Kawasaki Jukogyo Kabushiki Kaisha

Kabushiki Kaisha Kawasaki Zosen

Yasuo Saito

Masanori Hamamatsu

Kenichi Nakashima

Masaaki Higashi

Yukinobu Kohno

Hiroshi Ohnishi

Takashi Kawashima

Hajime Hirakawa

Kazuyuki Akimoto

Kazushi Ogawa

Takayuki Satomi

Hidenori Yoshida

Hiroaki Fujimoto

Makoto Baino

Hiroaki Mori

Yasunori Iwasaki

Kazuyuki Ebira

A short-term planned route from a start position that is a ship position at a first time up to an end position that is the ship position at a second time is designed based on a planned route, an estimated encounter marine phenomenon information, operation performance information measured on a ship, and a hull motion model of the ship, the estimated encounter marine phenomenon information being measured on the ship based on actually encountered marine phenomenon information. The short-term planned route makes a first evaluation function optimal, the first evaluation function containing: an index indicating an influence of a fluctuation portion between a planned position that is a ship position planned at the second time on the planned route and the end position; a fuel consumption index when the ship sails along the short-term planned route; and a safety index when the ship sails along the short-term planned route.

Ship maneuvering control method and ship maneuvering control system

A movable object maneuver method wherein a destination point is set; wherein a thrust value is calculated in real time which minimizes or maximizes a performance index associated with one or more state variables and thrust required for a movable object to reach the destination point and which takes into account non-linear conditions inherent to the movable object; and wherein the movable object is moved based on the calculated thrust value.

Method and system for maneuvering movable object

Force balance and moment balance associated with thrust of air and water craft equipped with thrust generators are preset in view of non-linear characteristics and dynamic characteristics of thrust generators. A performance index for minimizing thrusts generated by the thrust generators is defined. Using the balance as restricting condition, propeller thrusts of the thrust generators and rudder angles and changing speeds of rudders that minimize the performance index are calculated.

Method and device for allocating thrust

An aircraft engine run-up hangar comprises a building defining a test chamber capable of receiving an aircraft therein, an air inlet structure, and an exhaust structure. The air inlet structure is formed in a front end part of a roof structure corresponding to a front end part of the building, the exhaust structure is connected to a rear end part of the building and defines an exhaust passage extending obliquely upward from the back end of the building, and one or a plurality of current deflecting members are disposed near a lower end of the air inlet structure to deflect air currents flowing through the air inlet structure into the building toward an aircraft housed in the building. A current-straightening structure is incorporated into the air inlet structure. A current-straightening space is defined under the air inlet structure. A first current-straightening member, a second current-straightening member, a third current-straightening member and a fourth current-straightening member are disposed in a region in and around the current-straightening space.

Aircraft engine run-up hangar

An aircraft engine run-up hangar comprises a building defining a test chamber capable of receiving an aircraft therein, an air inlet structure, and an exhaust structure. The air inlet structure is formed in a front end part of a roof structure corresponding to a front end part of the building. The exhaust structure is connected to a rear end part of the building and defines an exhaust passage extending obliquely upward from the back end of the building. A ceiling included in the building has an inclined section sloping down backward to straighten air currents, and a groove is formed in a middle part, with respect to width, of the inclined section to permit a vertical tail fin of an aircraft to pass when the aircraft is carried into or out of the test chamber.

Growing community of inventors

Suita, Japan

Yasuo Saito