Abstract: A testing stand for a helicopter transmission is arranged in a testing stand (20) capable of swiveling deflection around a rotor shaft (4) with one output side rotor shaft (4) and at least one drive side input shaft (6, 8). Actuators (28, 30) are provided around the rotor shaft axis (4) for swiveling deflection of the helicopter transmission (2) to equalize shifts on connection couplings (14, 16, 22) occurring under load. It is suggested that the helicopter transmission (2) be clampable in the testing stand (20) by connection elements (24, 26) elastic with respectable to swiveling deflection.

Abstract: The invention relates to a device (3) for simultaneously interlocking a plurality of actuators (1) by means of a first locking element (5) which is assigned to each final control element (2) of an actuator (1) and which interacts with a second locking element (6). The second locking element is fixed inside the housing (4) in an actuating direction of the final control element (2) and is displaced into an interlocking position by spring force and into an unlocking position by an assisting force. The invention provides that a plurality of second locking elements (6) are interconnected and are actuated by a common device (11). As a result, the variety of parts, the safety risk, the weight, and the constructional complexity are reduced which is very important especially when the inventive device is used in helicopter.

Abstract: The invention relates to a transmission with torque division for a helicopter rotor drive. In a manner known per se, in the transmission a first power transmission branch has a first rotatable driving pinion (6) which is in constant engagement with a first toothed wheel (2) on the output side. At least one other power transmission branch has one other driving pinion (9) co-axial to the first driving pinion (6) and in constant engagement with one other toothed wheel (4) on the output side co-axial to the first toothed wheel (2) on the output side. One torsionally elastic member is arranged in the torque flow of each power transmission branch. The torsion-resistance of the torsionally elastic members determines the load proportions of the power transmission branches. The inventive transmission makes possible a high power density with small installation space, light weight and a small number of functional elements.

Abstract: A helicopter with rotor blades rotatably connected to a rotor head. The rotor head is non-rotatably connected with a rotor mast (1) pivoted in a transmission housing and driven by a transmission via at least one driving mechanism. A pitch of the rotor blades, relative to a plane of rotation of the rotor blades, is controlled via a swash plate, control rods (12) and via individual actuators (9) allocated to each individual rotor blade. The control rods (12) and the actuators (9) are mounted in the rotor mast (1) and the rotor head and those components act, via a mixing lever (11) and a control rod (8), upon a pivoted arm (7) which adjusts the pitch of the rotor blade. The control devices of the rotor blades do not interfere with the air flow, are affected only to a limited extent by centrifugal forces and additional stresses, and are also protected against influences of the weather.

Abstract: The invention is based on a helicopter having the following features: one rotor head (1) is non-rotatably connected with a rotor mast (3) which is rotatably mounted in a housing (5) of a transmission (6); one or more driving mechanisms actuate the rotor mast (3) via the transmission (6) with a summarizing gear (11) fastened on said rotor mast (3), one swash plate (17) is supported by its stationary part (18) via a first fork in a non-rotatable but axially displaceable manner and tiltably in all directions relative to this axis of said rotor mast (3); a rotatable part (19) of said swash plate (17) is rotatably supported against said stationary part (18) of said swash plate (17) via axial and radial bearings (23) and non-rotatably hinged on said rotor head (1) by means of a second fork.

Abstract: The inventive stress test rig for helicopter transmission comprises a first test rig transmission (16) which is driven by a motor (38) and forms a closed stress circuit via shafts (4, 14, 54), connecting couplings (12) a stress mechanism (40, 42), a second test rig transmission (52) and a test transmission (2) having a rotor shaft (4) on the output side. To house the test transmission (2), it has a clamping plate (23) which by means of at least one actuator (22) can be rotated about the rotor shaft axis of the test transmission to compensate load-induced displacements at the connecting couplings (12) of the test transmission.

Abstract: In a helicopter with the rotor blades controlled by a swash plate with a stationary part (11) and a rotary part (9) and hydraulic adjusters (4) in a stationary part of the helicopter or in a rotating system, it is proposed to fit a pump, especially a multi-cylinder reciprocating piston pump, between the stationary part (11) and the rotary part (9) of the swash plate. Besides reducing space needs, weight and costs, this provides a short, reliable oil distribution system to the consumers.

Abstract: In a helicopter having three or more rotor blades, and with mechanical actuation of the rotor blades by a swash plate and a superimposed electrohydraulic active control system, in addition to three regulating units (18) is an actuator (4) between a rotatable part (9) of the swash plate and a rotorblade mount (2) of each rotor blade. This arrangement allows for the safe actuation of individual blades in helicopter noise reduction, and increased efficiency at a modest constructional effort.

Abstract: The stress test rig consists of a rigidly mounted part which contains the devices uniformly used for all types of test gears and an assembly truck (37) which holds the test gear (16) and the required adapter devices. A test rig gear unit (2) forms a continuous stress circuit with a superimposed gear unit (9), an adaptation gear (23) and a second test rig gear (19) wherein the stress torque is set by a control unit (15) through the superimposed gear unit (9). The regulation variable for the stress torque is determined up to more than 80% by a control network (31). The test rig gear unit (2) is a bevel gear wheel and the superimposed gear unit (9) has a bevel gear step (13) so that the output shaft (14) of the superimposed gear unit (9) is pivoted and has a height adapted to an input shaft of an adaptation gear unit (23) or of a test gear unit (16).

Abstract: A device for transmitting linear motion for adjustment of a wing element (4) is provided with one input part (23) and one output part (26) wherein between the input part (23) and the output part (26) an uncoupling mechanism is provided which, above a preset force (release force) makes relative motion between the input part and the output part possible. One or more prestressed springs (42), which can absorb energy during relative motion, upon unloading, restores the input and output parts to an initial position. A translation mechanism converts the relative motion between the input part (23) and the output part (26). The converted motion acts upon the spring (42) whereby a force-path characteristic line of the device, corresponding to the translation mechanism, can be obtained. The translation mechanism consists of a crankshaft (52) with cam discs (50A, 50B) driven by a connecting rod (46) which act upon a piston (48) longitudinally movable within the housing (30) and prestressed by springs (42).