FIELD: transport.
SUBSTANCE: invention relates to structure made of composite material (CM) with a hole made in it and concerns aircraft (AC) wing and body. Structure made of CM is bottom skin of AC main wing. The structure contains structural element (SE) with holes and adjacent SE. The holes are access holes. Main wing bottom skin is formed by SE with holes and adjacent SE having separation surfaces passing in longitudinal direction of the main wing and connecting SE with holes with adjacent SE. Adjacent SE is connected with side section of SE with holes. SE with holes and adjacent SE are made so that they take up tensile load and/or compression load acting in longitudinal direction of a wing. Full rigidity of SE with holes under tension and/or compression in longitudinal direction of AC wing is less than Full rigidity of adjacent SE under tension and/or compression in longitudinal direction. Also, structure made of CM can be AC body skin. Body skin is formed by SE with holes and adjacent SE having separation surfaces passing in longitudinal direction of body and connecting SE with holes with adjacent SE. In this case, the holes are holes used as windows into which window material is set.
EFFECT: lower weight of CM structure, lower concentration of stresses occurring at peripheral edge of holes, simpler design of hole edge reinforcement.
8 cl, 18 dwg
