Abstract: A method and a device are described for compensation of mechanical stresses in an aircraft structure. The method comprises the steps of producing signals that represent mechanical stresses occurring in the aircraft structure, and operating actuators, which absorb at least some of the mechanical stresses and are arranged in the aircraft structure, such that the mechanical stresses are compensated.

Abstract: A method for manufacturing a fiber-composite component with a cladding field and a primary component for reinforcing the fiber-composite component includes the steps of: applying a prepreg semifinished product to a mold to form the cladding field, where in the prepreg semifinished product fibers extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fiber-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fiber-composite fuselage component of an aircraft with a shell component with at least one re

Abstract: A hull structure is provided, for use in particular in an aircraft or spacecraft, the hull structure including an outer skin and structural components which are connected to said skin, as well as an inner lining which forms a supporting structure together with the outer skin and the structural components.

Abstract: A method for manufacturing a fibre-composite component with a cladding field and a primary component for reinforcing the fibre-composite component includes the steps of: applying a prepreg semifinished product to a mould to form the cladding field, where in the prepreg semifinished product fibres extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fibre-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fibre-composite fuselage component of an aircraft with a shell component with at least one r

Abstract: A method and a device are described for compensation of mechanical stresses in an aircraft structure. The method comprises the steps of producing signals that represent mechanical stresses occurring in the aircraft structure, and operating actuators, which absorb at least some of the mechanical stresses and are arranged in the aircraft structure, such that the mechanical stresses are compensated.

Abstract: The present invention provides a hull structure, for use in particular in an aircraft or spacecraft, the hull structure comprising an outer skin and structural components which are connected to said skin, as well as an inner lining which forms a supporting structure together with the outer skin and the structural components.

Abstract: An intercostal for an aircraft for dissipating a load from a first frame onto a second frame and/or a skin of the aircraft, the intercostal having a framework.

Abstract: An intercostal for an aircraft for dissipating a load from a first frame onto a second frame and/or a skin of the aircraft, the intercostal having a framework.