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A method for producing a composite structure having a three-dimensionally curved portion and a cylindrical portion, comprising the steps of: (a) placing an outer skin made of a composite prepreg on a forming die; (b) mounting a honeycomb core on a portion of the outer skin that forms the three-dimen

A method for producing a composite structure having a three-dimensionally curved portion and a cylindrical portion, comprising the steps of: (a) placing an outer skin made of a composite prepreg on a forming die; (b) mounting a honeycomb core on a portion of the outer skin that forms the three-dimensionally curved portion; (c) superimposing an inner skin made of a composite prepreg thereon; (d) arranging a preformed frame member and a preformed stringer member each made of a composite prepreg on a portion of the inner skin that forms the cylindrical portion to prepare an assembly; and (e) forming the assembly by heating under a pressure. A composite structure of the present invention can be produced by the method.

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1. A method for producing a composite structure having a three-dimensionally curved portion and a cylindrical portion, comprising the steps of: (a) placing an outer skin made of a composite prepreg on a forming die; (b) mounting a honeycomb core on a portion of said outer skin that forms said three-

1. A method for producing a composite structure having a three-dimensionally curved portion and a cylindrical portion, comprising the steps of: (a) placing an outer skin made of a composite prepreg on a forming die; (b) mounting a honeycomb core on a portion of said outer skin that forms said three-dimensionally curved portion; (c) superimposing an inner skin made of a composite prepreg thereon; (d) arranging a preformed frame member and a preformed stringer member each made of a composite prepreg on a portion of said inner skin that forms said cylindrical portion to prepare an assembly; and (e) forming said assembly by heating under a pressure, wherein said assembly is formed by heating under a pressure while disposing an elastic plate and a press plate on a fin portion where said outer skin and said inner skin overlap each other. 2. The method for producing a composite structure according to claim 1, wherein said assembly is formed by heating under a pressure of 6 to 7 kg/cm2. 3. The method for producing a composite structure according to claim 1, wherein a plurality of said preformed frame members are linearly arranged at an interval on said portion of said inner skin that forms said cylindrical portion, one or more of preformed stringer members passing through said interval and intersecting said preformed frame members; and said assembly is formed by heating while using a forming jig comprising a combination of an elastic jig engageable with the intersection of said preformed frame members and said one or more of preformed stringer members, and rigid jigs attachable to said preformed frame members and said one or more of preformed stringer members in portions other than said intersection. 4. The method for producing a composite structure according to claim 1, wherein said composite structure constitutes part of an aircraft body.