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Power device of electric manned aircraft and electric manned aircraft

A power device and aircraft technology, applied in aircraft, motor vehicles, transportation and packaging, etc., can solve the problems of large battery ionization consumption, uneven discharge of battery power system, etc., and achieve the effect of stable operation

Pending Publication Date: 2021-06-22
GUANGDONG HUITIAN AEROSPACE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Normally, one ESC corresponds to one motor to control. When the electric manned aircraft flies to one side for a long time, the ionization consumption of the battery on one side will be relatively large, while the battery power consumption on the other side will be small, and the battery power system will be discharged. will be uneven

Method used

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  • Power device of electric manned aircraft and electric manned aircraft
  • Power device of electric manned aircraft and electric manned aircraft
  • Power device of electric manned aircraft and electric manned aircraft

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Embodiment Construction

[0028] Embodiments of the present application are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application.

[0029] Please also refer to figure 1 , the embodiment of the present application provides a power unit 10 of an electric manned aircraft. The power unit 10 includes a plurality of motor units 101 and a plurality of battery units 108 corresponding to the plurality of motor units 101 . Wherein, one motor set 101 includes multiple motors 1011 . A battery pack 108 includes multiple batteries, and each battery in the battery pack 108 is independently connected to a corresponding motor pack 101 to supply power to multiple motors ...

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Abstract

The invention discloses a power device of an electric manned aircraft and the electric manned aircraft. The power device comprises a plurality of motor sets and a plurality of battery packs corresponding to the motor sets. One motor group comprises a plurality of motors, one battery pack comprises a plurality of batteries, and each battery in the battery pack is independently connected with the corresponding motor group so as to supply power to the plurality of motors in the motor group. According to the power device of the electric manned aircraft and the electric manned aircraft, the independent batteries in the battery pack are used for supplying power to the multiple motors in the motor set, the electric quantity of the multiple batteries in the battery pack can be balanced, the voltage difference of the multiple batteries is kept relatively stable, and normal and stable operation of the batteries is ensured.

Description

technical field [0001] The present application relates to the technical field of battery charging, in particular to a power device of an electric manned aircraft and the electric manned aircraft. Background technique [0002] In the power system of a multi-rotor electric manned aircraft, generally each battery is connected to an ESC, and each ESC is connected to a motor, and the motor drives the propeller to rotate to realize the takeoff, landing and flight of the aircraft. Normally, one ESC corresponds to one motor to control. When the electric manned aircraft flies to one side for a long time, the ionization consumption of the battery on one side will be relatively large, while the battery power consumption on the other side will be small, and the battery power system will be discharged. will be uneven. Contents of the invention [0003] In view of this, embodiments of the present application provide a power device of an electric manned aircraft and the electric manned ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/24B64C27/08
CPCB64D27/24B64C27/08Y02T50/60
Inventor 赵德力全洪飞李杰伍惠康
Owner GUANGDONG HUITIAN AEROSPACE TECH CO LTD
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