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Integral hollow sandwich composite material for ice detection function skin

A composite material, the overall hollow technology, applied in the direction of deicing device, fuselage bulkhead, wing, etc., to achieve the effect of avoiding damage, high specific modulus, and compact skin structure

Active Publication Date: 2021-07-27
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the deficiencies of the prior art, the technical problem to be solved by the present invention is to provide an integral hollow interlayer composite material ice detection function skin, which solves the problem of wrapping the ice detection detector in the skin structure, so that the skin structure has the ice detection function The problem

Method used

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  • Integral hollow sandwich composite material for ice detection function skin
  • Integral hollow sandwich composite material for ice detection function skin
  • Integral hollow sandwich composite material for ice detection function skin

Examples

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Embodiment

[0032] Such as figure 1 As shown, an integral hollow interlayer composite material ice detecting function skin includes an outer panel 1, an inner panel 2, a core material 3 and an ultrasonic echo ice detector 4;

[0033] The core material 3 runs alternately between the outer panel 1 and the inner panel 2, forming an "8"-shaped structure;

[0034] There is a hollow structure between adjacent core materials 3, which can also be used for embedding wires or embedding functional devices.

[0035] Ultrasonic echo icing detectors 4 are embedded between adjacent core materials 3;

[0036] Both the outer panel 1 and the inner panel 2 are composed of fiber bundle layers;

[0037] The core material 3 is a fiber bundle;

[0038] The fiber bundles of the core material 3 run through the fiber bundle layup of the outer panel 1 and the inner panel 2 as warp yarns of the fiber bundle layup.

[0039] The thickness of the outer panel 1 and the inner panel 2 is 0.5 mm, and the thickness of t...

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Abstract

The invention discloses an ice detection function skin of an integral hollow interlayer composite material, which belongs to the field of aircraft structure design. Including the outer panel, inner panel, core material and ultrasonic echo icing detector; the core material alternately runs through the outer panel and the inner panel to form an "8"-shaped structure; the adjacent core materials are hollow structures; the ultrasonic echo The wave icing detector is embedded between the core materials; both the outer panel and the inner panel are composed of fiber bundles; the core material is fiber bundles; Bundle the warp of the layup. The skin with ice detection function obtained by the present invention has a compact structure, and the inner and outer surfaces of the skin do not need protrusions, which not only avoids damage to the aerodynamic shape of the aircraft wing, but also does not occupy the inner space of the wing, and the skin of the integral hollow interlayer composite material is resistant to delamination. The layer has excellent performance, and has high specific modulus and specific strength.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, and in particular relates to an ice-detecting function skin of an integral hollow interlayer composite material. Background technique [0002] Aircraft icing and anti-icing / deicing have always been one of the key points of aircraft design, and icing detection related technologies are an important part of this field. The currently commonly used axial vibration icing detection device needs to be installed on the outer surface of the airframe, which will have a certain impact on the aerodynamic shape of the aircraft, and will greatly increase the workload of fluid grid division and subsequent aerodynamic calculations in CFD analysis. [0003] Based on the above problems, through the analysis of structural characteristics, the parts prone to icing such as the leading edge of the wing in the airframe structure have the conditions to use the ice detection function skin. At present, there is no...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/12B64C3/26B64D15/20
CPCB64C1/12B64C3/26B64D15/20
Inventor 蔡登安陆方舟徐澧明周光明
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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