항공기 동체 스킨-스트링거 일체 성형 복합재 패널 제작 공법에 관한 연구

Method for Fabricating a Skin-Stringer Co-Cure Composite Panel for an Aircraft Body

A method for fabricating a skin-stringer Co-cure structure is investigated in which the existing skin and stringer assembly structure of an aircraft fuselage is formed by applying the composite air bladder bagging process with autoclave equipment. Most aircraft fuselage composite parts are in Korea using pre-impregnated material-based autoclave processes, and the skins and stringers are separately molded into parts and assembled by applying adhesives and fasteners to develop composite parts. In this case, the assembly labor-hours and manufacturing cost both increase because a separate assembly tool needs to be manufactured. To compensate for this, a method of forming a composite skin and stringer of an aircraft fuselage in a Co-cure structure by using an autoclave process was studied to produce a part specimen of the fuselage to ascertain the forming possibility and identify manufacturing problems.