Flight control module with integrated spoiler actuator control electronics

• US 6,561,463 B1
• Filed: 07/14/2000
• Issued: 05/13/2003
• Est. Priority Date: 07/14/2000
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Todd, John, Yount, Larry
• Primary Examiner(s): Poon, Peter M.
• Assistant Examiner(s): Collins, Timothy D.
• Application Number:
  US09/616,195
• Time in Patent Office: 1,033 Days
• Field of Search: 244/90.A, 244/196, 244/197, 244/225, 244/227, 244/228, 244/193, 244/90.R, 244/113, 244/110.D, 244/75.R, 244/213, 244/220, 244/221
• US Class Current: 244/196
• CPC Class Codes: B64C 9/12 surfaces of different type or function being simultaneously adjusted
• CPC Class Codes: B64C 9/32 Air braking surfaces
• CPC Class Codes: B64C 9/323 associated with wings
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A flight control module with integrated actuator spoiler control electronics, where the flight control functions have been integrated into the integrated modular avionics through the use of a flight control module (“FCM”), the FCM being configured to contain spoiler actuator control electronics (“ACE”). The spoiler ACE is used to control the roll functions of the spoiler. The spoiler ACE is configured to be separate from the FCM, even though it is located within the same modules and receives its power independent of the power supply for the FCM. In the event of a failure of the primary flight control surfaces of an airplane, the spoilers can be used to control the roll of the aircraft because the spoiler ACE is independent of the ACE used to control the primary flight control surfaces. The spoiler ACE can also be used in the event of a failure of the FCM because the spoiler ACE is independent of the FCM.

Claims

1. A module for insertion into an integrated modular avionics unit for use in an airplane comprising:

a flight control computer; and

actuator control electronics coupled to a spoiler;

wherein

said module is inserted into the integrated modular avionics unit and said flight control computer augments control of the airplane, and wherein said actuator control electronics is configured to operate said spoiler in the event of a failure of said flight control computer to provide backup roll control of said airplane.

2. The module of claim 1 wherein,

said module further comprises a connector at the rear of said module configured to interface with a backplane located on said integrated modular avionics unit.

3. The module of claim 2, wherein

said connector is configured to supply power and data to said module.

4. The module of claim 3, wherein

said module further comprises a power input independent of said connector.

5. The module of claim 4, wherein

said power input is configured to supply power only to said actuator control electronics.

6. The module of claim 1, wherein

said flight control computer provides augmentation information to said actuator control electronics.

7. The module of claim 6, wherein

said actuator control electronics is configured to operate said spoiler through an actuator coupled to said spoiler by sending electrical signals to said actuator.

8. The module of claim 1, wherein

said actuator control electronics comprises an augmentation unit, an interlock unit, and a limiter;

wherein both said limiter and said interlock unit are coupled to said augmentation unit;

said augmentation unit is coupled to input units, external to said module, controlled by a pilot;

said augmentation unit is coupled to a hydraulic actuator external to said module; and

said hydraulic actuator is coupled to a spoiler located on a wing of the airplane.

9. The module of claim 8, wherein

said interlock unit is coupled to at least one hardware sensor;

wherein,

said hardware sensor is configured to indicate when said airplane is on the ground; and

said interlock unit is configured to prevent certain commands from said flight control computer from being transmitted to said augmentation unit in the event said hardware sensor fails to indicate that said airplane is on the ground.

10. The module of claim 8, wherein

said limiter is configured to prevent the transmission of signals outside a predetermined range from said flight control computer to said analog augmentation unit.

11. The module of claim 8, wherein

said augmentation unit comprises an analog summer unit;

said interlock unit comprises analog electronics; and

said limiter comprises analog electronics.