Abstract: A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels.

Abstract: A method of joining two panels of an airframe or fuselage structure of an aircraft or spacecraft, including: preparing an edge region of a first panel to form a first joining surface; preparing an edge region of a second panel to form a second joining surface; aligning the panels with one another such that the joining surfaces abut or interface one another forming a joint area; and joining the panels at the joining surfaces in the joint area. In an embodiment, the preparing steps include machining, and cutting, the edge regions of the first and second panels in a single operation to form the first and second joining surfaces substantially simultaneously. In another embodiment, the first and second joining surfaces are substantially planar and extend at an oblique angle with respect to a primary plane or surface of the respective first and second panels.

Abstract: The invention relates to a device for detecting a flaw in a fibre-reinforced component, in particular delamination in a bearing region of a hole, by means of at least one probe, wherein an ultrasound field is emittable and detectable by means of the at least one probe. The ultrasound field is coupled according to the invention to the component at an angle of incidence ? of greater than 0° from a normal of an upper side of a component. The oblique radiation enables a higher degree of resolution to be achieved when detecting delamination in the bearing region of holes. Further variants of the device operate using at least one linear probe received in a self-positioning holder. The rotating linear probe is composed of a plurality of individual vibrator elements which are arranged at regular intervals behind one another.

Abstract: The invention relates to a device for detecting a flaw in a fibre-reinforced component, in particular delamination in a bearing region of a hole, by means of at least one probe, wherein an ultrasound field is emittable and detectable by means of the at least one probe. The ultrasound field is coupled according to the invention to the component at an angle of incidence ? of greater than 0° from a normal of an upper side of a component. The oblique radiation enables a higher degree of resolution to be achieved when detecting delamination in the bearing region of holes. Further variants of the device operate using at least one linear probe received in a self-positioning holder. The rotating linear probe is composed of a plurality of individual vibrator elements which are arranged at regular intervals behind one another.