Abstract: A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

Abstract: An aircraft structure (11) for flow control including a perforated panel (13) having an inner surface (15) directed to a structure interior (17), an outer surface (19) in contact with an ambient flow (21), and a plurality of micro pores (23) connecting the inner and outer surfaces (15, 19). Elongate crack stopper elements (25) are attached to the inner surface (15) of the perforated panel (13). The crack stopper elements (25) are configured to inhibit crack propagation within the perforated panel (13).

Abstract: A slat arrangement for a wing of an aircraft. The arrangement has a movable leading-edge slat and a connection section. The leading-edge slat includes a slat leading edge and a slat trailing edge. The connection section includes a receiving opening for receiving the slat trailing edge. The connection section includes an overhang having a free end. The slat trailing edge is configured to be translated under the overhang. A trailing region of the slat is configured to be elastically deformed by the overhang when the slat trailing edge is moved into the receiving opening.

Abstract: A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

Abstract: A leading edge structure (13) for a flow control system of an aircraft (1), including a double-walled leading edge panel having an inner wall element (45) and an outer wall element (47). Between the inner and outer wall elements (45, 47) are elongate stiffeners (49) spaced apart from one another. And, between adjacent stiffeners (49) are a hollow chamber (51). The outer wall element (47) includes micro pores (53). The inner wall element (45) includes passages (55) forming a fluid connection between the hollow chambers (51) and a vacuum system (15). An ice protection system in the stiffeners (49) includes hot air ducts (57) configured for connection to a hot air system (17), and the stiffeners (49) include hot air openings (59) forming a fluid connection between the hot air ducts (57) and the hollow chambers (51).

Abstract: A leading edge structure (1) for a flow control system of an aircraft, including a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) includes an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) includes elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formed between the inner and outer wall elements (21, 23), wherein the outer wall element (23) includes micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) includes openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7).

Abstract: An aircraft structure (11) for flow control including a perforated panel (13) having an inner surface (15) directed to a structure interior (17), an outer surface (19) in contact with an ambient flow (21), and a plurality of micro pores (23) connecting the inner and outer surfaces (15, 19). Weight reduction and maintaining required fatigue strength of the structure may be achieved because one or more elongate crack stopper elements (25) are attached to the inner surface (15) of the perforated panel (13), and the crack stopper elements (25) are configured to inhibit crack propagation within the perforated panel (13).

Abstract: An aircraft component includes a main body and at least one lug extending from the main body. The lug is formed of a composite component, a sleeve, and a filler component. The sleeve has a through hole extending along a longitudinal axis. The composite component includes continuous fibers embedded in a matrix. The sleeve is at a distance from the main body. The composite component extends from the main body around at least a section of the outer circumferential surface of the sleeve and back to the main body. The continuous fibers of the composite component extend from the main body around the section of the outer circumferential surface of the sleeve and back to the main body. An intermediate space is between the sleeve and the main body and is delimited by the sleeve and the composite component. The filler component is within the intermediate space.

Abstract: A distributed process control system having at least one automation unit on the plant side that calculates a plurality of first process variables and influences the process that is connected by first data link to a monitoring system that controls and/or monitors the process. The system has an external computing unit that is connected by a distributed communication mechanism to the automation unit and exchanges data with it using a second data link. The external computing unit calculates a plurality of second process variables that the of the automation unit uses to influence the process. A method for extending the function of at least one plant-side automation unit is also disclosed.

Abstract: A leading edge structure (13) for a flow control system of an aircraft (1), including a double-walled leading edge panel having an inner wall element (45) and an outer wall element (47). Between the inner and outer wall elements (45, 47) are elongate stiffeners (49) spaced apart from one another. And, between adjacent stiffeners (49) are a hollow chamber (51). The outer wall element (47) includes micro pores (53). The inner wall element (45) includes passages (55) forming a fluid connection between the hollow chambers (51) and a vacuum system (15). An ice protection system in the stiffeners (49) includes hot air ducts (57) configured for connection to a hot air system (17), and the stiffeners (49) include hot air openings (59) forming a fluid connection between the hot air ducts (57) and the hollow chambers (51).

Abstract: A leading edge structure (1) for a flow control system of an aircraft, including a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) includes an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) includes elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formed between the inner and outer wall elements (21, 23), wherein the outer wall element (23) includes micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) includes openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7).

Abstract: An automation facility and method for expanding the automation facility with at least one field device, wherein expansion of the expansion of the automation facility with a further field device occurs in a simplified manner such that no disruptive influence on process control during the expansion occurs.

Abstract: An automation facility and method for expanding the automation facility with at least one field device, wherein expansion of the expansion of the automation facility with a further field device occurs in a simplified manner such that no disruptive influence on process control during the expansion occurs.

Abstract: A distributed process control system having at least one automation unit on the plant side that calculates a plurality of first process variables and influences the process that is connected by first data link to a monitoring system that controls and/or monitors the process. The system has an external computing unit that is connected by a distributed communication mechanism to the automation unit and exchanges data with it using a second data link. The external computing unit calculates a plurality of second process variables that the of the automation unit uses to influence the process. A method for extending the function of at least one plant-side automation unit is also disclosed.

Abstract: An agitator for a fermenter, a fermenter and method of operating a fermenter are provided. The agitator has an agitator shaft which stands roughly vertically in the fermenter. Because of this, the substrate in the fermenter is circulated in horizontal planes. This allows the formation of several layered decomposition zones. In addition, the agitator is preferably designed so that it may be removed upwards from the fermenter during continuing operation. This means that it is not necessary to empty the fermenter for maintenance work on the agitator.

Abstract: The invention relates to an agitator for a fermenter, a fermenter and method of operating a fermenter. The agitator has an agitator shaft which according to the invention stands roughly vertically in the fermenter. Because of this, the substrate in the fermenter is circulated in horizontal planes. This allows the formation of several layered decomposition zones. In addition, the agitator is preferably so designed that it may be removed upwards from the fermenter during continuing operation. This means that it is not necessary to empty the fermenter for maintenance work on the agitator.