US 12,145,715 B2
Composite element and method of manufacturing the same
Mika Mustakangas, Halli (FI)
Assigned to Patria Aerostructures Oy, Halli (FI)
Appl. No. 16/603,495
Filed by Patria Aerostructures Oy, Halli (FI)
PCT Filed Apr. 6, 2018, PCT No. PCT/FI2018/050252
§ 371(c)(1), (2) Date Oct. 7, 2019,
PCT Pub. No. WO2018/185377, PCT Pub. Date Oct. 11, 2018.
Claims priority of application No. 20175325 (FI), filed on Apr. 7, 2017.
Prior Publication US 2021/0300518 A1, Sep. 30, 2021
Int. Cl. B64C 1/00 (2006.01); B29C 70/34 (2006.01); B29C 70/68 (2006.01); B29K 307/04 (2006.01); B29K 705/02 (2006.01); B29L 31/30 (2006.01)
CPC B64C 1/00 (2013.01) [B29C 70/34 (2013.01); B29C 70/68 (2013.01); B29K 2307/04 (2013.01); B29K 2705/02 (2013.01); B29L 2031/3076 (2013.01); B64C 2001/0072 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A composite element comprising:
a first skin plate and a second skin plate, which are both prefabricated composite elements comprising basic composite structure;
inner surfaces and outer surfaces of the skin plates, and wherein the inner surfaces are fastened permanently to form a composite element structure;
at least the first skin plate comprises several protrusions on the outer surface of the first skin plate for providing it with local stiffeners;
several additional first composite structures attached to the first skin plate only at locations of each of the several protrusions;
and wherein the several additional first composite structures form inner stiffeners at the several protrusions and are covered by the basic composite structure of the first skin plate on outer surface side of the composite element;
wherein
the first skin plate and the second skin plate are formed by a laminating technique; the basic composite structure of the first skin plate and the several additional first composite structures attached on an inner surface of the first skin plate are being bulged together at the several protrusions;
the several additional first composite structures are laminated on the inner surface of the first skin plate and are laminated at positions to form the several protrusions for the first skin plate; and
wherein the laminated additional first composite structures comprise reinforcing fibers which are oriented in only a longitudinal direction, whereby the laminated additional first composite structures are double layer structures each of which has a folded end at the inner surface of the first skin plate and another end that is towards the second skin plate, whereby said another end comprises edges of the laminated additional first composite structures, and
facing layers of the double layer structures and the edges at said another end are against each other and in direct contact with each other, wherein the composite element is a component of an aircraft.