Advanced Technology Institute of Commuter-helicopter, Ltd.

Natsuki Kondo

Eiichi Yamakawa

Hiroki Nishimura

Tomoka Tsujiuchi

The root end is attached to the rotor head for rotationally driving. The central portion has aerodynamic characteristics depending on the leading and trailing edges and which extend linearly from the root end in parallel to each other, and the chord dimension therebetween. A planform shape of the blade tip portion is defined by the first leading edge which extends forwardly as the distance from the outboard end of the leading edge of the central portion outwardly increases, the second leading edge and the side edge which are rearwardly swept as the distance from the outboard end of the first leading edge toward outboard side outwardly increases, the first trailing edge which is curved forwardly as the distance from an outboard end of the trailing edge of the central portion outwardly increases, and the second trailing edge which is swept rearwardly as the distance from the outboard end point of the first trailing edge outwardly increases. This configuration makes it possible to eliminate the delocalization in the supersonic region and greatly reduce high-speed impulsive noises.

Rotor blade for rotary wing aircraft

A low-noise level landing apparatus for helicopters comprises a helicopter position calculator for calculating the position of the helicopter, a data input device, an air data sensor for measuring an airspeed and a descending angle, a rotor tachometer for detecting a rotor rotational speed, a memory and a fuel gauge for calculating the weight of the helicopter, a rotor rotational speed controller for controlling the rotor rotational speed, a BVI noise generating area database device for storing noise levels in accordance with parameters of descending speed, airspeed, descending angle, rotor rotational speed and weight of the helicopter. A computer selects a flight route, an airspeed, a descending angle and a rotor rotational speed wherein noise is reduced, by setting a plurality of flight routes on the basis of the helicopter position and landing point and by referring to the noise generating area database device. Low-noise level landing is then carried out by pilot manual control or automatic flight control. By modifying the selected flight route on the basis of ground noise data received by a data receiver, the optimal flight route is reselected. As a result, a flight route wherein noise reduction can be attained during landing can be selected more properly.

Low-noise level landing apparatus and system for helicopters

A main rotor torque compensation apparatus for a helicopter having a main rotor and a tail rotor includes vertical tails that are supported at a variable angle of attack. An actuator adjusts the angle of attack such that the main rotor torque is compensated by the torque of the tails together with the torque of the tail rotor.

Growing community of inventors

Kakamigahara, Japan

Natsuki Kondo