Abstract: An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft. The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or for horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and from remainders of welding possible.

Abstract: A marine contra-rotating propeller system comprises a large gear driven by an engine, and a plurality of small gears disposed so as to respectively mesh with the large gear at a plurality of fixed positions along the circumference of the large gear. Planet gears are respectively mounted to the gear shafts of the small gears. A sun gear and an inner-toothed gear are respectively meshed with the planet gears. A rear propeller is mounted to an inner shaft serving as a gear shaft of the sun gear. A front propeller is mounted to a tubular outer shaft serving as a gear shaft of the inner-toothed gear. The present invention can eliminate, with the simple construction, the inconvenience caused by a differential planetary gear operations in the prior art, can derive a propeller efficiency to the maximum extent.

Abstract: A cogwheel drive mechanism for driving at least one aircraft propeller or helicopter rotor through two transmissions, with two axially displaced transmission-connection shafts and at least one output shaft in the form of a propeller shaft or rotor shaft. The object is to ensure that at least one driven section will remain fully functional between one of the transmissions and one propeller or the other during any conceivable type of malfunction. There are two spatially separated individual drive mechanisms, each of which is accommodated in a separated housing that accommodates sections of one or both of the output shafts and each of which has one of the two connecting shafts.

Abstract: An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft.The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and remainders of weldings possible. Ribs and holding portions are provided on the structure for assembly and/or disassembly of the wing portions to the pipe structure.

Abstract: In a jet aircraft having a drive which rotatably drives an airframe mounted accessory drive (12), a system for controlling the connection of the drive to the airframe mounted accessory drive is disclosed which permits the manual connection and disconnection of a rotatable shaft (18) from a driven shaft (22) with high reliability by a manually movable handle (30) which is connected to a fork (88) which is rotatable between first and second positions which translates a movable carrier (20) which carries the driven shaft between first and second positions. The system has minimal backlash which insures high integrity in sensed positions of the system which is necessary for safe operation of the aircraft.

Abstract: Aircraft with rotary wings, characterized in that it comprises a nacelle (1) surrounding the user who seats on a seat (9) slidingly arranged in the medial plane of said nacelle, substantially in the normal displacement direction of flight of the aircraft, two parallel crowns (40-41) carried by the nacelle and imparted with identical rotational motions but in inverted directions about a common axis, extending substantially at the center of the nacelle, perpendicularly to the plane of said crowns, each of the crowns supporting at least one pair of blades (48-49, 50-51) or wings diametrically opposite and arranged in the prolongation of each other, drive means (19-37) for driving the crowns about the nacelle and means (66-67) for changing in each pair of blades the pitch thereof in an equal but opposite way for each of them.

Abstract: A helicopter has two engines adapted to drive a main sustaining rotor and a plurality of auxiliary propulsion means through a transmission system that is selectively operable to vary the relative speeds of rotation of the sustaining rotor and the auxiliary propulsion means depending upon operating conditions.

Abstract: Double propeller for propelling aircraft, with two coaxially and axially offset propellers that can be driven separately by associated drive mechanisms through a central shaft and a hollow shaft. To reduce noise and maintain safe operation even when one propeller drive breaks down, the propellers rotate in the same direction and can at at least one prescribed angle of rotation to each other be coupled together in such a way that they cannot rotate in relation to each other by means of a clutch that can be disengaged.

Abstract: An improved autogyro including a main airframe having a main engine and pusher propeller as customarily applied in autogyros, and a lifting rotor having an auxiliary drive for the lifting rotor for tapping a minor portion of power from the main propulsive engine and transmitting it to the rotor, including a three-stage compound mechanical-hydraulic transmission for transferring power from the main engine to the lift rotor, wherein the hydraulic portion of the transmission serves functions of providing continuously variable transmission speed ratio, torque converter type of inverse speed-torque relationship, a one-way check valve allowing the rotor to free-wheel, an overpressure relief valve to prevent overtorquing of the lift rotor, a bypass valve acting as a clutch to engage and disengage the power, and a manual shut-off valve acting as a rotor brake and rotor parking lock.

Abstract: A fast forward flight helicopter is provided with a multiple speed helicopter rotor transmission. The transmission allows a variation in main rotor RPM or tail rotor RPM or both, dependent upon the desired flight conditions, while maintaining satisfactory lift and performance. With this means, noise is controlled without loss of aerodynamic performance. In one embodiment a helicopter is provided with a transmission for interconnecting the power input shaft through the main rotor shaft and tail rotor shaft in common. The transmission employed is a planetary gear transmission. A brake means is provided for clutching the planetary gear transmission from a first and second transmission speed so that power is continuously delivered, and shifting is accomplished in a smooth manner, thereby allowing the helicopter to remain in smooth flight. In another embodiment the main rotor is driven through the planetary gear transmission and the tail rotor is directly driven.

Abstract: An assembly for mounting a propeller, which is driven by an aircraft engine, on a longitudinal member of a lightweight aircraft. The assembly includes a sleeve positioned about the longitudinal member, and a pair of opposed adjustable cups securing the sleeve at its ends longitudinally relative to the longitudinal member. A rotating mechanism mounted to the propeller, rotatable about the sleeve, and driven by the aircraft engine rotates the propeller concentrically about a longitudinal axis of the longitudinal member. Suitable bearings are disposed between the rotating mechanism and the sleeve and the rotating mechanism rotates on these bearings. Vibration dampening rings are placed between the cups and the sleeve and dampen the vibration transmitted between the rotating mechanism and the longitudinal member.

Abstract: A motor-generator powered airplane is provided and consists of an internal combustion engine that drives an electric generator. Two transformers are electrically connected to the generator and are each electrically connected to an electric motor. Each electric motor drives a propeller so that the airplane can fly. An emergency battery is connected between the generator and the transformers so that in case of a failure of the engine the battery will supply electricity to continue operation of the electric motors.

Abstract: A hydraulic fluid driving arrangement for land, water or air vehicles includes rotary hydraulic motors driving respective propellers. The motors are arranged in pairs, with the two motors of each pair being on respective opposite sides of the longitudinal axis of the vehicle. One or more hydraulic pump is driven by a prime mover and deliver hydraulic fluid under pressure to two or more separate outlets, with the flows in all outlets being either proportionate or equal to each other, and the outlets being completely separate from each other. One outlet supplies fluid to the motors on one side of the vehicle's medial plane of symmetry and the other supplies fluid to the motors on the other side of the vehicle's medial plane. Respective flow adjustment means may operably associated with each outlet, and may be operated either independently or conjointly. Alternatively, control of the motor speeds may be provided by bypasses.

Abstract: Turbine powered, self-propelled vehicles utilizing multiple electric motors in sets to comprise part of a novel modular electric powertrain drive system. This novel powertrain system is particularly applicable to larger weight class tracked military vehicles, such as an M-1 tank. However, other large or smaller weight class turbine powered vehicles, are candidates including both track and wheel driven types, as well as certain airborne type vehicles such as helicopters and ground-effect vehicles. The modular powertrain drive system hereof basically comprises a plurality of electric high speed drive motors and also of electrical power generator devices, such as alternators, arranged to be commonly driven by the turbine's effective output shaft.

Abstract: A power unit for a hang-glider (1) or the like comprises a combustion motor (2) connected to one end of a drive shaft (9) and a propeller (10) connected to the other end of the drive shaft. To enable the power unit to be used both with pulling or traction-force propellers and pushing propellers (10) there is provided between the drive shaft (9) and the shaft (22) of the propeller (10) a flexible coupling (14) which enables the angle between the drive shaft and the propeller shaft to be adjusted at least in a vertical direction.

Abstract: An air conditioner refrigerant compressor driving and mounting apparatus for a helicopter of the type having a free rotating power output shaft, which rotates within a power take-off pad includes a compressor drive assembly drive shaft housing supported by the power take-off pad. A compressor drive assembly drive shaft is connected with the engine power output shaft, extends linearly through the compressor drive assembly housing, and is supported therein by bearing means. A compressor drive assembly drive shaft pulley is attached to the compressor drive assembly drive shaft and rotated thereby. Bracket means are provided for mounting an air conditioner refrigerant compressor on an outer surface of the compressor drive assembly housing such that a compressor drive shaft for driving the compressor is generally parallel with the compressor drive assembly drive shaft. A compressor pulley is attached to the compressor drive shaft and generally aligned with the compressor drive assembly drive shaft pulley.

Abstract: A vehicle like an aircraft or ship uses multiple propeller pairs to drive the vehicle. One propeller of each pair is located on one side of the vehicle and the other propeller of the same propeller pair on the other side of the vehicle. The propellers of each pair may revolve in opposite directions. A hydraulic transmission transfers the power from the power plant to the propellers, which are driven by hydraulic fluid motors of the transmission. The transmission forces each propeller of the same pair of propellers to revolve with equal rotary velocity relatively to the other propeller of the same pair. Propellers of different pairs have different pitches or sizes. Thereby the propellers use different powers at different speeds of the vehicle. Since the power plant drives a common transmission, the power supply to one of the pairs varies compared to the power supply to the other pair, when the vehicle travels at another speed.

Abstract: A power management system is disclosed for an advanced helicopter having h lift and thrust propulsion units and at least one power plant which comprises, a signal generator for generating a first signal which is proportional to the power available from the power plant, a circuit connected to the lift propulsion unit which has an output that varies according to the amount of power used by that propulsion unit and which receives the first signal for generating a second signal which is proportional to the amount of power remaining. The circuit is either used to power a limit actuator for limiting the amount of power the pilot can apply to the thrust propulsion unit or drive an indicator which indicates to the pilot the amount of power remaining for the thrust propulsion unit, or perform both functions.

Abstract: A helicopter transmission system includes a gearbox comprising a gearcase (11) having a hollow stub axle (12) by which operational loads are transmitted from a main sustaining rotor to a fuselage structure. One or more input speed reducing gear trains (20, 21, 22, 23) are individually supported in hollow lobe portion(s) (14) supported from the axle (12), the or each lobe portion having an individual lubricating oil sump (18) and circulating means (31) adapted to circulate lubricating oil to the respective gear trains. Preferably, interconnecting means (33) are provided to connect the respective individual sumps, and valve means (32, 35) are adapted to maintain a flow of lubricating oil in the event of a loss of oil from one of the sumps.

Abstract: A helicopter transmission system is disclosed in which drive from three engines is transmitted to two output channels each of which is divided by dividing means to drive two output pinions meshed with a common combining gear rotationally fixed to a sustaining rotor drive shaft. Balancing means are provided to balance the torque transmitted by the respective pairs of output pinions and, in the described embodiment, the balancing means comprise a plurality of meshing spur gears arranged with one of the spur gears drivingly connected to one of the engines and a further two of the spur gears are drivingly connected respectively to the two output channels. Conveniently, a further one of the spur gears provides a power take off to an anti torque rotor drive shaft.

Abstract: A V/STOL aircraft comprising a fuselage, having three sets of wings that are offset lengthwise and vertically. The center set of relatively small relatively thick wings 34 between the canard 14 and the rear relatively thin relatively large aerodynamic lift wings 18 are equipped with identical lift fans 36 enclosed in the wing by upper and lower movable slotted deflectors 40. The attitude of the slatted deflectors may be varied to transition the present invention from hovering to forward flight, and vice versa. The present invention's lift fans are interconnected by a balanced power distribution system, to insure constant, efficient use of total power and provide symmetrical lift about the aircraft's center of gravity resistibility. In the event of an engine failure, the remaining lift is still properly distributed to maintain symmetrical lift, so as to maintain balance and operational control of the aircraft in the lift mode.

Abstract: An aircraft drive system having two propellers, each of which is driven independently by a drive belt which is connected to a separate engine. The engines are mounted in cantilever fashion in a spaced relationship on a hollow sleeve. The sleeve is attached by a pair of spaced brackets to the frame of the aircraft. A shaft is rotatably telescopically mounted within the sleeve by bearings located on the ends of the sleeve. A pulley is fixedly mounted on one end of the shaft and is driven by one of the engines for rotating one of the propellers which is fixed on the other end of the shaft. Another pulley is rotatably mounted by bearings on the sleeve and is driven by a drive belt connected to the second engine. The second propeller is telescopically located about the sleeve adjacent the first propeller and is firmly connected to the second pulley which rotates said second propeller completely independent of the first propeller and in an opposite direction than the first propeller.

Abstract: A helicopter-like craft has plural propellers with substantial vertical axes which can be inclined forwardly to provide the forward movement of the vehicle. The propellers are driven by hydraulic fluid motors. One embodiment features the application of a four flow hydraulic pump which supplies two pairs of hydraulic pressure fluid flows, wherein the rate of flow in fluid in each flow of the pairs are equal. One of the pairs of flows may be of permanently fixed rate of flow but the flows of the other pair of flows is variable, but variable in such a system, that even at variation of rate of flow the rate of flow of the two flows of the variable flow--pair remains equal relatively to the other flow of the pair. This system of hydraulic drive is utilized to let the two front propellers of an airborne craft run with equal velocity even when the speed thereof is varified by the mentioned variablity in order to incline the vehicle into its forward movement.

Abstract: A connecting apparatus (16) for attaching a propeller or fan (14) to an engine (12) is disclosed. A connecting apparatus (16) includes a centrifugal clutch device (48) and drive and driven gears (40, 78) for reducing the speed of propeller (14) relative to engine (12). These elements are contained within a lubricant-filled housing comprised of housing (38) and spider bracket (34). Spider bracket (34) includes two pairs of vibration-dampening first and second mountings (140). First mountings (140) more stiffly resist engine vibration than second mountings (142), thereby dynamically balancing the powerplant with respect to the structural frame (20).

Abstract: A fluid motor has working chambers which take in and expell a fluid. The fluid under pressure acts in working chambers to produce a torque and thereby to drive the motor, constituting with the associated parts the drive of the motor.At least one separated fluid line supplies fluid into a space which includes or operates an additional member provided on the fluid motor. The mentioned fluid line and space are able to operate independently of the drive system of the motor.It is thereby possible to operate over the fluid line, for example by remote control, the additional member on the motor independently of the fluid flow of the drive of the motor. The additional member is thereby able to do an additional work or function independently of the drive of the motor.In other embodiments of the invention, the additional member may work in unison or dependence on the fluid drive of the motor, when so desired.

Abstract: The invention provides a helicopter of the type having two coaxial counterrotating rotors with a differential drive mechanism interposed between the power plant and the rotors. The power output of the power plant is coupled to the power input of the differential drive which has two power outputs, one of which is directly connected to the mounting hub of one of the rotors and the other one is connected to the mounting hub of the other rotor through a rotation inverting mechanism. Two embodiments are described and illustrated which differ only by the construction of the differential and the rotation inverting mechanisms.

Abstract: A vehicle for traveling in the air and on the ground is equipped with two, four, or eight propellers on vertical shafts, each driven by a rotary hydraulic motor of the radial-piston type. The motor comprises two rotors which are connected in individual hydraulic circuits supplied with fluid from different hydraulic pumps. One embodiment of the vehicle comprises an automobile with the propellers mounted in oblique air ducts or in shrouds pivotable in the travel direction. Each rotor of the hydraulic motors is coupled to the shaft unidirectionally so that in case of failure, the shaft can be driven by the other rotor. Each hydraulic pump preferably produces four equal fluid flows and comprises two rotors on a common shaft, each rotor with two separate groups of cylinders, the eccentricity of at least one of the rotors being adjustable. Both the hydraulic motor and the pump have inlet and outlet connections on the radial periphery of the housing.

Abstract: A vertical takeoff and landing airplane has a plurality of rotors which are positioned selectively about the center of balance of the airplane so that it can hover upon failure of any one of the rotors. Each rotor is driven by an associated steam propulsion unit and the rotors and propulsion units are constructed so that they may be tilted about their lateral axes from vertical lift positions to horizontal propulsion positions while the airplane is in flight. The working fluid upon which the propulsion units operate is supplied from two or more combustion centers which are separated from the propulsion units, and which produce a high pressure steam-combustion product mixture, automatically at a constant pressure, which is routed to a common pressure system for powering the individual propulsion units. Should one of the fuel combustion centers fail, the steam pressure requirements are provided for automatically by the remaining fuel combustion centers.

Abstract: An aircraft provided with airfoils of the non-rotating type that are configured and arranged to provide greater lift while at the same time offering stable flight at ultra-low airspeeds. The airfoils are arranged as a biplane and consist of a fixed wing and a movable wing which are designed so as to permit a much steeper takeoff and landing angle as well as offering more efficient flight at higher speeds with greater inherent safety.

Abstract: An air, water, or land vehicle has a body adapted to travel in a normal direction of travel and having a pair of forwardly directed propellers symmetrically spaced to each side of the centerline of the vehicle and each carried on a respective fluid motor. An engine on the vehicle drives at least one pump having two independent working chambers each of whose output is connected to the input of a respective one of the propeller-carrying motors and an adjustment is provided for increasing the discharge rate of the one pump relative to the other and vice versa for steering the vehicle.

Abstract: An annular rotor element is rotatably mounted in a housing and has a center opening in which a shaft element is journalled with annular clearance. An arrangement is provided for coupling the elements in motion-transmitting relationship in automatic response to relative rotation in one direction, and for uncoupling the elements in automatic response to relative rotation of the elements in an opposite direction.

Abstract: This invention relates to power transmission systems for helicopters having two or more engines, the transmission system comprising for each engine, drive shafting and gearing including a final drive gear for transmitting torque from each engine to a common output gear for connection to the rotor system, and an idler gear interconnecting the respective gearings to distribute available torque amongst the full complement of final drive gears. A particular embodiment is shown and described for a twin-engined helicopter in which an additional final drive gear is meshed with the output gear and driven from the idler gear so that, even in the event of an engine failure the available torque from the remaining engine is transmitted through all three final drive gears to the rotor system. In the particular embodiment the drive to the additional final drive gear is also arranged for connection to a tail rotor.