Aircraft control system

• US 6,986,486 B2
• Filed: 03/08/2001
• Issued: 01/17/2006
• Est. Priority Date: 03/29/2000
• Status: Expired due to Fees

• Current Assignee: BAE Systems Plc
• Original Assignee: BAE Systems Plc
• Inventors: Darbyshire, Ian Thomas
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US10/240,190
• Publication Number:
  US 20030141418A1
• Time in Patent Office: 1,776 Days
• Field of Search: 244/76.R, 244/76.C, 244/191, 244/194, 244/195, 701/3, 701/8, 701/9, 701/10
• US Class Current: 244/195
• CPC Class Codes: G05D 1/0055 with safety arrangements
• CPC Class Codes: G05D 19/02 characterised by the use of electric means

Abstract

This invention control system having: means (12) for detecting an irregularity in aircraft handling during flight; means (18) for causing temporarily a rigid body excitation in at least a portion of the aircraft; means (20) for monitoring an actual response to the excitation; means (22) for comparing the actual response and a target response to the rigid body excitation; and means (14) responsive to an output from the comparison means for determining the need for a modification of the current flight plan and for generating a corresponding control output. The invention also provides a corresponding method for controlling an aircraft.

Claims

1. An aircraft control system having:

means for detecting an irregularity in aircraft handling during flight;

means, responsive to an output from the detecting means, for causing a temporary application of a rigid body excitation in at least a portion of the aircraft;

means for monitoring an actual response to the rigid body excitation;

means for effecting a comparison of the actual response with a target response of the aircraft to the rigid body excitation; and

means responsive to an output from the comparison means for determining the need for a modification of the current flight plan for dealing with the irregularity and for generating a corresponding control output.

2. A system according to claim 1 which includes means for calculating a target response to the excitation.

3. A system according to claim 2 in which the calculating means comprise a stored mathematical model.

4. A system according to claim 3 in which the mathematical model is based on Euler Dynamic Equations of Motion.

5. A system according to claim 3 in which the mathematical model is based on an analysis of aircraft control laws and dynamic characteristics undertaken during design.

6. A system according to claim 1, in which the means for causing excitation comprise means for temporarily applying a low level periodic force to a rigid portion of the aircraft frame.

7. A system according to claim 1, in which the monitoring means is arranged to detect a frequency/transient characteristic of at least a portion of the aircraft.

8. A system according to claim 1, in which the monitoring means is arranged to detect at least one of the following:

inertial aircraft body rates, aircraft accelerations, and control surface positions.

9. A system according to claim 1, in which the comparison means is arranged to generate a flight condition analysis as an output.

10. A system according to claim 1, in which the control output represents one of a flight control adjustment signal and a flight plan alteration signal.

11. A method of controlling an aircraft comprising:

detecting an irregularity in aircraft handling during flight;

causing a temporary application of a rigid body excitation in at least a portion of the aircraft in response to such detection;

monitoring the actual response of at least a portion of the aircraft to the rigid body excitation;

comparing the actual response with a target response of the aircraft to the rigid body excitation;

determining the need for a modification of the current flight plan for dealing with the irregularity, and

generating a corresponding control output.

12. A method according to claim 11 in which the rigid body excitation comprises a low level periodic force temporarily applied to a rigid portion of the aircraft frame.

13. A method according to claims 11 in which the step of monitoring comprises detecting frequency/transient characteristics of at least a portion of the aircraft.

14. A method according to claim 11, which includes calculating a target response to the rigid body excitation.

15. A method according to claim 14 in which the step of calculating comprises employing a stored mathematical model of anticipated responses.

16. A method according to claim 11, in which the step of comparing includes generating a flight condition analysis.

17. A method according to claim 11, including the step of adjusting one of the flight control and altering the flight plan in response to the control output.