Trapezoidal wing

A trapezoidal wing technology, applied to the shape of the wing, motor vehicles, unmanned aircraft, etc., can solve the problem of reducing the stealth of the wing, and achieve the effect of improving stealth performance and reducing electromagnetic scattering energy

Active Publication Date: 2018-06-01
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For a trapezoidal wing, the trailing edge of the wing will also produce edge diffraction at different azimuth angles, which poses a greater challenge to reduce the stealth of the wing

Method used

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  • Trapezoidal wing
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Embodiment Construction

[0013] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. 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. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention especially relates to a trapezoidal wing, belonging to the field of aircraft structure designing. According to the invention, a wedge shape is designed for the leading edge (3) of the trapezoidal wing, so specular reflection at the leading edge (3) of the trapezoidal wing is reduced, and a strong scattering source is changed into a weak scattering source; a sawtooth shape is designedfor the trailing edge (4) of the trapezoidal wing, so the azimuth angle, generating edge diffraction, of the trailing edge (4) of the trapezoidal wing is identical to the azimuth angle, generating specular reflection, of the leading edge (3) of the trapezoidal wing, the main energy of the radar echo of an aircraft is controlled to within few narrow orientations, which enables the number of RCS wave peaks to be reduced; and furthermore, a wave-absorbing structure is arranged between every two sawteeth at the trailing edge (4) of the wing, so various weak points and hysteresis loss of the electromagnetic energy of incident waves in wave-absorbing materials are converted into heat which is dissipated. The trapezoidal wing of the invention is improved in stealth performance in the two aspectsof appearance stealth and material stealth.

Description

technical field [0001] The invention relates to the field of aircraft structure design, in particular to a trapezoidal wing. Background technique [0002] Due to military needs and the development of modern science and technology, the detection technology for aircraft is becoming more and more perfect, which poses a serious threat to the survivability of aircraft in war. Stealth performance has become an important indicator of the survivability of military aircraft and is a measure of An important criterion for the advanced nature of future military aircraft. [0003] As an important part of an aircraft, the wing is also an important source of electromagnetic scattering. Under the illumination of radar waves, the leading edge of the wing will produce a specular reflection. For the trapezoidal wing, the trailing edge of the wing will also produce edge diffraction at different azimuth angles, which brings a greater challenge to reducing the stealth of the wing. Contents of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/10
CPCB64C3/10B64U20/10
Inventor 刘建言王健崔力张扬张维仁王文颖艾俊强
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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