Abstract: A one-man helicopter 1 in which a drive transmission 10 that transmits driving force to upper and lower rotors 5 and 6 comprises first and second planet gear mechanisms 100 and 200 provided with a common carrier 104. When the common carrier 104 is rotated by a motor 301, a differential motion is generated between the two planet gear mechanisms. This results in the rotors being rotated at different velocities, which can be used to control yaw. A fore-and-aft swing mechanism 400 and right-and-left swing mechanism 500 depend from the lower end of a vertical shaft 41 on which the rotors are supported. Moving a stick 8 forward or backward, or to either side, tilts the vertical shaft 41 in the same direction. When the stick 8 is not subjected to a controlling force, the vertical shaft 41 reverts automatically to its original vertical state. This configuration makes it possible to realize a coaxial twin-rotor type helicopter having a compact, structurally simple control mechanism.

Abstract: A universal power drive and lifting rotor system module adaptable for powering various types of single and multiple rotor VTOL aircraft comprising an elongated component support framework on the top of which a lifting rotor assembly and transmission are mounted onto the front end of which an engine is externally supported and the rear end of which is adapted for attachment and external support of a VTOL augmentation framework carrying a lifting rotor torque compensating unit. The rotor assembly and transmission receive power from a power train comprising a main drive shaft coupled to the engine and supported for rotation within the component support framework to extend longitudinally thereof and connected through a pulley and belt rotational power arrangement to the rotor transmission power input shaft extending from within the transmission to above the rear end of the component support framework.

Abstract: A kite employing a controllable transmission between two specialized types of rotor assemblies. The torque rotor assembly, is designed to rotate when placed in a stream of wind, collecting power from the wind in the form of lift and torque. The lift rotor assembly, transfers torque energy from the torque rotor into lift, through the system of power transfer. Torque energy from the torque rotor assembly is used to power the control system for the transmission, the control system for a remote mechanism to steer the kite, and power for other devices and remote functions. This invention is dedicated to harnessing and utilizing wind power, both torque and lift, by providing a metered and therefore controllable amount of lift through the variability of the transmission, in a vector along the kite line. The usefulness of this vector of lift is enhanced because, it can be altered through the steering system while retaining the reeling ease of a single string, and can provide power for remote functions.

Abstract: The invention relates to an anti-crash seat with harness for an aircraft.The seat is mounted with limited sliding on at least one substantially vertical support (8), integral with the structure of said aircraft and associated with at least one energy-absorbing device (12), located between said seat and said structure. Advantageously:it is shaped as a bench (2) defining a plurality of seating spaces which are located side by side and each of which is equipped with a safety harness (6);it includes at least one additional energy-absorbing device (16), situated between said structure of the aircraft and a coupling mechanism (17) with locking provided at least at one of said seating spaces; andsaid mechanism (17) for coupling between said bench and said additional device is controlled by the harness (6) associated with said seating space.