Aircraft deceleration brake control system

• US 5,136,510 A
• Filed: 02/20/1990
• Issued: 08/04/1992
• Est. Priority Date: 02/20/1990
• Status: Expired due to Term

• Current Assignee: Aircraft Braking Systems Corp. (Meggitt-USA, Inc.)
• Original Assignee: Aircraft Braking Systems Corp. (Meggitt-USA, Inc.)
• Inventors: Beck, Arnold A.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US07/483,200
• Time in Patent Office: 896 Days
• Field of Search: 364/426.01, 364/426.02, 244/110 A, 244/111, 303/93, 303/97, 303/104, 303/105
• US Class Current: 701/70
• CPC Class Codes: B60T 13/66 Electrical control in fluid-pressure brake systems
• CPC Class Codes: B60T 8/00 Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force by changing number of effective brake cylinders in power brake systems B60T17/10
• CPC Class Codes: B60T 8/1703 for aircrafts
• CPC Class Codes: B64C 25/426 Braking devices providing an automatic sequence of braking
• CPC Class Codes: B64C 25/48 differentially operated for steering purposes

Abstract

An aircraft deceleration brake control system receives deceleration command signals from left and right brake pedals of an aircraft. An amplifier generates the difference between the two command signals while an inertial navigation system of the aircraft provides a signal corresponding to the instantaneous deceleration of the aircraft. First and second control signals, corresponding to the respective command signals, are generated as a function of the difference in value between the command signals and the amplitude of the instantaneous deceleration signal.

Claims

1. An aircraft deceleration brake control system, comprising:

first and second brake pedals respectively presenting first and second command signals;

first means for receiving said first and second command signals and generating a difference signal corresponding to a difference between said first and second command signals;

second means for generating a feedback signal corresponding to instantaneous deceleration of the aircraft;

third means for receiving said first and second command signals, said difference signal, and said feedback signal and generating therefrom first and second control signals, said first control signal being applied to a first brake valve driver, and said second control signal being applied to a second brake valve driver; and

wherein said first control signal equals said first command signal minus said feedback signal when said first command signal is greater than or equal to said second command signal.

2. The aircraft deceleration brake control system according to claim 1 wherein said second control signal equals said second command signal minus said difference signal when said first command signal is greater than said second command signal.

3. The aircraft deceleration brake control system according to claim 1, wherein said second control signal equals said second command signal minus said feedback signal when said second command signal is greater than or equal to said first command signal.

4. The aircraft deceleration brake control system according to claim 3, wherein said first control signal equals said first command signal minus said difference signal when said second command signal is greater than said first command signal.

5. The aircraft deceleration brake control system according to claim 1, wherein said third means comprises a pair of parallel amplifiers, oppositely biased such that a first of said amplifiers passes said difference signal only when said second command signal is greater than said first command signal, and a second of said amplifiers passes said difference signal only when said first command signal is greater than said second command signal.

6. The aircraft deceleration brake control system according to claim 5, wherein said first means comprises an amplifier generating said difference signal with a gain of less than unity.

7. An aircraft deceleration brake control system, comprising:

first and second brake pedals respectively presenting first and second command signals;

first means for receiving said first and second command signals and generating a difference signal corresponding to a difference between said first and second command signals;

second means for generating a feedback signal corresponding to instantaneous deceleration of the aircraft;

third means for receiving said first and second command signals, said difference signal, and said feedback signal and generating therefrom first and second control signals, said first control signal being applied to a first brake valve driver, and said second control signal being applied to a second brake valve driver; and

wherein said second control signal equals said second command signal minus said feedback signal when said second command signal is greater than or equal to said first command signal.

8. The aircraft deceleration brake control system according to claim 7, wherein said first control signal equals said first command signal minus said difference signal when said second command signal is greater than said first command signal.

9. An aircraft deceleration brake control system, comprising:

first and second brake pedals respectively presenting first and second command signals;

first means for receiving said first and second command signals and generating a difference signal corresponding to a difference between said first and second command signals;

second means for generating a feedback signal corresponding to instantaneous deceleration of the aircraft; and

third means for receiving said first and second command signals, said difference signal, and said feedback signal and generating therefrom first and second control signals, said first control signal being applied to a first brake valve driver, and said second control signal being applied to a second brake valve driver, said third means comprising a pair of parallel amplifiers, oppositely biased such that a first of said amplifiers passes said difference signal when said second command signal is greater than said first command signal, and a second of said amplifiers passes said difference signal only when said first command signal is greater than said second command signal.

10. The aircraft deceleration brake control system according to claim 9, wherein said first means comprises an amplifier generating said difference signal with a gain of less than unity.