FIELD: aviation.
SUBSTANCE: proposed composite beam (18) with built-in breakage initiator has strip (20) sinusoidal in section and lower flange (22). Strip (20) is stacked from at least one central layer of unidirectional carbon fibers oriented in depth of beam and aramide fabric layers and carbon fiber layer. Lower flange (22) is bonded on side of strip (20) and lower edge of each layer of unidirectional carbon fibers is shifted backward from respective edges of fabric layers and cuts in form of saw teeth are made on this lower edge for beginning of breakage in case of aircraft accident. Aircraft fuselage has framework with bracing frames whose lower parts are approximately straight and are connected with external skin by means of at least two composite beams (18).
EFFECT: possibility of absorbing compressive force in case of aircraft accident.
15 cl, 4 dwg
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