Rotor wing propelling device and control method

A propulsion device and rotor technology, applied in the aviation field, can solve problems such as complex structures and complex control methods of aircraft, and achieve the effects of reliable transmission structure, reduced complexity, and low manufacturing cost

Pending Publication Date: 2021-12-21
HUNAN TAOXUN AVIATION TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the past ten years, with the research progress of composite materials, power systems, sensors, especially flight control and other technologies, unmanned helicopters have developed rapidly and are increasingly becoming the focus of attention; in the field of unmanned helicopters, Coaxial dual-rotor drones have become a new species in the aircraft industry; however, the technology of coaxial dual-rotor drones has many difficulties that need to be overcome. The control method of the aircraft is relatively complicated, and its structure is relatively more complicated.

Method used

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  • Rotor wing propelling device and control method
  • Rotor wing propelling device and control method
  • Rotor wing propelling device and control method

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Experimental program
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Effect test

Embodiment 1

[0035] Such as Figure 1-Figure 2 As shown, this embodiment discloses a rotor propulsion device, which includes an upper power mechanism 1 , a central axis tilt drive assembly 3 and an upper vector tilt rotor assembly 2 .

[0036]The upper power mechanism 1 includes an upper drive module 11, an upper fixed central shaft 13, and an upper rotor drive slide rail 12; the upper drive module 11 is arranged on the upper end of the upper fixed central shaft 13, and the upper drive module 11 is connected with the upper rotor drive slide rail 12 It is used to drive the upper rotor drive slide rail 12 to rotate around the upper fixed central axis 13 . The upper drive module 11 can be a direct-drive brushless motor, a brushless motor and gearbox, or a fuel engine. In this embodiment, the upper drive module 11 uses a direct-drive brushless motor. The stator is fixedly connected with the upper fixed center shaft 13, and the rotor of the direct-drive brushless motor is connected with the up...

Embodiment 2

[0047] Such as Figure 2-6 As shown, this embodiment discloses a coaxial double-rotor propulsion device. Compared with the rotor propulsion device in Embodiment 1, this embodiment is equivalent to two symmetrically distributed rotor propulsion devices in Embodiment 1. Through two The rotor propulsion devices work together, and the two rotor propulsion devices share the No. 1 driver 32 and the No. 2 driver 33. The specific structure is as follows:

[0048] A coaxial double-rotor propulsion device includes an upper power mechanism 1 , a center axis tilt drive assembly 3 , an upper vector tilt rotor assembly 2 , a lower power mechanism 5 and a lower vector tilt rotor assembly 4 .

[0049] The upper power mechanism 1 includes an upper drive module 11, an upper fixed central shaft 13, and an upper rotor drive slide rail 12; the upper drive module 11 is arranged on the upper end of the upper fixed central shaft 13, and the upper drive module 11 is connected with the upper rotor driv...

Embodiment 3

[0063] refer to Figure 7 , this embodiment discloses a coaxial twin-rotor helicopter, comprising a fuselage 6 and a coaxial twin-rotor propulsion device arranged above the fuselage 6, the coaxial twin-rotor propulsion device being the coaxial twin-rotor propulsion device in Embodiment 2 device.

[0064] A control method of a coaxial twin-rotor helicopter disclosed in this embodiment is as follows:

[0065] The heading of the aircraft is controlled by adjusting the rotational speed difference of the upper and lower rotors, and the tilt angles of the upper vector tilt rotor assembly 2 and the lower vector tilt rotor assembly 4 are controlled by the No. 1 driver 32 and the No. 2 driver 33 to adjust the lift direction generated by the paddle disc , so as to control the rolling and pitching motion of the aircraft;

[0066] By accelerating or decelerating the up and down rotors at the same time, adjust the lift of the aircraft.

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Abstract

The invention discloses a rotor wing propelling device and a control method. The rotor wing propelling device comprises an upper power mechanism, a lower power mechanism, a middle shaft inclination driving assembly, an upper vector inclination rotor wing assembly and a lower vector inclination rotor wing assembly. According to the rotor wing propelling device and the control method, the rotor disc of the rotor wing is directly subjected to inclined control, the structure is relatively simplified, the number of parts is relatively small, and control is simpler. Compared with a common vector rotor mechanism, the rotor mechanism is higher in maneuverability, faster in response and higher in efficiency.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a rotor propulsion device and a control method. Background technique [0002] In the past ten years, with the research progress of composite materials, power systems, sensors, especially flight control and other technologies, unmanned helicopters have developed rapidly and are increasingly becoming the focus of attention; in the field of unmanned helicopters, Coaxial dual-rotor drones have become a new species in the aircraft industry; however, the technology of coaxial dual-rotor drones has many difficulties that need to be overcome. The control method of the aircraft is relatively complicated, and its structure is relatively more complicated. . Contents of the invention [0003] The object of the present invention is to provide a rotor propulsion device and a control method in order to overcome the above problems. [0004] In order to achieve the above object, the method ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/14B64C27/10B64D35/00B64C27/52
CPCB64C27/14B64C27/10B64D35/00B64C27/52
Inventor 葛讯沈元郭述臻李良伟刘卫东
Owner HUNAN TAOXUN AVIATION TECH CO LTD
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