Actuator device for aircraft, and aircraft

1. An actuator device for an aircraft comprising:

a first actuator that is operable to drive a flight control surface of the aircraft;

a second actuator that is operable to drive the flight control surface; and

a control system configured to control operation of the first actuator and the second actuator,

wherein the first actuator drives the flight control surface upon supply of hydraulic oil through a first hydraulic system from a first hydraulic power source,

wherein the second actuator drives the flight control surface upon supply of hydraulic oil through a second hydraulic system from a second hydraulic power source,

wherein the control system is configured to monitor a first hydraulic value of the hydraulic oil in the first hydraulic system and a second hydraulic value of the hydraulic oil in the second hydraulic system,

wherein the control system is configured to compare the monitored first hydraulic value to a predetermined first threshold value and compare the monitored second hydraulic value to a predetermined second threshold value,

wherein in a state in which the first actuator functions in an active state and the second actuator functions in a standby state, the control system is configured to perform a switching operation in response to a first condition set being satisfied,

wherein under the first condition set, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value and the monitored second hydraulic value is equal to or more than the predetermined second threshold value,

wherein under the switching operation, the control system switches the first actuator from the active state to a standby state and the control system switches the second actuator from the standby state to an active state,

wherein under the switching operation, the first actuator is in the active state when the control system switches the second actuator to the active state,

wherein the control system is further configured to monitor a current position of a cylinder of the first actuator and compare the monitored current position to a target position, and

wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a second condition set being satisfied, and

wherein under the second condition set, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value, the monitored second hydraulic value is less than the predetermined second threshold value, and a difference between the monitored current position and the target position of the cylinder of the first actuator is equal to or more than a predetermined third threshold value.

2. The actuator device for the aircraft according to claim 1 , wherein the first threshold value and the second threshold value have a relationship such that the first threshold value is less than the second threshold value.

3. The actuator device for the aircraft according to claim 1 , wherein the flight control surface is an aileron.

4. The actuator device for the aircraft according to claim 1 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a third condition set being satisfied, wherein under the third condition set the control system detects a failure of a device belonging to the first hydraulic system.

5. The actuator device for the aircraft according to claim 1 , further comprising:

a third actuator and a fourth actuator that are each operable to drive another flight control surface of the aircraft,

wherein the third actuator drives the other flight control surface upon supply of hydraulic oil through the first hydraulic system from the first hydraulic power source, and

wherein the fourth actuator drives the other flight control surface upon supply of hydraulic oil through a third hydraulic system from a third hydraulic power source.

6. The actuator device for the aircraft according to claim 1 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a third condition set being satisfied, wherein under the third condition set the control system detects that an operation mode for the first hydraulic system is changed from a normal mode to a direct mode.

7. The actuator device for the aircraft according to claim 6 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a fourth condition set being satisfied, wherein under the fourth condition set the control system detects a failure of a device belonging to the first hydraulic system.

8. An actuator device for an aircraft comprising:

a first actuator that is operable to drive a flight control surface of the aircraft;

a second actuator that is operable to drive the flight control surface; and

a control system configured to control operation of the first actuator and the second actuator,

wherein the first actuator drives the flight control surface upon supply of hydraulic oil through a first hydraulic system from a first hydraulic power source,

wherein the second actuator drives the flight control surface upon supply of hydraulic oil through a second hydraulic system from a second hydraulic power source,

wherein the control system is configured to monitor a first hydraulic value of the hydraulic oil in the first hydraulic system and a second hydraulic value of the hydraulic oil in the second hydraulic system,

wherein the control system is configured to compare the monitored first hydraulic value to a predetermined first threshold value and compare the monitored second hydraulic value to a predetermined second threshold value,

wherein in a state in which the first actuator functions in an active state and the second actuator functions in a standby state, the control system is configured to perform a switching operation in response to a first condition set being satisfied,

wherein under the first condition set, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value and the monitored second hydraulic value is equal to or more than the predetermined second threshold value,

wherein under the switching operation, the control system switches the first actuator from the active state to a standby state and the control system switches the second actuator from the standby state to an active state,

wherein under the switching operation, the first actuator is in the active state when the control system switches the second actuator to the active state, and

wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a second condition set being satisfied, wherein under the second condition set the control system detects that an operation mode for the first hydraulic system is changed from a normal mode to a direct mode.

9. The actuator device for the aircraft according to claim 8 , wherein the first threshold value and the second threshold value have a relationship such that the first threshold value is less than the second threshold value.

10. The actuator device for the aircraft according to claim 8 , wherein the flight control surface is an aileron.

11. The actuator device for the aircraft according to claim 8 , further comprising:

a third actuator and a fourth actuator that are each operable to drive another flight control surface of the aircraft,

wherein the third actuator drives the other flight control surface upon supply of hydraulic oil through the first hydraulic system from the first hydraulic power source, and

wherein the fourth actuator drives the other flight control surface upon supply of hydraulic oil through a third hydraulic system from a third hydraulic power source.

12. The actuator device for the aircraft according to claim 8 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a third condition set being satisfied, wherein under the third condition set the control system detects a failure of a device belonging to the first hydraulic system.

13. The actuator device for the aircraft according to claim 8 , wherein the control system is further configured to monitor a current position of a cylinder of the first actuator and compare the monitored current position to a target position,

wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to maintain the first actuator in the active state and the second actuator in the standby state in response to a third condition set,

wherein under the third condition set, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value, the monitored second hydraulic value is less than the predetermined second threshold value, and a difference between the monitored current position and the target position of the cylinder of the first actuator is less than a predetermined third threshold value.

14. The actuator device for the aircraft according to claim 13 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a fourth condition set being satisfied, wherein under the fourth condition set the control system detects a failure of a device belonging to the first hydraulic system.

15. The actuator device for the aircraft according to claim 14 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a fifth condition set being satisfied,

wherein under the fifth condition set the control system detects a failure of a device belonging to the first hydraulic system, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value, the monitored second hydraulic value is less than the predetermined second threshold value, and the difference between the monitored current position and the target position of the cylinder of the first actuator is equal to or more than the predetermined third threshold value.

16. The actuator device for the aircraft according to claim 13 , wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to perform the switching operation in response to a fourth condition set being satisfied,

wherein under the fourth condition set the control system detects a failure of a device belonging to the first hydraulic system, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value, the monitored second hydraulic value is less than the predetermined second threshold value, and the difference between the monitored current position and the target position of the cylinder of the first actuator is equal to or more than the predetermined third threshold value.

17. An actuator device for an aircraft comprising:

a first actuator that is operable to drive a flight control surface of the aircraft;

a second actuator that is operable to drive the flight control surface; and

a control system configured to control operation of the first actuator and the second actuator,

wherein the first actuator drives the flight control surface upon supply of hydraulic oil through a first hydraulic system from a first hydraulic power source,

wherein the second actuator drives the flight control surface upon supply of hydraulic oil through a second hydraulic system from a second hydraulic power source,

wherein the control system is configured to monitor a first hydraulic value of the hydraulic oil in the first hydraulic system and a second hydraulic value of the hydraulic oil in the second hydraulic system,

wherein the control system is configured to compare the monitored first hydraulic value to a predetermined first threshold value and compare the monitored second hydraulic value to a predetermined second threshold value,

wherein in a state in which the first actuator functions in an active state and the second actuator functions in a standby state, the control system is configured to perform a switching operation in response to a first condition set being satisfied,

wherein under the first condition set, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value and the monitored second hydraulic value is equal to or more than the predetermined second threshold value,

wherein under the switching operation, the control system switches the first actuator from the active state to a standby state and the control system switches the second actuator from the standby state to an active state,

wherein under the switching operation, the first actuator is in the active state when the control system switches the second actuator to the active state,

wherein the control system is configured to monitor a current position of a cylinder of the first actuator,

wherein the control system is configured to compare the monitored current position to a target position,

wherein in the state in which the first actuator functions in the active state and the second actuator functions in the standby state, the control system is further configured to maintain the first actuator in the active state and the second actuator in the standby state in response to a second condition set, and

wherein under the second condition set, the control system determines that the monitored first hydraulic value is equal to or less than the predetermined first threshold value, the monitored second hydraulic value is less than the predetermined second threshold value, and a difference between the monitored current position and the target position of the cylinder of the first actuator is less than the predetermined third threshold value.