Abstract: A device for manufacturing a composite component including a tool with a first and second sections forming first and second confinement surfaces, the sections movable relative to each other into and out of a fastening configuration. The device includes a closing mechanism with a closing section. In the fastening configuration, the first confinement surface and the second confinement surface face one another, and the sections and the closing mechanism are arranged such that a cavity is formed between the sections and the closing mechanism. The closing section is transferable from an open configuration into a closed configuration. In the closed configuration, the third confinement surface extends along a plane perpendicular to the first and second confinement surfaces, wherein, when the closing mechanism is heated from a first temperature to a second temperature, the closing section transfers from the open configuration into the closed configuration at a predefined temperature.

Abstract: An aircraft structural component is described, including an aircraft skeleton component which divides a space along a longitudinal axis of the aircraft skeleton component into two spatial portions arranged on opposite sides of the aircraft skeleton component, and including a fluid conduit component which runs on an outer side of the aircraft skeleton component and fluidically connects the two spatial portions. Also described is an aircraft wing with an aircraft structural component, as well as an aircraft with an aircraft structural component or with an aircraft wing.

Abstract: A device for manufacturing a composite component including a tool with a first and second sections forming first and second confinement surfaces, the sections movable relative to each other into and out of a fastening configuration. The device includes a closing mechanism with a closing section. In the fastening configuration, the first confinement surface and the second confinement surface face one another, and the sections and the closing mechanism are arranged such that a cavity is formed between the sections and the closing mechanism. The closing section is transferable from an open configuration into a closed configuration. In the closed configuration, the third confinement surface extends along a plane perpendicular to the first and second confinement surfaces, wherein, when the closing mechanism is heated from a first temperature to a second temperature, the closing section transfers from the open configuration into the closed configuration at a predefined temperature.

Abstract: An aircraft structural component is described, including an aircraft skeleton component which divides a space along a longitudinal axis of the aircraft skeleton component into two spatial portions arranged on opposite sides of the aircraft skeleton component, and including a fluid conduit component which runs on an outer side of the aircraft skeleton component and fluidically connects the two spatial portions. Also described is an aircraft wing with an aircraft structural component, as well as an aircraft with an aircraft structural component or with an aircraft wing.