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Wing leading edge of multifunctional solar aircraft

A wing leading edge, solar energy technology, applied in the direction of wings, aircraft parts, transportation and packaging, etc., can solve the problems of increasing the weight of the aircraft structure, damage to the spar, etc., to reduce weight, increase stability, and increase reusability Effect

Inactive Publication Date: 2016-04-06
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The energy storage batteries of the existing solar-powered aircraft are concentratedly placed on the fuselage, and because the operating temperature of the solar-powered aircraft is about -60 degrees when flying in the adjacent space, a heating and heat preservation structure is usually added on the surface of the energy storage battery to ensure the storage The energy battery can work normally; however, the concentrated placement of the energy storage battery on the fuselage will generate a concentrated load, resulting in a large stress on the spar, which is likely to cause damage to the wing spar; and the heat preservation structure of the energy storage battery increases the structure of the aircraft. weight

Method used

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  • Wing leading edge of multifunctional solar aircraft
  • Wing leading edge of multifunctional solar aircraft
  • Wing leading edge of multifunctional solar aircraft

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Embodiment Construction

[0024] The specific embodiments of the present invention will be described in further detail below in conjunction with the drawings and embodiments.

[0025] The present invention provides a wing leading edge of a multifunctional solar-powered aircraft. The wing leading edge includes: a leading edge body 1, an energy storage battery 2 and an outer shell 3;

[0026] The front edge main body 1 is made of foam material, and a battery compartment is arranged inside it, and the energy storage battery 2 is placed in the battery compartment;

[0027] The front edge body 1 is covered with an outer shell 3.

[0028] Preferably, in order to increase the heat preservation effect of the energy storage battery 2, a heating tape is attached to the energy storage battery 2.

[0029] In the present invention, by arranging the energy storage battery in the leading edge of the foam material, the leading edge structure not only maintains the aerodynamic shape of the front edge of the wing, but also serves...

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Abstract

The invention relates to the technical field of unmanned aerial vehicles, and provides a wing leading edge of a multifunctional solar aircraft. The wing leading edge comprises a leading edge body, energy storage batteries and an outer shell, wherein the leading edge body is made of foam materials, a battery cabin is formed in the leading edge body, and the energy storage batteries are placed in the battery cabin; the leading edge body is wrapped with the outer shell. According to the wing leading edge, the energy storage batteries can be kept warm, and the structural weight of the aircraft is reduced.

Description

Technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to the leading edge of a multifunctional solar-powered aircraft wing. Background technique [0002] The energy storage batteries of the existing solar aircraft are concentrated on the fuselage, and because the operating temperature of the solar aircraft is about -60 degrees when flying in close space, a heating and heat preservation structure is usually added on the surface of the energy storage battery to ensure storage The energy storage battery can work normally; however, the concentrated placement of the energy storage battery on the fuselage will generate a concentrated load, resulting in a large stress on the spar, which is likely to cause damage to the spar; and the thermal insulation structure of the energy storage battery increases the structure of the aircraft weight. Summary of the invention [0003] The technical problem to be solved by the present invention ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/00
CPCB64C3/00
Inventor 侯中喜郭正杨砚恒闫秋飞杨希祥柳兆伟刘多能麻震宇陈立立
Owner NAT UNIV OF DEFENSE TECH
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