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Power system and aircraft

A technology of power system and aircraft, applied in the field of power system and aircraft, can solve the problems of hindering the inhalation of downwash airflow, reducing the aerodynamic efficiency of aircraft, and reducing the aerodynamic efficiency of aircraft

Active Publication Date: 2018-03-27
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 aircraft
  • Power system and aircraft
  • Power system and aircraft

Examples

Experimental program
Comparison scheme
Effect test

no. 1 example

[0039] 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. 2 example

[0051] As a description of the second embodiment of the power system and the aircraft of the present invention, only the structure of the power system will be described below.

[0052] see Figure 10 and Figure 11 , power system 2 is made of duct 21, the first rotor unit, the second rotor unit, deflector 24 and fixed support 25, the first rotor unit is made of the first rotor 221 and the first drive motor 222, the second rotor unit Consists of the second rotor 231 and the second drive motor 232, the rotor shaft of the first drive motor 222 passes through the through hole formed in the rotor shaft of the second drive motor 232, and is coaxially arranged with the rotor shaft of the second drive motor 232 . From the lower lip of the duct 21 to the bottom of the second rotor 231, there are four deflectors 24 arranged radially along the duct 21, and the guide surfaces of the deflectors 24 are parallel to the center line of the duct 21. , four deflectors 24 are evenly distribute...

no. 3 example

[0057] As a description of the third embodiment of the power system and aircraft of the present invention, only the differences from the second embodiment of the power system and aircraft described above will be described below.

[0058] see Figure 13 The ratio of the paddle diameter of the first rotor 321 of the power system 3 to the paddle diameter of the second rotor 331 is 0.6, the first rotor 321 is located below the second rotor 331, and the rotor shaft of the second drive motor 332 passes through the rotor shaft formed in the second rotor 331. The through hole in the rotor shaft of a driving motor 322 is coaxially arranged with the rotor shaft of the first driving motor 322 .

[0059] During the flight of the aircraft, the downwash flow formed by the rotation of the first rotor 321 mainly passes through the blade root area of ​​the second rotor 331 , effectively supplementing the downwash flow in this area.

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PUM

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Abstract

The invention relates to a power system and an aircraft constructed by the power system. The power system comprises a duct, a first rotor wing unit and a second rotor wing unit, wherein the first rotor wing unit comprises first rotor wings; the second rotor wing unit comprises second rotor wings; the axis of the first rotor wings is collinear with the axis of the second rotor wings; the rotation directions of the first rotor wings and the second rotor wings for providing downwash airflow for a paddle root region of the second rotor wings are opposite; the ratio of the paddle diameter of the first rotor wing to the paddle diameter of the second rotor wing is 0.3-0.6. The moving devices driven by airflow and constructed by the power system, such as the aircraft, have good pneumatic efficiency.

Description

technical field [0001] The invention relates to a power system with two rotors coaxially arranged and an aircraft built with the power system. Background technique [0002] An 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 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. CN101934858A discloses a small electric ducted propeller type intelligent unmanned aerial vehicle, which consists of ducts, brackets, coaxial counter rotors, fairings, batteries, motors, drive control circuits and microcontrolle...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/32B64D35/00
Inventor 何春旺
Owner ZHUHAI PANLEI INTELLIGENT TECH CO LTD