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Wing spar/energy storage battery integrated structure

An energy storage battery and wing spar technology, which is applied in the directions of wings, power plant types, power plant cooling systems, etc. Disassembly and maintenance, reduced shape and structural design constraints, and the effect of avoiding extra weight

Active Publication Date: 2016-12-21
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This arrangement of energy storage batteries is not conducive to the concentrated force of the wing spar, but also brings excess structural weight. The flight time and range of solar-powered aircraft largely depend on energy consumption and weight, so this arrangement is not suitable. Conducive to the improvement of solar aircraft performance

Method used

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  • Wing spar/energy storage battery integrated structure
  • Wing spar/energy storage battery integrated structure
  • Wing spar/energy storage battery integrated structure

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Embodiment Construction

[0023] Below in conjunction with accompanying drawing, the present invention is described in further detail.

[0024] The present invention is a spar / energy storage battery integrated structure, the spar 1 of the wing is designed as a cylindrical structure, and the energy storage battery 2 is installed inside, such as figure 1 shown.

[0025] Such as figure 2 As shown, the wing spar 1 is designed to have three layers, which are carbon fiber shell 101, PMI foam interlayer 102, and Kevlar inner wall 103 from outside to inside. The carbon fiber shell 101 has good strength and rigidity, and mainly bears tension, pressure and shear force; the PMI foam interlayer 102 is light in weight, mainly bears bending moments and torques, and has strong resistance to instability; the Kevlar inner wall 103 has high strength, good toughness, and It is suitable for bearing tension and shear force and preventing the foam interlayer from breaking. The above-mentioned carbon fiber shell 101 and ...

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Abstract

The invention discloses a wing spar / energy storage battery integrated structure, belonging to the field of flight vehicle design. The structure adopts a wing spar with a square section, and the energy storage battery is fixed in the wing spar by a rib strip and a positioning bolt, so that the wing spar is loaded intensively; a PMI foaming layer is arranged in the wing spar, so that the PMI foaming layer is not only used as a sandwich structure to bear shearing stress and also used as thermal insulation material to carry out thermal insulation for an energy storage battery; cooling fans are arranged at the two ends of the wing spar, and convection is formed by the gap between the rib strips so as to cool the energy storage battery. On the premise of guaranteeing the work temperature of the energy storage battery, the stress characteristic of the wing spar can be greatly improved, meanwhile, the structure is simplified, and the weight is reduced, so that a solar-powered airplane has higher flight efficiency.

Description

technical field [0001] The invention belongs to the field of aircraft design and specifically designs a novel wing spar / energy storage battery integrated structure that can improve the force characteristics of the wing spar, control the working temperature of the energy storage battery, and reduce the structural quality of the aircraft. Background technique [0002] In order to reduce drag, solar-powered aircraft usually use large aspect ratio wings, which have poor structural rigidity and serious deformation of the wings under working conditions. Long-endurance solar-powered aircraft need energy storage batteries to store excess energy during the day for night flight. Most solar-powered aircraft use lithium-ion batteries as energy storage batteries, and their working temperature range is usually 0-40°C. When a solar-powered aircraft is flying at low altitude, the ambient temperature is high, and the energy storage battery generates heat, and the temperature will exceed 60°C...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/32B64D27/24B64D33/08
CPCB64C3/32B64D27/24B64D33/08
Inventor 马东立张良杨穆清王少奇夏兴禄
Owner BEIHANG UNIV
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