Patent DE-102007023622-A1 (DE)
Title: Device for aircraft construction, comprises carbon fiber reinforced plastic components that are connected to each other on batch over connecting members in non-positive manner, linking braces, and a receiving structure
Inventor: MOERICKE DANGER
IPC: B64C1/00
Filed: 2007-05-18
Abstract: The device for aircraft construction, comprises carbon fiber reinforced plastic components that are connected to each other on batch over connecting members (1) in non-positive manner. The first component is a base structure component that is an aircraft fuselage having a matrix like recess. The recess and its connecting members form a non-positive connection. The recess is formed as seats for the ends guidable over the first end of the connecting member. A receiving structure is intended at further component and aerodynamic wings and control surface. The device for aircraft construction, comprises carbon fiber reinforced plastic components that are connected to each other on batch over connecting members (1) in non-positive manner. The first component is a base structure component that is an aircraft fuselage having a matrix like recess. The recess and its connecting members form a non-positive connection. The recess is formed as seats for the ends guidable over the first end of the connecting member. A receiving structure is intended at further component and aerodynamic wings and control surface for the connecting member guidable over the second end of the connecting member. The connecting member consists of a cavity like cylinder (3). Microstructures (2) out of interior cylinders (4) provided to each other are arranged in the interior of the cavity like cylinder with different intervals. The interior cylinders have different diameter and different wall strength. Linking braces (5) supporting in the spacer area are arranged between the inner cylinder and the inner part of the outer cylinder. The connecting member has a cone form, pyramid form, ball form or a similar outside form on an external rectangular form. The inner micro structure has cylindrical or similarly formed components. The recess has an inner microstructure on the base-structure component. The inner microstructure is formed complementary to the microstructure of the connecting elements. The complementary formed connection surface of the both microstructures is subjected with an epoxy resin composition after the insertion of the connection element in the recess of the aircraft fuselage and forms a connection producing a material interference having congruent positions in non-positive manner. Stable stiffeners are formed in and on the recess of the aircraft fuselage. The first edge area of the first opening has a butt at the first end of base-structure component and the second edge area of the second opening has same butt at the second end different from the first end of the base-structure component. The microstructures of the connecting member and the microstructures in the recess of the base-structure body are formed according to detected load path of the load line and load concentration distribution of the power vectors gripping on the base-structure body from lateral forces and associated power of the external aerodynamic wings and control surface. For strengthening the layers of the load line within the connection between the layers in the load guiding area and the load concentration distribution area, titanium containing hybrid stiffeners are arranged in the microsystems of the connecting member and the microsystems of the recess of the base-structure component. Integrally arranged grid works and complementary passing plunger like mold are integrated in the both microsystems. For the generation of paths, resin composition with high shear force compatibility and energy leading phase for indurations are intended according to a mixing system from self produced energy and externally produced energy in the material. A simple physical pump system with dosage device is intended for the injection of resin composition material in the cylinder like hollow area. Carbon fiber reinforced plastic connecting members are intended for the connection of light metal component in the aircraft construction. The pretreatment material is etching, coating or adhesive material. The matrix system like macro-connection structure spread over the surface of the base structure body has connection elements and recesses for the reception of connection members. The load path of the load direction area and the load concentration distribution area optimally passes through uniform quantity distribution. The macro-connection structure on the surface of the base structure body has connecting membrane-recess of the base structure component for a first matrix of the connection system, and a second superimposed strip layer connection matrix. The matrix arrangement with the microsystem is formed on the connecting membrane and with microsystem. The aircraft fuselage to be connected and aerodynamic wings and control surface to be connected are formed as module system. A spectrum of modules is formed different categories. The transmission of different connection load and/or vector moderately directed power is intended from a first to second component. The microsystem and the macrosystem are intended for the connection of structure elements of each dimension internally within the aerodynamic wings and control surface or for connection of structure element internally within the aircraft fuselage.