FLIGHT CONTROL SYSTEM AND METHOD OF SEPARATING CONTROL LEVER LINKAGE

• US 20100305780A1
• Filed: 06/25/2008
• Published: 12/02/2010
• Est. Priority Date: 02/20/2008
• Status: Active Grant

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Sataka, Masahiko
• Granted Patent: US 8,352,098 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 13/12 Dual control apparatus
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A flight control system according to the present invention includes a first sensor, a flight control computer, a link mechanism, a separation unit, and a second sensor detecting a force transmitted from the first control lever to the link mechanism. The first sensor detects a force applied from an outside to a first control lever. The flight control computer determines whether or not stacking arises in the first control lever on the basis of the force detected by the first sensor and the force detected by the second sensor, and outputs a separation command to the separation unit when determining that the stacking arises. The separation unit disconnects the link mechanism on the basis of the separation command to separate a connection between the first control lever and the second control lever.

Claims

1. A flight control system comprising:

a first sensor configured to detect a force applied from an outside to a first control lever;

a link mechanism configured to mechanically connect said first control lever to a second control lever different from said first control lever, and transmit a force from said first control lever to said second control lever;

a second sensor configured to detect a force transmitted from said first control lever to said link mechanism;

a flight control computer configured to include a stack determination portion which determines whether or not stacking arises in said first control lever on the basis of said force detected by said first sensor and said force detected by said second sensor; and

a separation unit configured to disconnect said link mechanism on the basis of a separation command to separate a connection between said first control lever and said second control lever,

wherein said stack determination portion outputs said separation command to said separation unit when determining that said stacking arises in said first control lever.

2. The flight control system according to claim 1, wherein said stack determination portion determines that said stacking arises in said first control lever when a difference between said force detected by said first sensor and said force detected by said second sensor is equal to or more than a reference value.

3. The flight control system according to claim 1, wherein said stack determination portion determines that said stacking arises in said first control lever when number of times of cases, in which a difference between said force detected by said first sensor and said force detected by said second sensor is equal to or more than a reference value, is equal to or more than a predetermined value.

4. The flight control system according to claim 1, wherein said first sensor includes:

a first roll sensor configured to detect a force in a roll direction with respect to said first control lever, and

a first pitch sensor configured to detect a force in a pitch direction with respect to said first control lever,

wherein said second sensor includes;

a second roll sensor configured to detect a force in a roll direction with respect to said first control lever transmitted via said link mechanism, and

a second pitch sensor configured to detect a force in a pitch direction with respect to said first control lever transmitted via said link mechanism,

wherein said stack determination portion determines that said stacking arises in said first control lever when a difference between said force detected by said first roll sensor and said force detected by said second roll sensor is equal to or more than a first reference value or when a difference between said force detected by said first pitch sensor and said force detected by said second pitch sensor is equal to or more than a second reference value.

5. The flight control system according to claim 1, further comprising:

an artificial feel device configured to apply a reaction force to at least one of said first control lever and said second control lever,

wherein said stack determination portion determines that said stacking arises in said first control lever when a value obtained by subtracting a value of said reaction force from a value of a difference between said force detected by said first sensor and said force detected by said second sensor is equal to or more than a reference value.

6. The flight control system according to claim 1, wherein said stack determination portion stops a determination processing of stacking in an autopilot mode.

7. The flight control system according to claim 1, further comprising:

an output device configured to output a stack determination result of said stack determination portion in a manner that a pilot can confirm said determination result.

8. The flight control system according to claim 1, further comprising:

a determination switch configured to output a determination signal in response to an operation by a pilot,

wherein said stack determination portion determines said stacking based on said determination signal.

9. The flight control system according to claim 1, further comprising:

a displacement sensor configured to detect a displacement of said first control lever,

wherein said flight control computer controls control surfaces based on said displacement detected by said displacement sensor, and

wherein said stack determination portion prohibits said control of said control surfaces based on said displacement detected by said displacement sensor when determining that said staking occurs in said first control lever.

10. The flight control system according to claim 1, further comprising:

a confirmation switch configured to output a confirmation signal in response to an operation of a pilot,

wherein said flight control computer outputs said separation command based on said confirmation signal.

11. A method of separating a control lever linkage, which is a method of separating a link mechanism which mechanically connects a first control lever to a second control lever different from said first control lever and transmits a force from said first control lever to said second control lever, said method comprising:

a first sensor detecting a force applied from an outside to said first control lever;

a second sensor detecting a force transmitted from said first control lever to said link mechanism;

determining whether or not stacking arises in said first control lever on the basis of said force detected by said first sensor and said force detected by said second sensor;

outputting a separation command when determining that said stacking arises in said first control lever in said step of said stacking determination; and

disconnecting said link mechanism on the basis of said separation command to separate a connection between said first control lever and said second control lever.

12. The method of separating a control lever linkage according to claim 11, wherein said step of said stack determination includes;

calculating a difference between said force detected by said first sensor and said force detected by said second sensor, and

determining that said stacking arises in said first control lever when said difference between said forces is equal to or more than a reference value.

13. The method of separating a control lever linkage according to claim 11, wherein said step of said stack determination includes:

calculating a difference between said force detected by said first sensor and said force detected by said second sensor,

counting number of times of cases, in which said difference between said forces is equal to or more than a reference value, and

determining that said stacking arises in said first control lever when said number of times of cases is equal to or more than a predetermined value.

14. The method of separating a control lever linkage according to claim 11, wherein said step of said first sensor detecting a force applied from an outside to said first control lever, includes:

a first roll sensor detecting a force in a roll direction with respect to said first control lever, and

a first pitch sensor detecting a force in a pitch direction with respect to said first control lever, wherein said step of said second sensor detecting a force transmitted from said first control lever to said link mechanism, includes;

a second roll sensor detecting a force in a roll direction with respect to said first control lever transmitted via said link mechanism, and

a second pitch sensor detecting a force in a pitch direction with respect to said first control lever transmitted via said link mechanism,

wherein said step of said stack determination includes;

determining that said stacking arises in said first control lever when a difference between said force detected by said first roll sensor and said force detected by said second roll sensor is equal to or more than a first reference value or when a difference between said force detected by said first pitch sensor and said force detected by said second pitch sensor is equal to or more than a second reference value.

15. The method of separating a control lever linkage according to claim 11, further comprising:

applying a reaction force to at least one of said first control lever and said second control lever,

wherein said step of said stack determination includes;

calculating a value by subtracting a value of said reaction force from a value of a difference between said force detected by said first sensor and said force detected by said second sensor, and

determining that said stacking arises in said first control lever when said value obtained by subtracting said value of said reaction force from said value of said difference between said forces is equal to or more than a reference value.

16. The method of separating a control lever linkage according to claim 11, further comprising:

said stack determination portion stopping a determination processing of stacking in an autopilot mode.

17. The method of separating a control lever linkage according to claim 11, further comprising:

outputting a stack determination result of said step of said stack determination in a manner that a pilot can confirm said determination result.

18. The method of separating a control lever linkage according to claim 11, further comprising:

outputting a determination signal in response to an operation by a pilot,

wherein said step of said stack determination includes;

determining said stacking based on said determination signal.

19. The method of separating a control lever linkage according to claim 11, further comprising;

detecting a displacement of said first control lever; and

controlling control surfaces based on said displacement,

wherein said step of said stack determination includes;

prohibiting said control of said control surfaces based on said displacement when determining that said staking occurs in said first control lever.

20. The method of separating a control lever linkage according to claim 11, further comprising:

outputting a confirmation signal in response to an operation of a pilot,

wherein said step of said outputting a separation command, includes;

outputting said separation command based on said confirmation signal.