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 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.