Fuzzy logic antiskid control system for aircraft

• US 6,088,646 A
• Filed: 10/25/1996
• Issued: 07/11/2000
• Est. Priority Date: 10/25/1996
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Wiel, Colin T.
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): PIPALA, EDWARD J
• Application Number:
  US08/736,650
• Time in Patent Office: 1,355 Days
• Field of Search: 701/77, 701/70, 701/71, 303/100, 303/194, 303/126, 244/111
• US Class Current: 701/77
• CPC Class Codes: B60T 8/174 characterised by using special control logic, e.g. fuzzy logic , neural computing

Abstract

An antiskid control system for aircraft braking consisting of an iterative system having inputs including wheel speed, time since touchdown and the value of the control current generated by the previous iteration. Utilizing the previous value and applying fuzzy logic rules, the system modifies itself to adjust for variations in the coefficient of friction between the wheels and the runway.

Claims

1. An antiskid brake control system for an aircraft for providing an antiskid control current to an antiskid valve comprising in combination:

an iterative control system responsive to wheel speed and time since touchdown;

said iterative control system further responsive to the antiskid control current generated by a previous iteration;

said iterative control system utilizing four fuzzy inference systems for determining the values of four intermediate variables to provide said antiskid control current to the antiskid valve.

2. The antiskid brake control system of claim 1 wherein said four intermediate variables are reference velocity rate limit, change in antiskid current, gain, and change in base limit.

3. A method for estimating aircraft velocity comprising the steps of:

reading wheel speed;

comparing a subsequent wheel speed reading with a previous reference velocity; and

limiting the change in wheel speed to an amount determined by fuzzy inference.

5. The method according to claim 3 wherein said fuzzy interference utilizes current base limit and time since touchdown as inputs.

4. An antiskid control system for an aircraft for providing an antiskid control current for an antiskid valve comprising in combination:

an iterative system responsive to wheel speed, time since touchdown and the antiskid control current generated by a previous iteration for providing said antiskid control current;

fuzzy logic rules for adjusting said iterative system for variation in the coefficient of friction between the wheels of said aircraft and the runway.

6. An antiskid brake control system for aircraft utilizing a fuzzy system to calculate reference velocity limit;

said fuzzy inference system receiving base current limit and time since touchdown as inputs, and providing reference velocity rate limit as output.

7. An antiskid brake control system for aircraft utilizing a fuzzy system to calculate Gain;

said fuzzy inference system receiving base current limit as input and giving gain as output.

8. An antiskid brake control system for aircraft utilizing fuzzy system to calculate base current limit;

said fuzzy inference system receiving deviation of antiskid current from base limit, time since skid, wheelspeed error, and derivative of wheelspeed as inputs, and giving change in base limit as output.

9. A method of antiskid brake control for an aircraft comprising the steps of:

calculating a reference velocity by fuzzy inference;

calculating decision variables wheelspeed error, rate of change of wheelspeed error, derivative of wheelspeed, second derivative of wheelspeed, time since touchdown, time since skid, and deviation between base current limit and antiskid current limit;

calculating Δ

base current by fuzzy inference;

calculating Δ

antiskid current by fuzzy inference;

calculating gain by fuzzy inference; and

limiting antiskid current to base limit level.

10. An antiskid brake control system for an aircraft for providing an antiskid control current to an antiskid valve comprising in combination:

an iterative control system responsive to wheel speed and time since touchdown;

said iterative control system further responsive to the antiskid control current generated by a previous iteration;

said iterative control system utilizing four fuzzy inference systems for determining the values of four intermediate variables to provide said antiskid control current to the antiskid valve; and

wherein said four intermediate variables are reference velocity rate limit, change in antiskid current, gain and change in base limit.