Electronic arrangement for an aircraft and method for providing such an electronic arrangement

An electronic arrangement for an aircraft comprising:

• a structural portion of a structure of the aircraft which comprises
• a reinforcement arrangement of elongate longitudinal and transverse reinforcement elements which are connected to each other,
• an outer skin which is arranged at one side of the reinforcement arrangement and which is secured to the longitudinal and transverse reinforcement elements, wherein a face of the outer skin facing away from them forms an outer face of the structural portion, and
• one or more skin panels, each of which is a portion of the outer skin which is defined between two directly adjacent longitudinal reinforcement elements of the longitudinal reinforcement elements and two directly adjacent transverse reinforcement elements of the transverse reinforcement elements, and
• one or more structural elements, each of which has a frame and one or more electronic components which are secured to the frame,
• wherein, in at least one of the skin panels in the outer skin, an opening, which is arranged completely in the skin panel, is formed, and for each skin panel with the opening, an associated element of the structural elements is provided separately and is configured and is releasably secured with the frame thereof to the outer skin in the corresponding skin panel at the side of the outer skin opposite the outer face, such that the associated element closes a corresponding opening such that the skin panel has at least the same pressure tightness and at least the same resistance with respect to tensile, pressure and shearing forces which act in an extent direction of the outer skin in the skin panel as the same skin panel without the corresponding opening,
• wherein the structural portion has at least two of the skin panels and at least two of the structural elements, wherein at least two of the skin panels are arranged adjacent to each other and the structural elements which are associated with these skin panels are configured such that at least one of the electronic components thereof is common to the structural elements and is secured to the frame of each of the structural elements.

An electronic arrangement for an aircraft comprising:

• a structural portion of a structure of the aircraft which comprises
• a reinforcement arrangement of elongate longitudinal and transverse reinforcement elements which are connected to each other,
• an outer skin which is arranged at one side of the reinforcement arrangement and which is secured to the longitudinal and transverse reinforcement elements, wherein a face of the outer skin facing away from them forms an outer face of the structural portion, and
• one or more skin panels, each of which is a portion of the outer skin which is defined between two directly adjacent longitudinal reinforcement elements of the longitudinal reinforcement elements and two directly adjacent transverse reinforcement elements of the transverse reinforcement elements, and
• one or more structural elements, each of which has a frame and one or more electronic components which are secured to the frame,
• wherein, in at least one of the skin panels in the outer skin, an opening, which is arranged completely in the skin panel, is formed, and for each skin panel with the opening, an associated element of the structural elements is provided separately and is configured and is releasably secured with the frame thereof to the outer skin in the corresponding skin panel at the side of the outer skin opposite the outer face, such that the associated element closes a corresponding opening such that the skin panel has at least the same pressure tightness and at least the same resistance with respect to tensile, pressure and shearing forces which act in an extent direction of the outer skin in the skin panel as the same skin panel without the corresponding opening,
• wherein in each of the skin panels the respective opening and the associated structural element are constructed and sized in such a manner that the securing of the frame of the structural element to the outer skin can be produced and released from the side of the outer face and the structural element can be removed after the securing is released from the side of the outer face by the frame being tilted and moved outward out of the opening, or the structural element can be arranged in a securing position prior to the securing being produced from the side of the outer face by the frame being tilted and introduced into the opening.