Ihi Aerospace Co., Ltd.

Sinfonia Technology Co., Ltd.

Ihi Corporation

Nabtesco Corporation

Sumitomo Precision Products Co., Ltd.

Hitoshi Oyori

Noriko Morioka

Keisuke Onishi

Shingo Nakagawa

Yoshito Ohta

Yoichi Yamamoto

Hiroshi Saito

Naoki Seki

Nobuyuki Nakanishi

Hirotaka Sugawara

Masayuki Takada

Masaaki Monte

Yukio Shimomura

Yasunori Nihei

Masaya Wakita

Daiki Kakiuchi

Hiroyuki Asakura

An energy recovery device for an aircraft includes: a turbine that is provided between a cabin of the aircraft and an opening for discharging cabin discharge air from the cabin to the outside of the aircraft and is operated by only the cabin discharge air; and a power generator that is driven by the turbine.

Energy recovery device for aircraft

A heat exhaust system for an on-aircraft electric generator, includes: a fuel pump which is driven by electric power generated by an electric generator installed in an aircraft, and which measures and supplies fuel to an engine of the aircraft; a first heat exchanger which releases heat generated by the electric generator into the fuel supplied to the engine; a fuel flow rate determiner which determines a flow rate of the fuel supplied to the engine by the fuel pump; an electric generator output determiner which determines an output from the electric generator; and a heat release controller which controls heat release at the first heat exchanger by using at least one of the flow rate of the fuel determined by the fuel flow rate determiner and the output determined by the electric generator output determiner as a control parameter.

Heat exhaust system for on-aircraft electric generator

Two systems of a first pump unit and a third pump unit that supply fuel of a fuselage fuel tank, and a second pump unit and a fourth pump unit that supply fuel of fuel tanks in both right and left wings are provided corresponding to a left-wing engine and a right-wing engine, respectively. A supply source of the fuel to be supplied to the left-wing engine or the right-wing engine is switched by switching of the pump unit to be turned on.

Fuel supply apparatus for aircraft engine

A fuel supply device according to the present invention comprises a first fuel pump for forcing fuel from a fuel tank to a fuel passage, a first electric motor for driving the first fuel pump, a second fuel pump for forcing fuel from the fuel tank to the fuel passage, a second electric motor for driving the second fuel pump, a supply flow rate sensor for detecting flow rate in the supply passage, and a control device for controlling the flow rate in the supply passage to follow a desired value thereof, by regulating rotational speeds of the first and second electric motors depending on a difference between the desired value and a detected value of flow rate in the supply passage.

Fluid supply device

Heat exchangers are adjacent to electric driving units. Electric blowers of electric blower units rotate at rotational speed corresponding to amounts of heat generation of the electric driving units and suck air (ventilation air and outboard air). The sucked-in air passes through the heat exchangers that are adjacent to the electric driving units.

System for cooling electric driving unit of aircraft

Provided is a wheel drive system for aircraft RS including a motorthat is connected to a wheel, and provided with two voltage supply lines Land Lfor supplying the voltages Vta and Vpr with varying the length of a windingto be energized; a voltage supply unit for supplying the voltage Vta and Vpr to the two voltage supply lines Land L; and a control unitfor controlling the voltage supply unit, wherein the control unitis configured to select one of the two voltage supply lines Land L, and supply the voltage Vta or Vpr, by controlling the voltage supply unit.

Wheel drive system for aircraft

An aircraft electric actuator drive apparatus has an electric actuator and a secondary power supply device. The electric actuator is driven using electric power from a main power unit provided in an aircraft. The secondary power supply device can temporarily supply electric power to the electric actuator while electric power from the main power unit is applied to the electric actuator.

Aircraft electric actuator drive apparatus

An aircraft electric power system provided in an aircraft includes a predetermined DC power supply bus for supplying electric power to a load. The DC power supply bus is configured to always be connected to two or more types of power supply devices having different forms.

Aircraft electric power system

Multipliersandoutput values, which are obtained by multiplying a total drive command value Eby first and second gains Gand G, respectively, as first and second drive command values Eand E. Controllersandcontrol first and second actuators (motors)and, respectively, on the basis of the first and second drive command values. The detection values of the drive amounts of the actuators are denoted by Eand E, respectively, and the detection value of the drive amount of a driven body is denoted by E. A gain calculatorcalculates the gains Gand Gon the basis of E, Eand E. An upper limit value of E, which denotes the drive amount of the driven body, is denoted by L. When E, Eor Eapproaches zero, the first gain Gis brought close to (E&#x2212;L/2)/(E&#x2212;L).

Control device for drive device

A 0-axis current calculatorconfigured to calculate a target value of the 0-axis current by setting the current of the open phase to be zero when one of the phases becomes open, or determines that the target value of the 0-axis current is zero when there is no open phase is provided. Based on the target values of the d-axis current and the q-axis current, the target value of the 0-axis current calculated by the 0-axis current calculatorand the d-axis current, the q-axis current, and the 0-axis current transformed by the d-q-0 transformerthe current supplied to each phase of the motor are controlled.

Motor controller

An electricity generation system according to the present invention comprises a first electric generator designed to generate electricity by rotation of a high-pressure shaft of a compressor constituting a jet engine, a second electric generator designed to generate electricity by rotation of a low-pressure shaft of the compressor, a power distributor for distributing power generated by the first and second electric generators among a multiple loads, a first power regulation device for regulating power output of the first electric generator, a second power regulation device for regulating power output of the second electric generator, and a power control device which manipulates the first and second power regulation devices to ensure a specified amount or greater of jet engine surge margin.

Electricity generation system

An electricity generation device includes a permanent-magnet electric generator with three or more phase windings each having an output terminal and connected to a neutral point, and bidirectional semiconductor switching circuits capable of interrupting connections between the respective phase windings and the neutral point. Each switching circuit allows current to flow in both directions. A gate signal generation circuit outputs to one of the switching circuits during a period including the time at which the AC voltage excited in the corresponding phase winding turns from positive to negative and during a period including the time at which the AC voltage excited in the corresponding phase winding turns from negative to positive. A startup gate signal output circuit outputs a startup gate signal to all of the bidirectional semiconductor switching circuits when the permanent-magnet electric generator is to be started.

Electricity generation device and permanent-magnet electric generator

When it is determined that the number of times that motor rotation-indicative quantity has been detected has exceeded a measurement interval, a feedback speed value is calculated from a motor rotation-indicative quantity detected immediately before, a motor rotation-indicative quantity detected immediately before the last time a measurement interval determination means determined that the number of times had exceeded the measurement interval, and time that has elapsed since the last time the measurement interval determination means determined that the number of times had exceeded the measurement interval, and the measurement interval having a length calculated from a greater one between the calculated feedback speed value and a speed command value is set for the measurement interval determination means to refer to.

Motor control apparatus and method

To realize structure simplification and reduction in manufacturing cost without lowering power transmission efficiency and reliability. The present invention includes a first motor and a second motor , and a lead of a ball screw is disposed coaxially with a motor rotary shaft on a first motor side and a nut of the ball screw is disposed coaxially with a motor rotary shaft on a second motor side so that the first motor and the second motor are connected to each other via the ball screw

Growing community of inventors

Tokyo, Japan

Hitoshi Oyori