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Power system and multicopter

A multi-rotor aircraft and power system technology, applied in aircraft, motor vehicles, rotorcraft, etc., can solve problems such as energy loss, reduced aerodynamic efficiency of aircraft, and obstruction of downwash air inhalation.

Active Publication Date: 2020-03-31
ZHUHAI PANLEI INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During the flight, since the upper and lower rotors have the same blade diameter, the linear speed of rotation at each point on the blade gradually increases along the direction from the root of the two blades to the tip of the blade, so that the air is washed down in the area adjacent to the root of the blade. The flow rate is very small. Since the shape of the blade changes gradually from the root to the tip, the downwash flow in the middle of the blade is the largest. When the speed of the upper rotor is higher than that of the lower rotor, the downwash air generated by the upper rotor hits the lower rotor. If the speed of the upper rotor is lower than that of the lower rotor, the upper rotor will hinder the inhalation of the downwash airflow of the lower rotor, both of which will reduce the aerodynamic efficiency of the aircraft; even if the upper rotor The rotation speed of the rotor and the lower rotor is kept the same. When the blades of the upper rotor and the lower rotor overlap in the radial direction, there will be more serious air friction between the upper rotor and the lower rotor, which also reduces the aerodynamic efficiency of the aircraft.
In addition, the upper and lower rotors with equal propeller diameters are prone to airflow vibration noise during rotation, and the generation of vibration noise reduces the energy utilization rate of the aircraft

Method used

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  • Power system and multicopter
  • Power system and multicopter
  • Power system and multicopter

Examples

Experimental program
Comparison scheme
Effect test

no. 1 example

[0038] see figure 1 and figure 2 , the multi-axis aircraft 1 is composed of a frame and a control unit installed on the frame, an anti-torque control device 14, a travel control unit 15, a power system, a power supply and 4 side rotor units. Power system is made of duct 11 and the first rotor unit and the second rotor unit placed in duct 11; 4 side rotor units are the first duct fan 16 evenly distributed in the periphery of duct 11, the second Ducted fan 17, the first ducted fan 18 and the second ducted fan 19; a cross-shaped mounting bracket 111 is fixed in the duct 11, the first rotor 12 in the first rotor unit and the second rotor in the second rotor unit The driving motor of the rotor 13 is installed on the mounting bracket 111 by a fixed bracket, the axis of the first rotor 12 and the axis of the second rotor 13 are all collinear with the center line of the duct 11, and the first rotor 12 is positioned above the second rotor 13; The first ducted fans 16, 18 and the sec...

no. 4 example

[0060] As an illustration of the fourth embodiment of the power system and multi-axis aircraft of the present invention, only the differences from the second embodiment of the above-mentioned power system and multi-axis aircraft will be described below.

[0061] see Figure 14 , the power system 4 places the deflector originally placed at the lower lip of the duct between the first rotor 421 and the second rotor 431, the first drive motor 422 is located above the deflector 44, the first rotor 421 and the second rotor 431 The ratio of the blade diameter of the second rotor 431 is 0.5.

no. 5 example

[0063] As an explanation of the fifth embodiment of the power system and multi-axis aircraft of the present invention, only the differences from the fourth embodiment of the above-mentioned power system and multi-axis aircraft will be described below.

[0064] see Figure 15 , the second rotor unit of the power system 5 is located above the deflector 54 , the first rotor unit is located below the deflector 54 , and the second drive motor 532 is located above the second rotor 531 . The ratio of the paddle diameters of the first rotor 521 to the second rotor 531 is 0.4.

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Abstract

The invention relates to a power system and a multi-rotor aircraft comprising the same, wherein the power system comprises a duct, a first rotor wing unit and a second rotor wing unit; the first rotor wing unit comprises a first rotor wing; the second rotor wing unit comprises a second rotor wing; both an axis of the first rotor wing and an axis of the second rotor wing are collinear with a central line of the duct; the rotational directions of the first rotor wing and the second rotor wing are opposite; both the first rotor wing and the second rotor wing are arranged in the duct; the propeller diameter of the first rotor wing used for providing downwash flow for a propeller root region of the second rotor wing is smaller than that of the second rotor wing. The multi-rotor aircraft comprising the power system has good pneumatic efficiency.

Description

technical field [0001] The invention relates to a power system with two rotors coaxially arranged and a multi-axis aircraft constructed with the power system. Background technique [0002] A multi-axis aircraft usually includes a frame and more than one power system and control unit installed on the frame. The power system usually includes more than one rotor unit. The rotor unit usually includes a power device and a rotor driven by the power device. The angle of the blades of the rotors is a fixed value, and the flight attitude of the aircraft is adjusted by changing the relative rotational speeds between different rotors during the flight. The control unit usually includes a detection sensor, a control circuit board, and an ESC. The ESC is used to adjust the rotation speed of the rotor; the control unit is used to detect the flight attitude of the aircraft and regulate the power unit to control the aircraft's attitude, direction, and speed. [0003] Publication No. CN1019...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/10B64C27/32
Inventor 何春旺
Owner ZHUHAI PANLEI INTELLIGENT TECH CO LTD