Cross-type coaxial tilting rotor amphibious drone

A tilt-rotor, cross-shaped technology, applied in the direction of rotorcraft, unmanned aircraft, motor vehicles, etc., can solve the problems of difficult to complete underwater operations, slow response speed, instability, etc., to achieve flexible adjustment, Reduce forward resistance and ensure the effect of underwater work

Pending Publication Date: 2019-09-27
GUANGDONG UNIV OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention provides a cross-shaped coaxial tilt-rotor amphibious UAV to solve the problems that the existing

Method used

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  • Cross-type coaxial tilting rotor amphibious drone
  • Cross-type coaxial tilting rotor amphibious drone
  • Cross-type coaxial tilting rotor amphibious drone

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Embodiment 1

[0033] A cross-shaped coaxial tilt-rotor amphibious UAV, such as figure 1 and Figure 4 As shown, it includes a body 1, a tilting coaxial multi-rotor mechanism located on the body 1, and a waterproof sealed cabin 15. A power supply module and a flight control module are installed in the waterproof sealed cabin 15, and the flight control module is connected to the The tilting coaxial multi-rotor mechanism and the power module are electrically connected.

[0034] Wherein, the tilting coaxial multi-rotor mechanism is a tilting coaxial eight-rotor mechanism composed of a fixed rotor structure and a tilting rotor structure.

[0035] Wherein, the tilt rotor structure includes a first tilt rotor substructure and a second tilt rotor substructure which are arranged symmetrically;

[0036] Such as figure 2As shown, the first tilting rotor substructure includes a first waterproof steering gear 21, a first pipe connector 22, a first pipe clamp 23, a first bearing 24, a first machine a...

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Abstract

The invention discloses a cross-type coaxial tilting rotor amphibious drone which comprises a drone body, a tilting-type coaxial multi-rotor mechanism and a waterproof sealed cabin, wherein the tilting-type coaxial multi-rotor mechanism and the waterproof sealed cabin are arranged on the drone body; a power module and a flight control module are mounted in the waterproof sealed cabin; the flight control module is electrically connected with the tilting-type coaxial multi-rotor mechanism and the power module; and the tilting-type coaxial multi-rotor mechanism is designed to be a tilting-type coaxial eight-rotor mechanism composed of a fixed rotor structure and a tilting-type rotor mechanism. The cross-type coaxial tilting rotor amphibious drone disclosed by the invention is equipped with the tilting-type coaxial eight-rotor mechanism; through the tilting control of rotors, the circumstance that the counter torsion moment is changed through the acceleration and deceleration of motors, and then the yaw angle of the drone body is changed can be replaced; during the underwater operation, the motors on two sides can be tilted forward, the drone body can be kept horizontal so as to reduce the resistance, and the utilization efficiency of the maximum lift force of the motors can be improved; and the own rotation and work of the cross-type coaxial tilting rotor amphibious drone under the air and underwater high-resistance conditions can be achieved.

Description

technical field [0001] The invention relates to the technical field of amphibious drones, in particular to a cross-shaped coaxial tilt-rotor amphibious drone. Background technique [0002] Modern countries generally use multi-rotor UAVs to complete object detection tasks in the air, and use submersibles to complete underwater detection tasks. However, there is no good solution for detection areas that require frequent water-air transitions, which brings inconvenience to detection. In addition, most of the existing multi-rotor UAVs use the same steering motor to speed up and reverse the direction of the motor to decelerate to control the direction and size of the counter-torque resultant force of the propeller; The motor located in the rear half of the fuselage accelerates to tilt the fuselage. However, under this control method, when the take-off weight of the aircraft is greater than half of the total lift of the motor, the stability and response speed of the aircraft will ...

Claims

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Application Information

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IPC IPC(8): B64C35/00B64C27/08B64C27/10B64C27/52B64D27/24
CPCB64C35/008B64C27/08B64C27/10B64C27/52B64D27/24B64U50/19Y02T50/60
Inventor 杨嘉鹏邓一晖谢礼杰郭皓天郑宗楷鲁仁全
Owner GUANGDONG UNIV OF TECH
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