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Electric aircraft driven by hybrid power battery

A power battery, electric aircraft technology, applied in the direction of battery/battery traction, electric vehicles, power plant types, etc. The problem of poor resistance to impact deformation, etc., to achieve the effect of improving reliability and safety, high power, and long cruising time

Pending Publication Date: 2020-01-17
高洪江
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to overcome the energy density of lithium-ion batteries in the prior art that cannot meet the needs of long-range flight of electric aircraft, the lithium-ion battery is prone to thermal runaway, the lithium-ion battery has poor shock resistance and deformation resistance, and a single battery module cannot achieve safety. Redundancy and other issues

Method used

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  • Electric aircraft driven by hybrid power battery
  • Electric aircraft driven by hybrid power battery
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Embodiment Construction

[0026] The technical solutions in the embodiments of the present invention will be clearly and completely described below, obviously, the described embodiments are only some of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by persons of ordinary skill in the art based on the embodiments of the present invention belong to the protection scope of the present invention.

[0027] The present invention will be described in detail below with reference to the accompanying drawings and examples. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0028] In the description of the present invention, the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and does not require that...

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Abstract

The invention provides an electric aircraft driven by a hybrid power battery. Two power battery devices are arranged on the electric aircraft, the first power battery device is a secondary battery module, and the second power battery device is a fuel battery module, so that the technical advantages of a secondary battery module and a fuel battery module can be fully utilized, the characteristics of high power and low energy density of a lithium ion battery are exerted, the high-power power supply is provided at the take-off stage, and the characteristics of high energy density and low power ofa metal-air battery are exerted for mileage increase or emergency. The electric aircraft driven by the hybrid power battery solves the power requirement problem for electric power during the takeoffprocess of the electric aircraft and the energy requirement problem for electric power during long-voyage cruise flight, improves the reliability and safety of a power system of the electric aircraft,and has the characteristics of small pollution, safety, long cruise time, long voyage and the like.

Description

technical field [0001] The invention relates to the technical field of electric aircraft, in particular to an electric aircraft driven by a hybrid battery. Background technique [0002] In response to energy and environmental crises, countries are stepping up efforts to develop a variety of new electric aircraft, including multi-rotor and fixed-wing. Electric aircraft are generally powered by power battery modules, and the performance requirements for power battery modules include power density (kw / kg) and energy density (KWh / kg). Electric aircraft have different power requirements in different flight phases, the power is the highest during the take-off phase, and the power is lower during the cruising and descending altitude phases. [0003] Electric aircraft generally use secondary battery modules, such as lithium-ion power battery modules, as a power source. The lithium-ion power battery module has the characteristics of high discharge rate and high power. The power-typ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/24B60L50/75
CPCB64D27/24B60L50/75Y02T50/60Y02T90/40Y02T10/70
Inventor 高洪江杜明洹
Owner 高洪江
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