing seat is fixed between the upper fixing plate (3), an upper shock-absorbing seat is fixed on the top surface of the upper fixing plate (3), and the flight control module (2) is fixed on the upper shock-absorbing seat.

2. The body structure of a ducted UAV according to claim 1, characterized in that: The flight control module (2) is located at the center of the upper fixed plate (3), the upper shock absorbing seats are symmetrically distributed at the four corners of the bottom surface of the flight control module (2), and the lower shock absorbing seats are symmetrically distributed at the four corners of the bottom surface of the upper fixed plate (3).

3. The body structure of a ducted UAV according to claim 2, characterized in that: The upper shock-absorbing seat comprises a support rod (5), and the upper and lower ends of the support rod (5) are both fixed with a cylindrical base (6), the cylindrical base (6) at the lower end of the support rod (5) is fixed on the top surface of the upper fixed plate (3), and the cylindrical base (6) at the upper end of the support rod (5) is fixed on the bottom surface of the flight control module (2), and the lower shock-absorbing seat comprises a support rod (7), and the upper and lower ends of the support rod (7) are both fixed with a cylindrical base (8), the cylindrical base (8) at the lower end of the support rod (7) is fixed on the top surface of the lower fixed plate (4), and the cylindrical base (8) at the upper end of the support rod (7) is fixed on the bottom surface of the upper fixed plate (3).

4. The body structure of a ducted UAV according to any one of claims 1 to 3, characterized in that: A landing gear (9) is provided on the main beam (1), and the landing gear (9) is fixed on the lower end surface of the main beam (1). The landing gear (9) is symmetrically arranged on the front and rear sides of the flight control module (2).

5. The body structure of a ducted UAV according to claim 4, characterized in that: A fixing frame (10) and a telescopic frame (11) are installed on both left and right side walls of the main beam (1), the fixing frame (10) is placed on the front and rear sides of the telescopic frame (11), the fixing frame (10) and the telescopic frame (11) are located in the same horizontal plane, and the fixing frame (10) and the telescopic frame (11) are symmetrically arranged on the left and right sides of the flight control module (2).

6. The body structure of a ducted UAV according to claim 5, characterized in that: The material of the main beam (1) and the material of the landing gear (9) are both carbon fiber materials, and the material of the fixing frame (10) and the material of the telescopic frame (11) are both aviation aluminum 7075.

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