Advanced Technology Institute of Commuter-Helicopter, Ltd.

Kawasaki Jukogyo Kabushiki Kaisha

Japan Defence Agency, Japanese Government

Hiroki Nishimura

Eiichi Yamakawa

Makoto Aoki

Shunichi Bandoh

Natsuki Kondo

Yoshiyuki Niwa

Sumio Sako

Mikio Terashima

Ryutaro Yabe

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

Upper and lower surfaces of an aerofoil are defined by the following coordinates given in the table below, and the configuration of a leading edge of the aerofoil is defined by the following leading edge radius and the center of circle. Thus drag divergence Mach number Mdd and maximum lift coefficient Clmax can be increased and the noise level can be reduced.

Helicopter blade aerofoil

A three-dimensional digital map prepared by an satellite or the like is stored in a first memory as a wide-area information. Narrow-area information obtained by a laser radar is stored in a second memory. Obstacle information on obstacles, such as high-voltage power lines, high buildings and cranes, is stored in a third memory. These three information are read out to generate virtual images on a see-through type display mounted on a helmet of a pilot so that the virtual images is superimposed on the actual field of vision.

Flight system and system for forming virtual images for aircraft

The coordinates defining the upper surface, lower surface, leading edge configuration and center of circle for a helicopter blade airfoil are given to increase maximum lift coefficient and lift-to-drag ratio, and to reduce noise level.

helicopter blade aerofoil

Growing community of inventors

Kakamigahara, Japan

Hiroki Nishimura