Airplane surface temperature detection system

A technology for detection systems and aircraft surfaces, applied to thermometers, thermometers with physical/chemical changes, measuring devices, etc., to achieve the effects of low integration level, improved flight performance, and increased lift-to-drag ratio

Inactive Publication Date: 2016-08-10
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

[0005] The object of the present invention is to provide a kind of aircraft surface temperature detection system, utilize intelligent skin

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Embodiment Construction

[0020] 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 discloses an airplane surface temperature detection system and belongs to the airplane temperature detection technology field. The airplane surface temperature detection system comprises a sheath, a single-mode fiber, a multi-mode fiber, a hollow tube, a laser device and a photoelectric coupler, wherein one end of the single-mode fiber is connected with the laser device, one end of the multi-mode fiber is connected with the photoelectric coupler, the hollow tube is embedded in the sheath, the other end of the single-mode fiber and the other end of the multi-mode fiber are arranged in the hollow tube, end faces of the single-mode fiber and of the multi-mode fiber and the hollow tube form an enclosed chamber, the end faces of the single-mode fiber and of the multi-mode fiber are in parallel with each other in the enclosed chamber, the end faces are bonded with high reflection films, and light signals emitted by the laser device pass through the single-mode fiber, then pass through the enclosed chamber and pass through the multi-mode fiber to enter the photoelectric coupler. The airplane surface temperature detection system is advantaged in that weight of an aircraft can be reduced, the space is saved, design is simplified, and stealth and anti-electromagnetic interference of an airplane are facilitated.

Description

technical field [0001] The invention relates to the technical field of aircraft temperature detection, in particular to an aircraft surface temperature detection system. Background technique [0002] In the traditional design concept, the skin is only a structural structure that meets the requirements of aerodynamics and strength. When it is necessary to install sensors to measure the surface temperature, holes are drilled in the skin, which brings unnecessary structural and other losses, and the integration level is low. [0003] Future wars will become increasingly complex and changeable, the multi-dimensional battlefield environment will become increasingly severe and interpenetrating, and the requirements for the survivability of weapons and equipment will become higher and higher; on the other hand, the design of military aircraft will become increasingly complex, integrated, multi-functional and multi-purpose. These two pose considerable challenges to the design of air...

Claims

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Application Information

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IPC IPC(8): G01K11/32G01K11/322G01K11/324
CPCG01K11/32
Inventor 杨林
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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