Abstract: A method of detecting the closure and/or opening of a navigable element forming part of a network of navigable elements within a geographic area. A passability parameter is associated with each segment of an electronic map representing the navigable network and indicates a likelihood of closure of the element represented by the segment. The value of the passability parameter decays over time. When a device is detected on the element represented by the segment, the passability parameter is increased, and when a closure report is received relating to the segment, the parameter is decreased. In one set of embodiments, when the passability parameter decreases below a first threshold value, the element represented by the segment is determined to be potentially closed. In another set of embodiments, when the passability parameter increases above a second threshold value, the closed element represented by the segment is determined to be opened.

Abstract: A wing arrangement for an aircraft including a latching arrangement (29, 29?, 29?) having a latching member (31, 31?, 31?) and an engagement device (33), wherein the latching member (31, 31?, 31?) is fixed to a wing tip section (13), and the engagement device (33) has a base member (35) on a wing base section (7) and has an abutment surface (43), and an engagement member (45, 45?, 63) supported on the base section (7) and moves between a release position and a latching position by an actuator (49, 49?) coupled to the engagement member (45, 45?, 63) and the base section (7), wherein when the tip section (13) is in the deployed position, the latching member (31, 31?, 31?) abuts the abutment surface (43) and the engagement member (45, 45?, 63) can move between the release position and the latching position, wherein when the latching member (31, 31?, 31?) abuts the abutment surface (43) and the engagement member (45, 45?, 63) is in the latching position, the engagement member (45, 45?, 63) abuts on a surface sect

Abstract: A system, vehicle and method are provided that automatically activate and deactivate a driver assistance system. The automatic activation and deactivation depend on predefined criteria such as brake or gas pedal release, current vehicle velocity, and the presence of a lead vehicle.

Abstract: A wing arrangement for an aircraft is described including a wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled with each other by a coupling arrangement so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19?).

Abstract: A rotational joint (101) that rotatably couples a wing tip device (4) to a fixed wing (3), and includes an outer race (8) and an inner race (9), a rotational drive member (70) and the race that is rotationally fixed relative to the wing tip device (4) each being provided with a coupling section (110, 111, 114), the coupling sections coupled to each other by a coupling member (119), that is received in a bore (112, 113) in one of the coupling sections, such that rotation of the drive member (70) rotates the race that is rotationally fixed relative to the wing tip device, to rotate the wing tip device (4) from one configuration to the other, wherein the coupling member (119) is mounted in the bore such that it is movable radially within the bore.

Abstract: A method of determining whether one or more navigable elements of a navigable network within a geographic area are still affected by a precipitation weather event. A quantity parameter is associated with each segment of an electronic map representing the navigable network and indicates the amount of precipitation remaining on the navigable element or portion thereof represented by the segment. The value of the quantity parameter increases in the presence of any precipitation weather event, and decreases according to a predefined function with respect to time in the absence of any such precipitation weather event. A speed of travel of one or more devices along the navigable element or portion thereof represented by a segment is determined and compared to an expected speed of travel for the segment; the value of the quantity parameter being decreased based on the comparison.

Abstract: A wing for an aircraft is disclosed having a fixed wing, and a foldable wing tip portion mounted to the fixed wing via a tip hinge rotatable about a tip hinge axis between an extended position and a folded position. An arresting device is provided that allows to arrest the foldable wing tip portion with respect to the fixed wing in a very precise position and at the same time can be engaged in a simple and quick manner, is achieved in that the wing includes an arresting system including a first hook mounted to the foldable wing tip portion and a second hook mounted to the fixed wing, wherein the first hook and the second hook are configured to be moved relative to one another between an arrested position, where the first and second hooks are engaged and relative movement of the first and second aircraft components is inhibited, and a release position, where the first and second hooks are disengaged and relative movement of the first and second aircraft components is allowed.

Abstract: A latching device for a wing (3) including a base (11) and a tip section (13). There is a first bore (27) extending from the base section (11) and a second bore (27) extending from the tip section (13) wherein the bores are aligned when the tip section is deployed for flight and out of alignment when the tip section (13) is folded. The latching device (29) includes a housing (33) with an interior cavity (35), a spindle (39) in the interior cavity, a nut (47) threaded on the spindle, wherein rotation of the spindle causes; a latching bolt (31) coupled to the nut (47) and being moved as the nut moves along the rotating spindle between retracted and extended positions; a guide (49) to guide the nut (47) along the spindle and of the latching bolt between the retracted position and the extended position, and a latch actuator (41).

Abstract: A wing for an aircraft is disclosed having a fixed wing and a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position. The wing may include an actuation unit with reduced complexity, and may include a ground latch device for latching the foldable wing tip portion in the folded position.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatable about a first hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the first hinge axis. A wing having an actuation unit with reduced complexity and weight and that is arranged entirely inside the outer contour of the wing is disclosed in which the actuation unit is arranged at one of the fixed wing and the foldable wing tip portion and is coupled to the other of the fixed wing and the foldable wing tip portion via a linkage. The linkage includes a first link element and a second link element, wherein the first link element is rotatably mounted to the one of the fixed wing and the foldable wing tip portion via a second hinge and is rotatably coupled to the second link element via a third hinge.

Abstract: A speaker includes a multi-magnet structure including at least an inner magnet and an outer magnet. A voice coil is suspended from a membrane into a gap between the inner magnet and the outer magnet, and a spider is attached to the membrane and suspended at least partially by the inner magnet. The spider is configured to stabilize the membrane throughout a range of movement responsive to a force generated by the voice coil and the multi-magnet structure.

Abstract: A speaker includes a multi-magnet structure including at least an inner magnet and an outer magnet. A voice coil is suspended from a membrane into a gap between the inner magnet and the outer magnet, and a spider is attached to the membrane and suspended at least partially by the inner magnet. The spider is configured to stabilize the membrane throughout a range of movement responsive to a force generated by the voice coil and the multi-magnet structure.

Abstract: A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a first hinge (11) rotatable about a first hinge axis (13) between an extended position (15) and a folded position (17), and an actuation unit (19) arranged at the fixed wing (5) and coupled to the foldable wing tip portion (9) via a linkage (21) including a first link element (23) and a second link element (25), wherein the first link element (23) is mounted to a rotatable output (27) of the actuation unit (19) and is rotatably coupled to the second link element (25) via a second hinge (29), and wherein the second link element (25) is rotatably coupled to the foldable wing tip portion (9) via a third hinge (31).

Abstract: The disclosed technology provides a computing device with a slot antenna assembly including a slot formed in a metal exterior surface of a computing device case; an acoustic transceiver positioned to transmit an acoustic wave out through the slot and to receive a reflected portion of the acoustic wave in through the slot when the acoustic wave is reflected by an object; a proximity detector coupled to the acoustic transceiver that determines a physical separation between the object and the slot antenna based on a temporal separation between transmission of the acoustic wave and receipt of the reflected portion of the acoustic wave; and a transmission power controller that adjusts transmission power of the slot antenna based on the determined physical separation.

Abstract: A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation unit for actuating the foldable wing tip portion for movement about the hinge axis. The wing includes a brake unit for securing the foldable wing tip portion in the folded position, and the brake unit is formed separately from the actuation unit.

Abstract: An actuation unit (15) for actuating a foldable wing tip portion (9) of a wing (3) for an aircraft (1). The actuation unit (15) includes a track (25) configured to be mounted to a fixed wing (5), a carriage (27) configured to engage the track (25) for guided movement along the track (25), and configured to be coupled to a drive unit (31) for driving the carriage (27) along the track (25), and a link (29) configured to be coupled to the carriage (27) and configured to be coupled to a foldable wing tip portion (9).

Abstract: The present invention relates to a device (2) for determining an optimal placement of a pedicle screw (4), comprising a processing unit (14), wherein the processing unit is configured to receive a model data set representing a model surface (22) of a human vertebra model (18) and a pedicle screw model (30) being optimally placed in a span of a pedicle section (28) of the model surface, wherein the processing unit is configured to receive 5 image data representing a surface image (26) of at least one human vertebra (6), GO and wherein the processing unit is configured to adapt the model data set for each of a number of the at least one human vertebra, such that an adapted model data set representing a correspondingly adapted model surface (36), which fits to the surface image of the respective human vertebra, is provided for each of the number of the at least one human vertebra, wherein each of the 10 adapted model data sets also represents a correspondingly adapted pedicle screw model (38).

Abstract: The present invention provides an improved ultrasound imaging system arranged to evaluate a set of acquired 3D image data in order to provide a compounded 3D image of a fetus irrespective of its position and movement.

Abstract: A method of detecting the closure and/or opening of a navigable element forming part of a network of navigable elements within a geographic area. A passability parameter is associated with each segment of an electronic map representing the navigable network and indicates a likelihood of closure of the element represented by the segment. The value of the passability parameter decays over time. When a device is detected on the element represented by the segment, the passability parameter is increased, and when a closure report is received relating to the segment, the parameter is decreased. In one set of embodiments, when the passability parameter decreases below a first threshold value, the element represented by the segment is determined to be potentially closed. In another set of embodiments, when the passability parameter increases above a second threshold value, the closed element represented by the segment is determined to be opened.

Abstract: A method of detecting the closure and/or opening of a navigable element forming part of a network of navigable elements within a geographic area. A passability parameter is associated with each segment of an electronic map representing the navigable network and indicates a likelihood of closure of the element represented by the segment. The value of the passability parameter decays over time. When a device is detected on the element represented by the segment, the passability parameter is increased, and when a closure report is received relating to the segment, the parameter is decreased. In one set of embodiments, when the passability parameter decreases below a first threshold value, the element represented by the segment is determined to be potentially closed. In another set of embodiments, when the passability parameter increases above a second threshold value, the closed element represented by the segment is determined to be opened.