Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Abstract: A filter arrangement for high frequency signals, HF signals, is described. The filter arrangement includes a housing in which there is a cavity that extends in the longitudinal direction of the housing. The waffle-iron arrangement is arranged in the cavity and includes a carrier plate having a plurality of recesses, wherein there is an electrically conductive material arranged in at least some of the recesses, wherein the electrically conductive material in each case forms a pin in the at least some recesses. This structure makes it possible to provide a filter arrangement for very high frequencies, because the structure allows the carrier plate and the pins arranged therein to be provided with very small geometrical dimensions.

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) surrounding a plenum (17) and having a first side portion (21), a second side portion (27), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), wherein the leading edge panel (13) includes micro pores (45), wherein a first port device (49) is arranged in the first side portion (21) fluidly connected to the plenum (17) via a duct (53) defined by a duct structure (105), and wherein the first port device (49) comprises a first door (55) pivotable by a first hinge (57) about a first hinge axis (59).

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) having micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61).

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Abstract: A control surface of an aircraft comprises a fixed skin panel, a first flexurally elastic skin panel and a second flexurally elastic skin panel, which is connected to the first flexurally elastic skin panel and is configured to at least partially overlap the fixed skin panel. Furthermore, the control surface comprises an actuator system, which is configured to move the second flexurally elastic skin panel parallel to the fixed skin panel, wherein the actuator system has a fixed structural element arranged in a root region of the control surface, and a structural element that is movable relative to the fixed structural element.

Abstract: An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.

Abstract: A leading edge structure for an aircraft flow control system includes a leading edge panel curvingly surrounding a plenum. The leading edge panel has a first side portion and a second side portion with an inner surface facing the plenum and an outer surface contacting an ambient flow. The leading edge panel includes a plurality of micro pores forming a fluid connection between the plenum and the ambient flow. An air outlet is arranged in the first or second side portion and is fluidly connected to the plenum for letting out air from the plenum into the ambient flow. The air outlet is formed as a fixed air outlet including an outlet panel extending in a fixed manner from the leading edge panel into the ambient flow, such that a rearward facing outlet opening is formed between the leading edge panel and a rear edge of the outlet panel.

Abstract: A magnetic field sensor element with a piezo electric substrate having predetermined shear wave velocity VS, two pairs of interdigital electrodes, arranged on the substrate on the ends of a delay section, having a period length p of at least 10 micrometers, a non-magnetic, electrically non-conductive guide layer arranged on the substrate along the delay section, and a magnetostrictive functional layer arranged on the guide layer, wherein the shear wave velocity in the guide layer is smaller than VS, wherein a) the substrate is oriented to generate and propagate mechanical shear waves upon applying a temporally periodic, electrical voltage to at least one interdigital electrode pair in the range of frequency VS/p and, wherein b) the thickness of the guide layer equals at least 10% and at most 30% of the period length p of the interdigital electrodes.

Abstract: A magnetic field sensor element with a piezo electric substrate having predetermined shear wave velocity VS, two pairs of interdigital electrodes, arranged on the substrate on the ends of a delay section, having a period length p of at least 10 micrometers, a non-magnetic, electrically non-conductive guide layer arranged on the substrate along the delay section, and a magnetostrictive functional layer arranged on the guide layer, wherein the shear wave velocity in the guide layer is smaller than VS, wherein a) the substrate is oriented to generate and propagate mechanical shear waves upon applying a temporally periodic, electrical voltage to at least one interdigital electrode pair in the range of frequency VS/p and, wherein b) the thickness of the guide layer equals at least 10% and at at most 30% of the period length p of the interdigital electrodes.

Abstract: An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.

Abstract: A control surface of an aircraft comprises a fixed skin panel, a first flexurally elastic skin panel and a second flexurally elastic skin panel, which is connected to the first flexurally elastic skin panel and is configured to at least partially overlap the fixed skin panel. Furthermore, the control surface comprises an actuator system, which is configured to move the second flexurally elastic skin panel parallel to the fixed skin panel, wherein the actuator system has a fixed structural element arranged in a root region of the control surface, and a structural element that is movable relative to the fixed structural element.

Abstract: The present invention relates to a resonator device having a stacked arrangement of laminated layers including a plurality of dielectric layers, and at least one resonator comprising a short-circuit electrode, a first capacitor electrode and a second capacitor electrode. Each electrode comprises at least a portion of a layer of electrically conductive material provided on a surface of one of the dielectric layers. The second capacitor electrode is disposed spaced, in the stacking direction, from the short-circuit electrode and the first capacitor electrode. The short-circuit electrode and the second capacitor electrode are electrically interconnected by a first electrical connection comprising at least one via hole penetrating one or more of the dielectric layers.

Abstract: A multi-layered device includes an inductor electrode layer connected between one end of a first viahole inductor conductor and a side-surface ground electrode, and arranged substantially in parallel to a dielectric sheet, when the first and second viahole inductor conductors are arranged in such a positional relation that a distance between the first and second viahole inductor conductors is smaller than 1.5 times a length of the first viahole inductor conductor.

Abstract: The present invention relates to a resonator device having a stacked arrangement of laminated layers including a plurality of dielectric layers, and at least one resonator comprising a short-circuit electrode, a first capacitor electrode and a second capacitor electrode. Each electrode comprises at least a portion of a layer of electrically conductive material provided on a surface of one of the dielectric layers. The second capacitor electrode is disposed spaced, in the stacking direction, from the short-circuit electrode and the first capacitor electrode. The short-circuit electrode and the second capacitor electrode are electrically interconnected by a first electrical connection comprising at least one via hole penetrating one or more of the dielectric layers.

Abstract: A multi-layered device includes an inductor electrode layer connected between one end of a first viahole inductor conductor and a side-surface ground electrode, and arranged substantially in parallel to a dielectric sheet, when the first and second viahole inductor conductors are arranged in such a positional relation that a distance between the first and second viahole inductor conductors is smaller than 1.5 times a length of the first viahole inductor conductor.

Abstract: The present invention relates to a microwave band-pass filter comprising a plurality of coupled resonators including at least one coaxial resonator (1). For suppression of higher order or spurious pass-bands the filter is characterised in that a central hole (9) extends from the upper end of the inner conductor (6) of said at least one coaxial resonator through at least part of the length of the inner conductor, the central hole (9) forming a wave guide section, the cut-off frequency of which being above the pass-band of the band-pass filter, and in that the wave guide section contains in an upper portion (11) thereof a low loss dielectric material with a dielectric constant sufficiently high so that the cut-off frequency of the wave guide section is below the first higher order response of the band-pass filter, and in that the lower end portion (10) of the central hole (9) contains a lossy material.