Abstract: A method for changing test substrates in a continuous-flow vacuum system in a multiple-treatment-step process cycle for treating a substrate, a treatment method using the method for changing test substrates, and systems for treating a plurality of substrates (61) and for changing test substrates. For at least two treatment steps, at least two test substrates (66) are transferred to a vacuum treatment system at the beginning of the process cycle and are transferred back out once the process cycle is concluded. Subsequently, the first test substrate (66) concurrently treated in this step is removed from the measurement position (70) it occupied during the treatment and is deposited in an empty position (71) without a test substrate (66). Subsequently, the second test substrate (66) which has not been treated yet is deposited in the resulting free measurement position (70) for the purpose of supplying the second test substrate to the subsequent treatment step.

Abstract: A structural arrangement comprising a fiber reinforced polymer component, a cold gas spraying electrically conductive layer, and a polyether sulfone foil arranged on the fiber reinforced polymer component, at least in a region between the fiber reinforced polymer component and the cold gas sprayed electrically conductive layer.

Abstract: An add-on element for a perforated plate having throughbores arranged in a regular grid includes an attachment part having a throughbore, an extension part, and a connecting element configured to secure the attachment part to an underside of the perforated plate by passing through a respective one of the throughbores of the perforated plate and the throughbore in the attachment part.

Abstract: A shear connection for interchangeably connecting two airframe parts of an aircraft. The shear connection may include first and second interface parts. The second interface part may overlap in the longitudinal direction at an overlap section with at least one of the first interface part and the first airframe part. The shear connection may further comprise means that rigidly and non-interchangeably attach the first interface part to the first airframe part and the second interface part to the second airframe part and a shear bolt that rigidly and interchangeably connects the second interface part with the at least one of the first interface part and the first airframe part at the overlap section, thereby interchangeably connecting the first and second airframe parts.

Abstract: Holding devices for receiving a plurality of substrates in a substrate treatment system are disclosed. Holding devices comprise a flange, at least one segment that is releasably disposed on the flange, and at least one carrier for receiving one or a plurality of substrates. The flange has connection faces for disposing the at least one segment on the flange. The at least one segment has a segment support structure. The at least one carrier is assembled on the segment support structure.

Abstract: A method of manufacturing a structural arrangement on the basis of a fiber reinforced polymer component, comprising at least the steps of: providing a fiber reinforced polymer component; fixing a polyether sulfone foil on the fiber reinforced polymer component, at least in a region where an electrically conductive layer is to be formed; and performing a cold gas spraying process for spraying electrically conductive particles onto the polyether sulfone foil in order to create the electrically conductive layer.

Abstract: A structural arrangement comprising a fiber reinforced polymer component, a cold gas spraying electrically conductive layer, and a polyether sulfone foil arranged on the fiber reinforced polymer component, at least in a region between the fiber reinforced polymer component and the cold gas sprayed electrically conductive layer.

Abstract: A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.

Abstract: A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly that is arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping.

Abstract: A rotary wing aircraft that comprises a structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.

Abstract: Holding devices for receiving a plurality of substrates in a substrate treatment system are disclosed. Holding devices comprise a flange, at least one segment that is releasably disposed on the flange, and at least one carrier for receiving one or a plurality of substrates. The flange has connection faces for disposing the at least one segment on the flange. The at least one segment has a segment support structure. The at least one carrier is assembled on the segment support structure.

Abstract: An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.

Abstract: A shear connection for interchangeably connecting two airframe parts of an aircraft. The shear connection may include first and second interface parts. The second interface part may overlap in the longitudinal direction at an overlap section with at least one of the first interface part and the first airframe part. The shear connection may further comprise means that rigidly and non-interchangeably attach the first interface part to the first airframe part and the second interface part to the second airframe part and a shear bolt that rigidly and interchangeably connects the second interface part with the at least one of the first interface part and the first airframe part at the overlap section, thereby interchangeably connecting the first and second airframe parts.

Abstract: A method of manufacturing a structural arrangement on the basis of a fiber reinforced polymer component, comprising at least the steps of: providing a fiber reinforced polymer component; fixing a polyether sulfone foil on the fiber reinforced polymer component, at least in a region where an electrically conductive layer is to be formed; and performing a cold gas spraying process for spraying electrically conductive particles onto the polyether sulfone foil in order to create the electrically conductive layer.

Abstract: A rotary wing aircraft that comprises a structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.

Abstract: A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly that is arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping.

Abstract: A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.

Abstract: A fuel tank and a differential frame in a fuselage airframe of a helicopter, the fuel tank being installed between the fuselage lower cover shell and the floor panel. The differential frame separates the fuel tank into two individual compartments, the differential frame having a web below the floor panel with a variable-height with a minimum height at the symmetry axis of the fuselage cross-section and a maximum height at lateral frame roots regions. A transversal beam is attached at each of its both ends to the differential frame bridging the entire variable-height of the differential frame and the fuel tank with two front and rear fuel bladders covering both individual tank compartments with a middle bladder installed between the transversal beam and the variable-height web of the differential frame.

Abstract: An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.

Abstract: A fuel tank and a differential frame in a fuselage airframe of a helicopter, the fuel tank being installed between the fuselage lower cover shell and the floor panel. The differential frame separates the fuel tank into two individual compartments, the differential frame having a web below the floor panel with a variable-height with a minimum height at the symmetry axis of the fuselage cross-section and a maximum height at lateral frame roots regions. A transversal beam is attached at each of its both ends to the differential frame bridging the entire variable-height of the differential frame and the fuel tank with two front and rear fuel bladders covering both individual tank compartments with a middle bladder installed between the transversal beam and the variable-height web of the differential frame.