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Composite wing unmanned aerial vehicle and pneumatic balance method

An aerodynamic balance and UAV technology, applied in the field of aviation flight, can solve the problems of damaged wings, inability to achieve aerodynamic balance, UAV control experience, aerial photography, gimbal shake frequency, battery life, etc.

Pending Publication Date: 2022-04-05
重庆交通大学绿色航空技术研究院 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] During the vertical take-off and landing flight, the drone is vulnerable to the influence of natural wind, and the power provided by the propeller of the drone itself cannot achieve aerodynamic balance, which makes the drone hover in the air or take off and land. Swing, which not only has a great impact on the UAV control experience, the vibration frequency of the aerial photography gimbal, and the battery life, but even causes the wing of the UAV to collide with the ground during take-off and landing. damaged

Method used

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  • Composite wing unmanned aerial vehicle and pneumatic balance method
  • Composite wing unmanned aerial vehicle and pneumatic balance method
  • Composite wing unmanned aerial vehicle and pneumatic balance method

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Embodiment Construction

[0025] figure 1 It is a structural schematic diagram of the present invention, as shown in the figure, the compound wing UAV in this embodiment includes a fuselage 1, a left wing 2 and a right wing 3 located on both sides of the fuselage 1, and a wing located at the front end of the fuselage 1. The main rotor 4 and the auxiliary rotor installed on the wing; also include an aerodynamic balance mechanism, the aerodynamic balance mechanism includes an air chamber 01 installed on the fuselage 1 and a drainage tube connected to the air chamber 01, and every two drainage tubes are one A group of the drainage tubes includes a left drainage tube 02 and a right drainage tube 03 respectively located on the wings on both sides of the fuselage 1, and the air outlet direction of the left drainage tube 02 is the same as that of the right drainage tube 03. As shown in the figure, this solution integrates the main rotor 4, left wing 2, right wing 3 and auxiliary rotor on the fuselage 1, so th...

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Abstract

The invention discloses a composite wing unmanned aerial vehicle and an aerodynamic balance method. The composite wing unmanned aerial vehicle comprises a fuselage, wings located on the two sides of the fuselage, a main rotor located at the front end of the fuselage and auxiliary rotors installed on the wings. The unmanned aerial vehicle further comprises a pneumatic balance mechanism, the pneumatic balance mechanism comprises an air chamber installed on the vehicle body and drainage pipes connected to the air chamber, every two drainage pipes form a group, and each group of drainage pipes comprises a left drainage pipe and a right drainage pipe which are located on wings on the two sides of the vehicle body correspondingly. The controllability of the unmanned aerial vehicle is improved, and the use safety of the unmanned aerial vehicle is improved.

Description

technical field [0001] The invention relates to the field of aviation flight, in particular to a compound wing unmanned aerial vehicle and an aerodynamic balancing method. Background technique [0002] During the vertical take-off and landing flight, the drone is vulnerable to the influence of natural wind, and the power provided by the propeller of the drone itself cannot achieve aerodynamic balance, which makes the drone hover in the air or take off and land. Swing, which not only has a great impact on the UAV control experience, the vibration frequency of the aerial photography gimbal, and the battery life, but even causes the wing of the UAV to collide with the ground during take-off and landing. damaged. [0003] Therefore, in order to solve the above problems, a compound-wing unmanned aerial vehicle and an aerodynamic balance method are needed, which can reduce the instability of the unmanned aerial vehicle during hovering or take-off and landing, improve the maneuver...

Claims

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Application Information

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IPC IPC(8): B64C27/22B64C15/00
Inventor 于洋梁思佳杨理于涛杨雅琳李睿哲
Owner 重庆交通大学绿色航空技术研究院
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