FIELD: composite materials.
SUBSTANCE: invention is related specifically to a method for manufacturing a honeycomb panel from a carbon fiber prepreg, and can be used in rocket and aircraft construction, in manufacturing of three-layer structures with increased resistance to loads at high temperatures. In manufacturing of a three-layer panel, a unidirectional carbon prepreg is wound on a mandrel in the form of a metal tube with a section of a given diameter and length, and the carbon prepreg from twill fabric is prepared for curing in a flat form, then the facing plates and mandrels with the prepreg wound on them are cured, after which the mandrels are removed from cured tubes, and the tubes are cut into equal parts of the required size, prepared for gluing, then each tube is wrapped with cyanate ester adhesive film, placed in a crimping mandrel to form a honeycomb sheet and cured, after which the honeycomb block is removed from the crimping mandrel and cut into a core of the required thickness, they are processed and covered with previously cured facing plates on both sides, laying a cyanate ester adhesive film between the plates and the filler, after which the three-layer panel is placed in a vacuum bag and cured.
EFFECT: invention ensures improved performance and uniform strength of the three-layer panel structure at high temperatures.
3 cl, 3 dwg, 1 tbl
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Authors
Dates
2023-06-06—Published
2022-05-16—Filed