FLIGHT CONTROL SYSTEM

• US 20100318245A1
• Filed: 08/05/2010
• Published: 12/16/2010
• Est. Priority Date: 03/03/2005
• Status: Abandoned Application

• Current Assignee: Nabtesco Corporation
• Original Assignee: Nabtesco Corporation
• Inventors: Nakagawa, Shingo, Kojima, Satoru
• Application Number:
  US12/850,709
• Publication Number:
  US 20100318245A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 13/504 using electro-hydrostatic actuators [EHA's]
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

A flight control system for an aircraft includes a PCS generating a pilot control signal based on pilot operations of a stick control and others, an FCC for controlling flight control surfaces of the aircraft, a surface control device arranged for each flight control surface to control it based on a surface control signal transmitted from the FCC, and a data bus for connecting the FCC and the surface control device. The surface control device includes an ACE executing servo calculation process and outputting an actuator operation signal, and an actuator section for controlling hydraulic oil supplied to a hydraulic cylinder based on the actuator operation signal. A single flight control surface is controlled by a plurality of ACE and actuator section pairs, and the ACE includes a normal control section, a monitoring section, a backup control section, and the like.

Claims

1. A flight control system for an aircraft, comprising:

a pilot command system (PCS) including a pilot control signal generator outputting control operations of a pilot as a pilot control signal;

a flight control computer (FCC) outputting a surface control signal based on said pilot control signal and a sensor signal output from a sensor equipped on said aircraft;

a surface control device for controlling a flight control surface of said aircraft, one or more of said surface control devices being arranged for a single piece of said flight control surface; and

a data bus for electrically connecting said FCC with said surface control device, wherein

said surface control device includes actuator control electronics (ACE) outputting an actuator operation signal based on said surface control signal, and an actuator section for driving said flight control surface in response to said actuator operation signal,

said ACE includes an interface section for communicating data with said FCC via said data bus, a normal control section generating a normal actuator operation signal for controlling said flight control surface based on said surface control signal transmitted from said FCC via said interface section, a monitoring section for monitoring whether or not operations of said normal control section and said actuator section are normal and outputting a normal control command when it is judged that said operations of said normal control section and said actuator section are normal, a backup control section generating a backup actuator operation signal for controlling said flight control surface in lieu of said normal control section, a switching section for switching between said normal actuator operation signal and said backup actuator operation signal in response to a backup control switching command, an amplifier section for amplifying and outputting one of said normal actuator operation signal and said backup actuator operation signal switched by said switching section as said actuator operation signal, and a control command output section outputting a control command that is a logical addition of said normal control command and a backup control command,

said actuator section includes an electro-hydraulic converter for controlling flow amount of hydraulic oil in response to said actuator operation signal, a cylinder for driving said flight control surface by flow amount of said hydraulic oil controlled by said electro-hydraulic converter, and a solenoid valve for permitting said hydraulic oil to flow into said cylinder when said control command is being output and for blocking said hydraulic oil to flow into said cylinder when said control command is not being output, and

said FCC outputs said backup control command and said backup control switching command when it is judged by said FCC based on monitoring results transmitted from said monitoring section that said operation of said normal control section is abnormal.

2. A flight control system as set forth in claim 1, wherein said PCS further includes a backup control signal generator outputting control operations of said pilot as a backup control signal, and a backup command generator generating said backup control command and said backup control switching command in response to operations of said pilot in lieu of said FCC, and wherein

said backup control command and said backup control switching command are fed into said backup control section through said FCC, said data bus and said interface section, and said backup control signal is fed into said backup control section directly.

3. A flight control system as set forth in claim 1, wherein said PCS further includes a backup control signal generator outputting control operations of said pilot as a backup control signal, and a backup command generator generating said backup control command and said backup control switching command in response to operations of said pilot in lieu of said FCC, and wherein

said backup control command and said backup control switching command are fed into said backup control section directly, and said backup control signal is fed into said backup control section through said FCC, said data bus and said interface section.

4. A flight control system as set forth in claim 1, wherein said PCS further includes a backup control signal generator outputting control operations of said pilot as a backup control signal, and a backup command generator generating said backup control command and said backup control switching command in response to operations of said pilot in lieu of said FCC, and wherein

said backup control command and said backup control switching command are fed into said backup control section directly, and said backup control signal is fed into said backup control section directly.

9. A flight control system as set forth in any one of claims 1 to 8, wherein said normal control section is composed of a first programmable logic device for executing a normal control program, said monitoring section is composed of a second programmable logic device for executing a monitoring program including a predetermined portion of said normal control program, and said backup control section is composed of a third programmable logic device for executing a backup control program having a hardware configuration different from those of said first programmable logic device and said second programmable logic device.

10. A flight control system as set forth in claim 9, wherein said first programmable logic device and said second programmable logic device are field programmable gate arrays (FPGA) having a maximum gate size of 300,000 to 1,000,000 gates, and said third programmable logic device is a complex programmable logic device (CPLD) having a maximum gate size of 100,000 gates.

5. A flight control system for an aircraft, comprising:

a pilot command system (PCS) including a pilot control signal generator outputting control operations of a pilot as a pilot control signal;

a flight control computer (FCC) outputting a surface control signal based on said pilot control signal and a sensor signal output from a sensor equipped on said aircraft;

a surface control device for controlling a flight control surface of said aircraft, one or more of said surface control devices being arranged for a single piece of said flight control surface; and

a data bus for electrically connecting said FCC with said surface control device, wherein

said surface control device includes actuator control electronics (ACE) outputting an actuator operation signal based on said surface control signal, and an actuator section for driving said flight control surface in response to said actuator operation signal,

said ACE includes an interface section for communicating data with said FCC via said data bus, a normal control section generating a normal actuator operation signal for controlling said flight control surface based on said surface control signal transmitted from said FCC via said interface section, a monitoring section for monitoring whether or not operations of said normal control section and said actuator section are normal and outputting a normal control command when it is judged that said operations of said normal control section and said actuator section are normal, a backup control section generating a backup actuator operation signal for controlling said flight control surface in lieu of said normal control section, a switching section for switching between said normal actuator operation signal and said backup actuator operation signal in response to a backup control switching command, a servo calculator for carrying out servo calculation based on said normal actuator operation signal and said backup actuator operation signal switched by said switching section and outputting calculation results as said actuator operation signal, and a control command output section outputting a control command that is a logical addition of said normal control command and a backup control command,

said actuator section includes an electro-hydraulic converter for controlling flow amount of hydraulic oil in response to said actuator operation signal, a cylinder for driving said flight control surface by flow amount of said hydraulic oil controlled by said electro-hydraulic converter, and a solenoid valve for permitting said hydraulic oil to flow into said cylinder when said control command is being output and for blocking said hydraulic oil to flow into said cylinder when said control command is not being output, and

said FCC outputs said backup control command and said backup control switching command when it is judged by said FCC based on monitoring results transmitted from said monitoring section that said operation of said normal control section is abnormal.

6. A flight control system as set forth in claim 5, wherein said PCS further includes a backup control signal generator outputting control operations of said pilot as a backup control signal, and a backup command generator generating said backup control command and said backup control switching command in response to operations of said pilot in lieu of said FCC, and wherein

said backup control command and said backup control switching command are fed into said backup control section through said FCC, said data bus and said interface section, and said backup control signal is fed into said backup control section directly.

7. A flight control system as set forth in claim 5, wherein said PCS further includes a backup control signal generator outputting control operations of said pilot as a backup control signal, and a backup command generator generating said backup control command and said backup control switching command in response to operations of said pilot in lieu of said FCC, and wherein

said backup control command and said backup control switching command are fed into said backup control section directly, and said backup control signal is fed into said backup control section through said FCC, said data bus and said interface section.

8. A flight control system as set forth in claim 5, wherein said PCS further includes a backup control signal generator outputting control operations of said pilot as a backup control signal, and a backup command generator generating said backup control command and said backup control switching command in response to operations of said pilot in lieu of said FCC, and wherein

said backup control command and said backup control switching command are fed into said backup control section directly, and said backup control signal is fed into said backup control section directly.