QUARTZ CERAMIC ANTENNA FAIRING OF A MISSILE AND THE METHOD OF ITS MANUFACTURE Russian patent published in 2018 - IPC H01Q1/42 

FIELD: antenna.

SUBSTANCE: invention "Quartz ceramics antenna fairing of a missile and the method of its production" refers to the construction and technology of manufacturing of antenna fairings of rockets made from ceramic materials, more precisely from quartz ceramics. Presented technical solution, including a shell of porous quartz ceramics, strengthened and hermetically sealed with an organopolymer and bonded to a metal frame from an invar alloy using a sealant, consists in the following: shell is a resonant structure with a thickening of the wall in the fastening zone of the frame by 15-45% in comparison with the radio-transparent zone in order to increase the strength and heat-shielding properties of the shell and to increase the axial thickness of the toe inside the shell to (0.3-1.0)λ - of the working wavelength of the antenna to improve the fairing, entirely made from quartz ceramics with a density of 1.97-2.01 g / cm³, bending strength of not lower than 50 MPa after hardening and sealing the inner and outer surfaces with an organopolymer for a total thickness (depth) of not more than 0.1λ. Method for manufacturing the rocket's antenna fairing includes forming a ceramic semi-finished part by slip casting in a gypsum form from an aqueous silica glass slip with SiO content₂ of not less than 99.9% at a moisture content of 13-16% of a polydisperse grain composition with a particle size in the range of 0.1-500 μm, sintering of the shell according to the regime, excluding the formation of cristobalite in the material to a density of 1.97-2.01 g / cm³, after which it is machined with a diamond tool to the specified parameters and the wall thickness with a thickening in the zone of the frame and sock, as well as the deposition and impregnation of the porous shell with an organopolymer, for example TMFT, MFSS-8, on the inner surface and fluoroplastic or silicone enamels on the outer surface to a total thickness of not more than 0.1λ.

EFFECT: proposed technical solution provides obtaining antenna fairings of missiles with improved radio technical and strength characteristics.

2 cl, 2 dwg