Flight control system

• US 6,650,973 B2
• Filed: 12/16/2002
• Issued: 11/18/2003
• Est. Priority Date: 12/26/2001
• Status: Expired due to Term

• Current Assignee: Teijin Seiki Co., Ltd. (Nabtesco Corporation)
• Original Assignee: Teijin Seiki Co., Ltd. (Nabtesco Corporation)
• Inventors: Yamamoto, Tsuyoshi
• Primary Examiner(s): Marc-Coleman, Marthe Y.
• Application Number:
  US10/319,558
• Publication Number:
  US 20030120399A1
• Time in Patent Office: 337 Days
• Field of Search: 701/4, 701/3, 701/11, 701/8, 701/14, 244/175, 244/195, 244/196, 244/221, 318/564
• US Class Current: 701/4
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

A flight control system for controlling a flight of an aircraft, having an actuator for actuating flight control surfaces and outputting a feedback signal in return; a flight control computer for operating the actuator; and an actuator control computer for controlling the operation of the actuator. The flight control computer comprises an FCC processor for generating an instruction signal to operate the actuator on the basis of an operational instruction signal inputted from a pilot and a state signal indicative of the state of an aircraft, and generating a reference signal on the basis of the instruction signal and the feedback signal from the actuator. The actuator control computer comprises an ACC processor for generating an actuator control signal on the basis of the instruction signal generated by the FCC processor and the feedback signal from the actuator, and a servo amplifier for amplifying the actuator control signal generated by the ACC processor to be outputted to the actuator. The actuator is operative to actuate the flight control surfaces in accordance with the actuator control signal amplified by the servo amplifier and output a feedback signal in return. The flight control computer further comprises a comparing section for comparing the actuator control signal generated by the ACC processor with the reference signal generated by the FCC processor to detect a failure wherein the FCC processor is different in design from the ACC processor.

Claims

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

an actuator for actuating flight control surfaces and outputting a feedback signal in return;

a flight control computer for operating said actuator; and

an actuator control computer for controlling the operation of said actuator;

said flight control computer comprising;

an FCC processor for generating an instruction signal to operate said actuator on the basis of an operational instruction signal inputted from a pilot and a state signal indicative of the state of an aircraft, and generating a reference signal on the basis of said instruction signal and said feedback signal from said actuator,

said actuator control computer comprising;

an ACC processor for generating an actuator control signal on the basis of said instruction signal generated by said FCC processor and said feedback signal from said actuator, and

a servo amplifier for amplifying said actuator control signal generated by said ACC processor to be outputted to said actuator,

said actuator is operative to actuate said flight control surfaces in accordance with said actuator control signal amplified by said servo amplifier and output a feedback signal in return,

whereby

said flight control computer further comprises;

a comparing section for comparing said actuator control signal generated by said ACC processor with said reference signal generated by said FCC processor to detect a failure,

said FCC processor is different in design from said ACC processor.

2. The flight control system as set forth in claim 1, in which

said FCC processor is operative to generate said reference signal in accordance with FCC software,

said ACC processor is operative to generate said actuator control signal in accordance with ACC software, and

said FCC software is different from said ACC software in design.

3. The flight control system as set forth in claim 1, in which

said FCC processor is operative to receive said feedback signal from said actuator not through said ACC processor.

4. The flight control system as set forth in claim 1, in which

said comparing section is operative to receive said actuator control signal generated by said ACC processor not through said ACC processor.

5. The flight control system as set forth in claim 1, in which

said FCC processor comprises:

an instruction signal generating section for generating an instruction signal to operate said actuator on the basis of an operational instruction signal inputted from a pilot and a state signal indicative of the state of an aircraft, and

a reference signal generating section for generating a reference signal on the basis of said instruction signal generated by said instruction signal generating section and said feedback signal from said actuator, and

said comparing section is operative to compare said actuator control signal generated by said ACC processor with said reference signal generated by said reference signal generating section to detect a failure.

6. The flight control system as set forth in claim 1, in which

said actuator control computer further comprises

a digital analog converter for converting said actuator control signal generated by said ACC processor from digital to analog format to be outputted to said servo amplifier and said FCC processor, and

said servo amplifier is operative to amplify said actuator control signal in analog format converted by said digital analog converter to be outputted to said actuator, and

said comparing section is operative to compare said actuator control signal in analog format converted by said digital analog converter with said reference signal generated by said FCC processor to detect a failure.

7. The flight control system as set forth in claim 1,

said actuator control computer further comprises

a control prevention section for preventing said actuator from being controlled by said actuator control computer,

said comparing section is operative to compare said actuator control signal generated by said ACC processor with said reference signal generated by said FCC processor to generate a control prevention signal in accordance with the result of the comparison, and

said control prevention section is operative to prevent said actuator from being controlled by said actuator control computer in response to said control prevention signal generated by said comparing section.

8. The flight control system as set forth in claim 7, in which

said comparing section is operative to output said control prevention signal to said control prevention section not through said ACC processor.

9. The flight control system as set forth in claim 1, in which

said comparing section forms part of said FCC processor.

10. The flight control system as set forth in claim 1, further comprising a data bus for connecting said actuator control computer with said flight control computer so that said actuator control computer is operative to receive said instruction signal and said control prevention signal from said flight control computer and transmit said actuator control signal and said feedback signal to said flight control computer.

11. A flight control system for controlling a flight of an aircraft, comprising:

an actuator for actuating flight control surfaces and outputting a feedback signal in return;

a flight control computer for operating said actuator; and

an actuator control computer for controlling the operation of said actuator;

said flight control computer comprising;

an FCC processor for generating an instruction signal to operate said actuator on the basis of an operational instruction signal inputted from a pilot and a state signal indicative of the state of an aircraft, and generating a reference signal on the basis of said instruction signal and said feedback signal from said actuator,

said actuator control computer comprising;

an ACC processor for generating an actuator control signal on the basis of said instruction signal generated by said FCC processor and said feedback signal from said actuator, and

a servo amplifier for amplifying said actuator control signal generated by said ACC processor to be outputted to said actuator,

said actuator is operative to actuate said flight control surfaces in accordance with said actuator control signal amplified by said servo amplifier and output a feedback signal in return,

whereby

said flight control computer further comprises;

a comparing section for comparing said actuator control signal generated by said ACC processor with said reference signal generated by said FCC processor to detect a failure,

said FCC processor is operative to generate said reference signal in accordance with FCC software,

said ACC processor is operative to generate said actuator control signal in accordance with ACC software, and

said FCC software is different from said ACC software in design.