Flight control system

• US 6,567,727 B2
• Filed: 09/18/2001
• Issued: 05/20/2003
• Est. Priority Date: 09/18/2000
• Status: Expired due to Term

• Current Assignee: Airbus Defence and Space GmbH (Airbus SE)
• Original Assignee: EADS Deutschland GmbH (Airbus SE)
• Inventors: Westphal, Peter
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): Marc-Coleman, Marthe Y.
• Application Number:
  US09/954,215
• Publication Number:
  US 20020055809A1
• Time in Patent Office: 609 Days
• Field of Search: 701/3, 701/4, 701/5, 701/6, 701/7, 701/8, 701/9, 701/10, 701/14, 701/17, 701/120, 701/77, 701/98
• US Class Current: 701/4
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: G05D 1/0055 with safety arrangements

Abstract

A flight control system automatically recognizes safety-critical flight conditions and transmits timely guidance to the pilot for correcting such flight conditions. The flight control system includes a computer which runs parallel to the flight control computer, and uses fuzzy logic to carry out risk evaluations with respect to actual flight conditions using knowledge bases implemented in the flight control system. The results of these risk evaluations are displayed in the cockpit.

Claims

1. A computer-based onboard aircraft flight information system which automatically and continuously evaluates flight data parameters determined on board, and displays information to the pilot determined from the evaluation, said flight information system comprising a computer which runs parallel to a flight control computer of the aircraft, wherein:

the computer which runs in parallel uses fuzzy logic to carry out risk evaluations with respect to actual aircraft flight conditions using knowledge bases implemented in the flight information system;

the results of the risk evaluations are displayed in the cockpit;

the flight information system determines individual risks relevant to the flight conditions and determines an overall risk therefrom; and

the overall risk is continuously indicated on the display as a luminous bar.

2. The flight information system according to claim 1, wherein with respect to a determined overall risk, in the event of danger, the flight control system automatically generates an operating instruction for the pilot, whose implementation can eliminate the dangerous flight condition.

3. The flight information system according to claim 2, wherein the operating instruction is also supplied additionally to a head up display.

4. The flight information system according to claim 3, wherein the overall risk is determined according to Sugeno summation methodology.

5. The flight information system according to claim 2, wherein the overall risk is determined according to Sugeno summation methodology.

6. The flight information system according to claim 1, wherein the overall risk is determined according to Sugeno summation methodology.

7. An aircraft flight information and warning system, comprising:

for an aircraft having a computer-based flight control system that includes a first flight control computer;

a second computer which runs in parallel to the first computer and shares information generated and received by the first computer;

fuzzy logic means implemented in said second computer, for performing risk evaluations with respect to actual aircraft flight conditions using knowledge bases implemented in the flight control system;

a display unit connected to display results of risk evaluations performed by said second computer;

the flight information system determines individual risks relevant to the flight conditions and determines an overall risk therefrom; and

the overall risk is continuously indicated on the display as a luminous bar.

8. The flight information system according to claim 7, wherein with respect to a determined overall risk, in the event of danger, the flight control system automatically generates an operating instruction for the pilot, whose implementation can eliminate the dangerous flight condition.

9. The flight information system according to claim 7, wherein the operating instruction is also supplied additionally to a head up display.

10. The flight information system according to claim 7, wherein the overall risk is determined according to Sugeno summation methodology.