Aircraft electric actuator drive apparatus

Patent metadata

Field	Value
Publication number	US-9868515-B2
Application number	US-201414470194-A
Country	US
Kind code	B2
Filing date	Aug 27, 2014
Priority date	Aug 30, 2013
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

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.

First claim

What is claimed is:

1. An aircraft electric actuator drive apparatus, comprising:
a plurality of electric actuators driven using electric power from a main power unit provided in an aircraft;
a flywheel battery that temporarily and simultaneously supplies electric power to the electric actuators while electric power from the main power unit is applied to the electric actuators; and
a flywheel battery control device that controls the flywheel battery, wherein
the flywheel battery control device operates the flywheel battery based on a total value of necessary electric power required for operations of the respective electric actuators.

2. The aircraft electric actuator drive apparatus according to claim 1 ,
wherein the flywheel battery control device detects a load of the electric actuators, and operates the flywheel battery in accordance with a result of the detection.

3. The aircraft electric actuator drive apparatus according to claim 1 ,
further comprising a motor driver that distributes electric power to the electric actuators and outputs a signal for specifying an operational state of the electric actuators to the flywheel battery control device,
wherein the flywheel battery control device and the motor driver are separately disposed.

4. The aircraft electric actuator drive apparatus according to claim 3 ,
wherein the electric actuators include a movable portion and an electric motor that operates the movable portion, and
the movable portion, the electric motor, and the motor driver are disposed adjacent to one another.

5. The aircraft electric actuator drive apparatus according to claim 1 ,
further comprising an electric actuator control device that controls the electric actuators, and
the electric actuator control device and the flywheel battery control device are formed integrally.

6. The aircraft electric actuator drive apparatus according to claim 1 ,
further comprising an electric actuator control device that controls the electric actuators, and
the electric actuator control device can control operations of the electric actuators and output a signal for specifying an operational state of the electric actuators to the flywheel battery control device.

7. The aircraft electric actuator drive apparatus according to claim 1 ,
wherein the flywheel battery has an inverter-controlled power supply device.

8. The aircraft electric actuator drive apparatus according to claim 1 ,
wherein the electric actuators include an electric actuator for a flight control system for controlling a flight of the aircraft.

Assignees

• Nabtesco Corp
• Ihi Aerospace Co Ltd
• Ihi Aerospace Co Ltd

Inventors

• Nakagawa Shingo
• Yamamoto Yoichi
• Oyori Hitoshi

Classifications

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64C13/50 Primary

  using electrical energy · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title

• Y02T50/40

  Weight reduction · CPC title