Abstract: The invention relates to a disposable absorbent pant comprising a central chassis and elasticized front and rear belt. The central chassis comprises an absorbent core with an absorbent layer. The absorbent layer comprises a continuous channel formed therein.

Abstract: A semi-active system for providing a required fluid flow, the system comprising an outlet configured to protrude into the main flow direction of an external fluid flow external to the semi-active system, an exhaust channel provided, in relation to the main flow direction of the external fluid flow, beneath the outlet, the exhaust channel being configured to inject an exhaust fluid flow into the external fluid flow, a device configured to produce a jet fluid flow and a pipe provided within the exhaust channel, the pipe being configured to fluid-communicatively couple to the device, and entrain, by the produced jet fluid flow, the exhaust fluid flow.

Abstract: A flow body of an aircraft includes: a flow surface exposed to an airstream during flight of the aircraft, the flow surface generating at least one region of turbulent airflow during flight of the aircraft, at least one perforated area including a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings, and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold, the second end including a suction opening and being arranged in the at least one region of turbulent airflow, wherein the suction opening is adapted for inducing a suction force in the at least one suction duct when the flow surface is exposed to an airstream during flight, thereby inducing a flow of air from through the plurality of openings.

Abstract: A flow body of an aircraft includes: a flow surface exposed to an airstream during flight of the aircraft, the flow surface generating at least one region of turbulent airflow during flight of the aircraft, at least one perforated area including a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings, and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold, the second end including a suction opening and being arranged in the at least one region of turbulent airflow, wherein the suction opening is adapted for inducing a suction force in the at least one suction duct when the flow surface is exposed to an airstream during flight, thereby inducing a flow of air from through the plurality of openings.

Abstract: A semi-active system for providing a required fluid flow, the system comprising an outlet configured to protrude into the main flow direction of an external fluid flow external to the semi-active system, an exhaust channel provided, in relation to the main flow direction of the external fluid flow, beneath the outlet, the exhaust channel being configured to inject an exhaust fluid flow into the external fluid flow, a device configured to produce a jet fluid flow and a pipe provided within the exhaust channel, the pipe being configured to fluid-communicatively couple to the device, and entrain, by the produced jet fluid flow, the exhaust fluid flow.

Abstract: An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

Abstract: An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

Abstract: A motion-restraint arrangement (48) with elongate lines of elements (10), wherein each line of elements (10) has a number of individual elements (12) which can be erected by spring elements (20) from a small-volume thin storage condition into a large-volume active condition. Each respective individual element (12) has flexible lateral edge elements (16, 18), which in the active condition define a parallelepiped. The spring elements (20) extend in spatially diagonal relationship between the corners (22) of the respective parallelepiped (14). A motion-restraint arrangement (48) which is easy and inexpensive to produce and which has optimum restraint properties is obtained in that the spatially diagonal spring elements (20) are formed by spring wires (24), which extend in a zigzag shape in the longitudinal direction of the respective line of elements (10).

Abstract: A method for assigning digital image information to the navigational data of a medical navigation system is provided. The method includes: producing digital image information from a digital image recording device for a patient being monitored by means of the navigation system; transmitting a signal from the image recording device to the navigation system when an image is produced, the signal including assignment information for assigning the image information to the navigational data which apply to the image information; and transmitting the image information from the image recording device to the navigation system, wherein the image information and the corresponding navigational data are assigned to each other.

Abstract: A motion-restraint arrangement (48) with elongate lines of elements (10), wherein each line of elements (10) has a number of individual elements (12) which can be erected by spring elements (20) from a small-volume thin storage condition into a large-volume active condition. Each respective individual element (12) has flexible lateral edge elements (16, 18), which in the active condition define a parallelepiped. The spring elements (20) extend in spatially diagonal relationship between the corners (22) of the respective parallelepiped (14). A motion-restraint arrangement (48) which is easy and inexpensive to produce and which has optimum restraint properties is obtained in that the spatially diagonal spring elements (20) are formed by spring wires (24), which extend in a zigzag shape in the longitudinal direction of the respective line of elements (10).

Abstract: In a method for generation of an x-ray image of a subject in a patient, a first x-ray image showing the subject in the patient is acquired. A subject image containing only image information in the imaging region of the subject is created from the first x-ray image by image regions of the first x-ray image that do not belong to the imaging region of the subject being removed. A second x-ray image of the patient is acquired in the region of the subject. The subject image is associated with the second x-ray image with positional accuracy and both are merged into a sum image.

Abstract: The present invention relates to a wing tip extension (7) for a wing, having an upper and a lower surface (10 and 11) and a leading edge and a trailing edge (12 and 13), the geometries of which are such that between a connection region (8), for connection with a wing, and the tip (9) of the wing tip extension (7) there is provided a continuous increase of the local dihedral, a continuous increase both of the sweepback angle of the leading edge (12) and also of the trailing edge (13), and a continuous decrease of the chord of the wing tip extension (7), and in that the wing tip extension (7) in the connection region (8) carries on from the wing in substance continuously. The wing tip extension (7) in accordance with the invention thereby ensures a significant reduction of the overall drag.

Abstract: The invention relates to assigning digital image information to the navigational data of a medical navigation system, wherein:

Abstract: The present invention relates to a wing tip extension (7) for a wing, having an upper and a lower surface (10 and 11) and a leading edge and a trailing edge (12 and 13), the geometries of which are such that between a connection region (8), for connection with a wing, and the tip (9) of the wing tip extension (7) there is provided a continuous increase of the local dihedral, a continuous increase both of the sweepback angle of the leading edge (12) and also of the trailing edge (13), and a continuous decrease of the chord of the wing tip extension (7), and in that the wing tip extension (7) in the connection region (8) carries on from the wing in substance continuously. The wing tip extension (7) in accordance with the invention thereby ensures a significant reduction of the overall drag.

Abstract: A foldable wing or airfoil, which is especially but not exclusively adapted for a projectile, and which incorporates interengaging telescopable fin sections. A nose in the foldable wing, which is hingable in the region of one end through a pivot in a longitudinal groove, has a chamber opening facing away from its leading edge and which is located between the wing part surfaces for receiving the interlocking fin sections, which sections are profiled in U-shaped configuration. The chamber also receives a base or root spar which is hinged in the region of its leading end in the chamber, and wherein the front ends of the fin sections straddle the root spar and are each hinged along the root spar offset relative to each other.