Abstract: In a rotor mast for a rotorcraft, the rotor mast can be coupled in a rotationally fixed manner to a drive unit of a helicopter rotor transmission, which allows a particularly smooth running operation. This is achieved in that the rotor mast is configured in two parts, and comprises a bearing mast and an outer mast, with the outer mast, configured as a hollow body, is mounted, concentrically surrounding the bearing mast, such that it can rotate about a central axis relative to the bearing mast. The outer mast can be operatively connected with the helicopter rotor transmission, and the bearing mast can be mounted in the rotorcraft in a locationally and rotationally fixed manner, such that the outer mast can be coupled with a main rotor in a rotationally fixed manner, and can be set in rotation with the helicopter rotor transmission.

Abstract: A helicopter rotor transmission in which the average lubricant monitoring and replenishment intervals are to be significantly increased. The helicopter rotor transmission has a central cavity, in which runs a bearing mast that is fixed in a locationally and rotationally manner, which is held passing through the gear housing at least partially in the direction of the central axis. An internally toothed gear ring of a rotatable rotor mast can be rotated about the central axis, with fixed rotation of the planetary gears about their planetary gear axes, such that the rotor mast can be set in rotation by means of a gear ring driver attached to the gear ring.

Abstract: A tail rotor device, which can be attached to a tail boom of a rotary wing aircraft, in particular of a helicopter, encompassing a sheathing, which forms an air flow channel with a channel depth running in the direction of a channel axis perpendicular to the vertical axis and longitudinal axis and an inner channel diameter, so that a tail rotor with rotor blades can be rotatably mounted in the air flow channel, wherein the sheathing is designed in such a way that its channel depth in a negative longitudinal direction tapers toward the back, wherein the objective is to improve the forward flight characteristics during operation and reduce the power consumption of the main rotor. This is achieved by virtue of the selected variable channel depth is always less than one fourth of the inner channel diameter, and the ratio between the variable channel depth of the sheathing in the direction of the longitudinal axis and the inner channel diameter of the sheathing lies between 20.5% and 14%.

Abstract: A helicopter load hook has a release mechanism that can be mounted in a fixed position in a housing for controllable identification and release of a swivel movement of a hook. The release mechanism includes a magnetic switch and a drum that can rotate. The release mechanism also includes at least one latching piece, which can be swivelled about a latching piece axis of rotation and at least one force receiver, which can be swivelled about a swivel axis, together with a pin. The pin can be connected with a locking lug on the drum together with a hook follower on the hook, such that an indirect connection between the hook and the drum, or more particularly, the magnetic switch, can be achieved, and any direct contact between the hook and the magnetic switch is eliminated. In the closed position of the hook the pin makes any swivelling movement of the hook impossible.

Abstract: A rotor blade coupling device for coupling to a rotor mast having a rotor head centerpiece. The coupling device has at least three rotor blade mountings mounted on the rotor head centerpiece and accommodating at least three rotor blades lying in a rotor plane, and at least one connecting element between adjacent rotor blade mountings. The rotor blade mountings can carry out pivoting motions about a pivoting axis extending vertical to the rotor plane. The at least one connecting element is a damping device, and the rotor blade coupling device has a plate-shaped transfer element, which respectively crosses a rotor blade mounting and is coupled to at least one damping device. The rotor blade coupling device has a simplified design and ensures improved damping of lead-lag motions.

Abstract: A load hook substructure for attachment onto or into the cabin structure of a helicopter, having a housing in which a shaft with a hook attachment is mounted, such that a load hook can be connected with the shaft and thereby with the load hook substructure; this improves the flying characteristics of the helicopter in the case of flights with a load carried underneath. This is achieved in that the shaft passes through the interior of the housing in the longitudinal direction between a housing end wall and a housing wall, such that it can move linearly, and a return spring device is arranged between a damping plate arranged on the shaft and the housing end wall, and a damping device is arranged between the damping plate and the lower housing wall. The damping device has at least one flexibly compressible damping element, which develops a damping action in the event of a linear movement of the shaft.

Abstract: A tail rotor device, which can be attached to a tail boom of a rotary wing aircraft, in particular of a helicopter, encompassing a sheathing, which forms an air flow channel with a channel depth running in the direction of a channel axis perpendicular to the vertical axis and longitudinal axis and an inner channel diameter, so that a tail rotor with rotor blades can be rotatably mounted in the air flow channel, wherein the sheathing is designed in such a way that its channel depth in a negative longitudinal direction tapers toward the back, wherein the objective is to improve the forward flight characteristics during operation and reduce the power consumption of the main rotor. This is achieved by virtue of the selected variable channel depth is always less than one fourth of the inner channel diameter, and the ratio between the variable channel depth of the sheathing in the direction of the longitudinal axis and the inner channel diameter of the sheathing lies between 20.5% and 14%.

Abstract: In a helicopter cabin that can be fastened to a fuselage structure of a helicopter, encompassing a cabin floor surface, which extends from a front area to a rear area of the helicopter cabin, with front seats and pilot cabin doors arranged in the front area, and the pilot cabin doors along with a front surface and additional walls include part of an outer hull of the helicopter cabin that envelops the cabin floor surface, the comfort is to be enhanced on the ground and during flight. This is accomplished by virtue of the fact that the cabin floor surface of the helicopter cabin exhibits a cutout with a cutout depth directed toward the longitudinal axis in the area of the front seats tapered in the direction of the longitudinal axis.

Abstract: A method for purifying Apo A-l is provided including the steps of providing a solution comprising Apo A-l and guanidine hydrochloride and filtering the solution through a filter having a pore size in a range from 15 nrn to 35 nm to thereby reduce viral contamination of the Apo A-l. An Apo A-f preparation is provided having at least a 12 LRV (log reduction value) for a parvovirus; and/or at least 9 log LRV for a non-enveloped virus; and/or at least 8.5 log LRV for a lipid enveloped virus. Also provided are pharmaceutical compositions and reconstituted high density lipoprotein formulation comprising Apo A-l and methods of treating diseases disorders or conditions.

Abstract: In a rotor blade coupling device for coupling with a rotor mast so as to create a rotor head of a rotary-wing aircraft, in particular a gyroplane or a helicopter, encompassing a rotor head central piece, at least two rotor blade holders fastened to the rotor head central piece for accommodating at least two rotor blades lying in a rotor plane, as well as at least one joining means between adjacent rotor blade holders, a simplified structural design is to be achieved for the rotor blade coupling device, and the rotor blade coupling device is to enable an agile control. This is achieved by virtue that the rotor blade coupling device as the joining means encompasses at least one closed ring. The ring is arranged so as to cross all rotor blade holders at least at one respective joining location, and at least indirectly join together all rotor blade holders.

Abstract: A rotor blade coupling device (9) comprising a torsionally rigid carrier (4) is disclosed, the carrier (4) being mounted in a manner which is free of centrifugal force between a thrust bearing (3) and a control bearing (5), resilient impact and pivoting movements of the rotor blade coupling device (9) being able to take place in a damped manner. The rotor blade coupling device (9) is clamped between a rotor head star (101) and a rotor head central piece (102) and held rotatably about the rotor axis A. The centrifugal forces which occur, are transmitted from a rotor blade holder (2) to the rotor head star (101) and thus kept away from the carrier (4).

Abstract: A rotor blade coupling device (9) comprising a torsionally rigid carrier (4) is disclosed, the carrier (4) being mounted in a manner which is free of centrifugal force between a thrust bearing (3) and a control bearing (5), resilient impact and pivoting movements of the rotor blade coupling device (9) being able to take place in a damped manner. The rotor blade coupling device (9) is clamped between a rotor head star (101) and a rotor head central piece (102) and held rotatably about the rotor axis A. The centrifugal forces which occur, are transmitted from a rotor blade holder (2) to the rotor head star (101) and thus kept away from the carrier (4).

Abstract: An observation port (4) in a primary structure (13) of a helicopter cabin (0) is disclosed, which is arranged between a pilot's seat (2) and a co-pilot's seat (3). The observation port (4) is delimited from the interior by an inner screen (15), and from the atmosphere by an outer screen (16), wherein the pilot can observe the space underneath the helicopter cabin (0) through the observation port (4). As a result of the configuration of the observation port (4) the pilot can assume an ergonomic and relaxed seating position at any time, even when he is executing flights with suspended loads. By means of the observation port (4) and the windows (15, 16), which extend laterally between the two pilots' seats (2, 3), a novel unrestricted vertical visual frame of reference onto the suspended load is achieved, wherein the length of the load cable has practically no influence.

Abstract: A rotor blade coupling device (9) comprising a torsionally rigid carrier (4) is disclosed, the carrier (4) being mounted in a manner which is free of centrifugal force between a thrust bearing (3) and a control bearing (5), resilient impact and pivoting movements of the rotor blade coupling device (9) being able to take place in a damped manner. The rotor blade coupling device (9) is clamped between a rotor head star (101) and a rotor head central piece (102) and held rotatably about the rotor axis A. The centrifugal forces which occur, are transmitted from a rotor blade holder (2) to the rotor head star (101) and thus kept away from the carrier (4).

Abstract: An observation port (4) in a primary structure (13) of a helicopter cabin (0) is disclosed, which is arranged between a pilot's seat (2) and a co-pilot's seat (3). The observation port (4) is delimited from the interior by an inner screen (15), and from the atmosphere by an outer screen (16), wherein the pilot can observe the space underneath the helicopter cabin (0) through the observation port (4). As a result of the configuration of the observation port (4) the pilot can assume an ergonomic and relaxed seating position at any time, even when he is executing flights with suspended loads. By means of the observation port (4) and the windows (15, 16), which extend laterally between the two pilots' seats (2, 3), a novel unrestricted vertical visual frame of reference onto the suspended load is achieved, wherein the length of the load cable has practically no influence.

Abstract: A connection box (1) suited for wiring one or more solar cells (33) includes a housing base (2) and a housing top (3) that includes retaining means (21) for receiving a circuit board.

Abstract: The measurement transducer includes at least two oscillatably held transducer tubes vibrating, at least at times, during operation, of which at least one transducer tube serving to convey at least a volume portion of a medium to be measured, communicates with a pipeline; as well as at least one transducer element for converting electrical energy into mechanical and/or vice versa. The two transducer tubes are mechanically coupled together by means of at least one, inlet-side, coupling element and by means of at least one, outlet-side, coupling element in such a manner that both the inlet-side coupling element, as well as also the outlet-side coupling element, are subjected during operation repeatedly to deformations which correspond to vibrations of at least one of the two transducer tubes for converting electrical energy into mechanical, oscillatory energy and/or vice versa.

Abstract: The measurement transducer includes at least two oscillatably held transducer tubes vibrating, at least at times, during operation, of which at least one transducer tube serving to convey at least a volume portion of a medium to be measured, communicates with a pipeline; as well as at least one transducer element for converting electrical energy into mechanical and/or vice versa. The two transducer tubes are mechanically coupled together by means of at least one, inlet-side, coupling element and by means of at least one, outlet-side, coupling element in such a manner that both the inlet-side coupling element, as well as also the outlet-side coupling element, are subjected during operation repeatedly to deformations which correspond to vibrations of at least one of the two transducer tubes for converting electrical energy into mechanical, oscillatory energy and/or vice versa.

Abstract: An anti-D immunoglobulin G-preparation is produced in high-yield from human plasma containing anti-D IgG, or a plasma fraction containing an anti-D IgG, in which (A) the plasma, or the plasma fraction, with a pH in the range of pH 3.5 to 6.5 and a conductivity value in the range of 2 to 4 mS/cm, is subjected to ion exchange chromatography with an adsorbent which has carboxymethyl groups as functional groups, the anti-D IgG being bound to the adsorbent, (B) the adsorbent with the bound anti-D IgG is first rinsed with a wash solution at a pH in the range of 5 to 8 and a conductivity value in the range of 2 to 4 mS/cm, and the anti-D IgG is subsequently eluted, and further (C) the eluted anti-D IgG at a pH in the range of 6 to 8 and a conductivity value in the range of 2 to 4 mS/cm is treated with an alkaline adsorbent with ion-exchange characteristics in order to bind undesired components, and finally, the anti-D IgG is concentrated.