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Visible light window assembly for supersonic flight vehicle

A window component and visible light technology, which is applied to aircraft parts, aircraft accessories, fuselage, etc., can solve the problems of large impact and achieve the effects of reducing heat flux density, satisfying heat insulation, and satisfying light transmittance

Active Publication Date: 2019-04-12
TIANJIN JINHANG INST OF TECH PHYSICS
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  • Abstract
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  • Claims
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Problems solved by technology

[0004] The invention proposes a visible light window assembly of supersonic aircraft to solve the technical problems of how to improve heat insulation, light transmission, short-time large impact resistance and high temperature resistance

Method used

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  • Visible light window assembly for supersonic flight vehicle

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Embodiment Construction

[0018] In order to make the purpose, content and advantages of the present invention clearer, the specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0019] This embodiment proposes a visible light window assembly suitable for the outer surface of a supersonic vehicle, and its structure is as follows figure 1 shown. The visible light window assembly includes assembly mounting screws 1, supersonic vehicle skin 2, assembly mounting gland 3, metal rubber damping ring 4, window pressure ring screw 5, window lower pressure ring 6, window upper pressure ring 7, outer layer Window glass 8, inner window glass 9, and window glass spacer 10.

[0020] The material of the outer layer window glass 8 and the inner layer window glass 9 is fused silica, and the fused silica material has a high transmittance to visible light and ultraviolet light with a wavelength less than 4 micron...

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Abstract

The invention belongs to the technical field of optical window design, and specifically relates to a visible light window assembly suitable for the outer surface of a supersonic flight vehicle. The visible light window assembly includes assembly mounting screws, supersonic flight vehicle skins, assembly mounting glands, metal rubber damper rings, window pressing ring screws, window lower pressingrings, window upper pressing rings, outer layer window glass, inner layer window glass, and window glass spacers. The visible light window assembly adopts fused silica glass as a light transmissive material, and the material is high in transmittance for visible light, is opaque to infrared radiation, satisfies transmittance of light, and satisfies heat insulation; double-layer window design is employed, an air gap layer between double layers of windows enables heat flux density of heat conduction to be greatly reduced, and a purpose of effective heat insulation is achieved; and the metal rubber damping rings are connected in series between the visible light window and the supersonic flight vehicle skins, are resistant to high temperature and resistant to short-time big impact, and ensure installation stiffness of the visible light window.

Description

technical field [0001] The invention belongs to the technical field of optical window design, and in particular relates to a visible light window assembly suitable for the outer surface of a supersonic aircraft. Background technique [0002] The currently developed supersonic vehicle has a flight speed of Mach 4, and its outer surface temperature is close to 500°C, which is very high. The supersonic vehicle is designed with an explosive bolt near its visible light window assembly. When the explosive bolt is working, it will produce a 0.3ms, 1000g impact on the visible light window assembly, which is a short-term large impact. Therefore, it is necessary to develop a visible light window assembly with heat insulation, light transmission, short-term large impact resistance and high temperature resistance according to the characteristics of supersonic aircraft. Contents of the invention [0003] (1) Technical problems to be solved [0004] The invention proposes a visible li...

Claims

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Application Information

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IPC IPC(8): B64C1/14
CPCB64C1/1484
Inventor 王丰年孙凯
Owner TIANJIN JINHANG INST OF TECH PHYSICS
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