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Supporting structure of electric aircraft power battery system

A technology of supporting structure and power battery, applied in the field of aircraft, can solve the problems of increasing the thickness of the structure, reducing the weight and volume of the aircraft and power battery system, and achieving the effect of reducing the strength requirement, increasing the effective income, and reducing the weight

Active Publication Date: 2020-05-05
成都沃飞天驭科技有限公司 +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the low energy density of batteries, the power battery system of pure electric aircraft is heavy and large, and its weight accounts for about 30% of the maximum take-off weight of the aircraft. As a result, it is necessary to provide a strong installation platform when installing the battery system. support
[0003] In the case of an emergency landing of an aircraft, the mass items in the cabin that may harm the crew will experience a large forward static inertial load; the current power battery system is installed on the installation platform supported by the fuselage frame. The local thickness provides more structural strength to bear the forward load of the power battery system in emergency landing situations, and increasing the structural thickness results in weight gain, which will inevitably reduce the effective load of the aircraft and reduce the economy of the aircraft

Method used

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  • Supporting structure of electric aircraft power battery system
  • Supporting structure of electric aircraft power battery system
  • Supporting structure of electric aircraft power battery system

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Embodiment Construction

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0027] Reference herein to "one embodiment" or "an embodiment" refers to a particular feature, structure or characteristic that can be included in at least one implementation of the present invention. In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "top", "bottom" etc. is based on the orientation or positional relationship shown in the drawings, and i...

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Abstract

The invention discloses a supporting structure of an electric aircraft power battery system. The supporting structure comprises a longitudinal beam, a supporting rod, a first connector and a second connector, wherein the longitudinal beam is located on one side of a power battery system and fixed to a fuselage of the electric aircraft, the first connector is arranged on the power battery system and used for being connected with a first end of the supporting rod, the second connector is arranged at an end, away from the power battery system, of the longitudinal beam and used for connecting thesecond end of the supporting rod. The supporting structure of the electric aircraft power battery system is advantaged in that the forward load of a power battery system mounting platform is shared, the strength requirement of a fuselage frame structure is reduced, so the weight of the fuselage frame structure is reduced, and economy and safety of the aircraft structure are improved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a support structure for a power battery system of an electric aircraft. Background technique [0002] Pure electric aircraft use power battery system and motor system instead of internal combustion engine power. Pure electric aircraft has the characteristics of simple structure, easy operation and use, good maintainability, low cost of use, and good economy. In terms of design, the overall layout of the pure electric aircraft is flexible, and the optimal layout and innovative layout can be adopted, and the aircraft with extraordinary performance can be designed to meet the needs of special purposes. However, due to the low energy density of the battery, the power battery system of a pure electric aircraft is heavy and bulky, and its weight accounts for about 30% of the maximum take-off weight of the aircraft. As a result, when installing the battery system, it is necessary to p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/26B64D27/24
CPCB64D27/24B64D27/40Y02T50/40
Inventor 吕金泽汤晓明周龙超陈修贤李军军
Owner 成都沃飞天驭科技有限公司
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