Power generation controller of aircraft

Patent metadata

Field	Value
Publication number	US-2021380270-A1
Application number	US-201917286883-A
Country	US
Kind code	A1
Filing date	Oct 21, 2019
Priority date	Oct 24, 2018
Publication date	Dec 9, 2021
Grant date	—

Abstract

A power generation controller of an aircraft includes a low-temperature start-up control section and a power generation control section. When it is determined that an oil temperature of a hydraulic actuator configured to change an operation position of a speed change element of a hydraulic transmission satisfies a predetermined low-temperature condition when starting up an aircraft engine, the low-temperature start-up control section sets a power generator to a power non-generating state and controls the hydraulic actuator such that the speed change element is positioned at an acceleration side of a median in a speed change range. When it is determined that the oil temperature satisfies a predetermined low-temperature start-up completion condition, the power generation control section sets the power generator to a power generating state and controls the hydraulic actuator in accordance with a rotational frequency of the aircraft engine.

First claim

1 . A power generation controller of an aircraft,
the power generation controller being configured to control a hydraulic transmission configured to change speed of rotational power of an aircraft engine and transmit the rotational power to a power generator, the power generation controller comprising: a low-temperature start-up control section configured to, when it is determined that an oil temperature of a hydraulic actuator configured to change an operation position of a speed change element of the hydraulic transmission satisfies a predetermined low-temperature condition when starting up the aircraft engine, set the power generator to a power non-generating state and control the hydraulic actuator such that the speed change element is positioned at an acceleration side of a median in a speed change range; and a power generation control section configured to, when it is determined that the oil temperature satisfies a predetermined low-temperature start-up completion condition, set the power generator to a power generating state and control the hydraulic actuator in accordance with a rotational frequency of the aircraft engine.

2 . The power generation controller according to claim 1 , wherein:
the hydraulic transmission is a continuously variable transmission including an upper limit stopper configured to defines a maximum acceleration position of the speed change element; and when the oil temperature satisfies the low-temperature condition, the low-temperature start-up control section continuously outputs an acceleration-side drive signal to the hydraulic actuator such that the speed change element is positioned at the maximum acceleration position defined by the upper limit stopper.

3 . The power generation controller according to claim 1 , wherein the low-temperature start-up completion condition includes a temperature continuation condition in which a state where the oil temperature is a reference temperature or more is continued for a predetermined period of time or more.

4 . The power generation controller according to claim 3 , further comprising a temperature condition determining section configured to determine whether or not the oil temperature satisfies the low-temperature start-up completion condition, wherein:
the temperature condition determining section samples information of the oil temperature at a predetermined cycle; and the low-temperature start-up completion condition is a condition in which a number of times a sample value of the oil temperature becomes a reference temperature or more becomes a predetermined number of times or more in a row.

5 . The power generation controller according to claim 4 , wherein when an absolute value of a deviation between a previous value of the sample value and a current value of the sample value is a first threshold or more, the temperature condition determining section substitutes the previous value for the current value.

6 . The power generation controller according to claim 5 , wherein when a number of times the absolute value of the deviation becomes a second threshold or more becomes a predetermined number of times or more in a row, the temperature condition determining section resets the previous value.

7 . The power generation controller according to claim 1 , wherein when it is determined that the rotational frequency of the aircraft engine has exceeded a predetermined rotational frequency, the low-temperature start-up control section outputs a protection signal which weakens the rotational power transmitted to the power generator through the hydraulic transmission.

8 . The power generation controller according to claim 7 , wherein the protection signal is a signal which controls the hydraulic actuator such that the speed change element is positioned at a deceleration side of the median in the speed change range.

Assignees

• Kawasaki Heavy Ind Ltd

Inventors

• Nakashima Kenichi
• Ootsuki Satoshi
• Kobayashi Shuma
• Matsuda Kippei

Classifications

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• B64D31/06

  actuated automatically · CPC title

• F16H61/6648 Primary

  controlling of shifting being influenced by a signal derived from the engine and the main coupling · CPC title

• F04C14/22

  by changing the eccentricity between cooperating members · CPC title

• B64C19/00

  Aircraft control not otherwise provided for · CPC title