Fuzzy logic based emergency flight control with thrust vectoring capability

• US 6,662,086 B2
• Filed: 06/18/2001
• Issued: 12/09/2003
• Est. Priority Date: 09/25/1999
• Status: Expired due to Term

• Current Assignee: Jerome H. Lemelson, Robert D. Pedersen, Tracy D. Blake
• Original Assignee: Jerome H. Lemelson, Robert D. Pedersen, Tracy D. Blake
• Inventors: Blake, Tracy D., Lemelson, Jerome H., Pedersen, Robert D.
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): Hernandez, Olga
• Application Number:
  US09/884,341
• Publication Number:
  US 20010044680A1
• Time in Patent Office: 904 Days
• Field of Search: 701/3, 701/4, 701/14, 701/40, 701/44, 701/200, 701/213, 701/215, 340/988, 340/993, 340/994, 731/70.R
• US Class Current: 701/3
• CPC Class Codes: B64C 13/16 actuated automatically, e.g. responsive to gust detectors
• CPC Class Codes: B64C 15/02 the jets being propulsion jets
• CPC Class Codes: B64D 31/06 actuated automatically

Abstract

A fuzzy logic based emergency flight control system for an aircraft. The system has a thrust vectoring flight control system, an aerodynamic flight control system, and a fuzzy logic controller. The thrust vectoring flight control system provides thrust to the aircraft in an emergency situation alone or in combination with aerodynamic flight controls. The fuzzy logic controller executes fuzzy logic algorithms for assessing the emergency situation and controlling the aircraft thrust vectoring and aerodynamic flight control systems in the emergency situation. An adjustable nozzle is coupled to an exhaust thrust end of an engine of the aircraft and is angularly adjusted to direct thrust of the aircraft in a determined direction after fuzzy logic controller assessment of the emergency situation. Alternatively, an adjustable panel is mounted to a wing of the aircraft and positionable near an exhaust thrust end of an engine of the aircraft to direct thrust of the aircraft in a determined direction after the fuzzy logic controller assessment of the emergency situation. The fuzzy logic controller further includes a position, attitude, and heading determination system for determining position, attitude, and heading of the aircraft. The position, attitude, and heading determination system further includes global positioning system receivers mounted at extremities of the aircraft and a determination processor coupled to the global positioning receivers for calculating and assessing position, attitude, and heading of the aircraft.

Claims

1. A fuzzy logic method for controlling an aircraft comprising:

(a) obtaining input variables related to the aircraft, including;

(1) obtaining at least one of altitude of the aircraft, wind shear magnitude in proximity of the aircraft, air speed of the aircraft, and proximity parameters of the aircraft to other aircraft and objects;

(2) obtaining at least one of position, attitude, and heading of the aircraft; and

(3) communicating the input variables to a fuzzy logic controller;

(b) fuzzifying the input variables into input fuzzy sets by using the fuzzy logic controller;

(c) obtaining fuzzified output variables from the fuzzified input variables;

(d) using the fuzzified output variables to calculate crisp output values for controlling the aircraft; and

(e) executing commands based on the crisp output values wherein the commands control the aircraft;

wherein;

(f) obtaining position, attitude, and heading of the aircraft further comprises;

(1) locating global positioning system receivers at extremities of the aircraft;

(2) using the global positioning receivers to communicate to global positioning system satellites; and

(3) using received signals from the global positioning system satellites for determining at least one of position, attitude, and heading of the aircraft.

2. The fuzzy logic method for controlling an aircraft according to claim 1 wherein the input variables range in levels.

3. The fuzzy logic method for controlling an aircraft according to claim 2 wherein the range in levels includes at least a very low level, a low level, a medium level, a high level, and a very high level.

4. The fuzzy logic method for controlling an aircraft according to claim 2 wherein membership in the input fuzzy sets range from zero to one.

5. A fuzzy logic method for controlling an aircraft comprising:

(a) obtaining input variables related to the aircraft, including at least one of position, attitude, and heading of the aircraft, and communicating the input variables to a fuzzy logic controller;

(b) fuzzifying the input variables into input fuzzy sets by using the fuzzy logic controller;

(c) obtaining fuzzified output variables from the fuzzified input variables;

(d) using the fuzzified output variables to calculate crisp output values for controlling the aircraft;

(e) using a thrust vectoring system coupled to the aircraft wherein the thrust vectoring system is angularly adjustable in thrust and provides thrust magnitude to the aircraft; and

(f) executing commands based on the crisp output values wherein the commands control the aircraft;

wherein;

(g) obtaining position, attitude, and heading of the aircraft further comprises;

(1) locating global positioning system receivers at extremities of the aircraft;

(2) using the global positioning receivers to communicate to global positioning system satellites; and

(3) using received signals from the global positioning system satellites for determining at least one of position, attitude, and heading of the aircraft.

6. The fuzzy logic method for controlling an aircraft according to claim 5 further comprising obtaining current thrust magnitude of the thrust vectoring system.

7. The fuzzy logic method for controlling an aircraft according to claim 5 further comprising obtaining current thrust angle of the thrust vectoring system.

8. A fuzzy logic method for controlling an aircraft comprising:

(a) obtaining input variables related to the aircraft, including at least one of position, attitude, and heading of the aircraft, and communicating the input variables to a fuzzy logic controller;

(b) fuzzifying the input variables into input fuzzy sets by using the fuzzy logic controller;

(c) obtaining fuzzified output variables from the fuzzified input variables;

(d) using the fuzzified output variables to calculate crisp output values for controlling the aircraft; and

(e) executing commands based on the crisp output values wherein the commands control the aircraft;

wherein;

(f) obtaining position, attitude, and heading of the aircraft further comprises;

(1) locating global positioning system receivers at extremities of the aircraft;

(2) using the global positioning receivers to communicate to global positioning system satellites; and

(3) using received signals from the global positioning system satellites for determining at least one of position, attitude, and heading of the aircraft; and

(g) at least some of the output variables are thrust vectoring flight control variables and at least some of the commands are thrust vectoring flight control commands.

9. The fuzzy logic method for controlling an aircraft according to claim 8 wherein output variables are thrust vectoring flight control variables and aerodynamic flight control variables and the commands are thrust vectoring flight control commands and aerodynamic flight control variables.

10. The fuzzy logic method for controlling an aircraft according to claim 8 wherein one of the thrust vectoring flight control variables is a thrust vectoring nozzle angle variable and one of the thrust vectoring flight control commands is a thrust vectoring nozzle angle command for controlling thrust nozzle angle of a thrust vectoring flight control system in controlling the aircraft.

11. The fuzzy logic method for controlling an aircraft according to claim 8 wherein at least some of the output variable are aerodynamic flight control variables and at least some of the commands are aerodynamic flight control commands.

12. The fuzzy logic method for controlling an aircraft according to claim 11 wherein one of the aerodynamic flight control variables is a rudder angle variable and one of the aerodynamic flight control commands is a rudder angle command for controlling a rudder of the aircraft in controlling the aircraft.

13. The fuzzy logic method for controlling an aircraft according to claim 11 wherein one of the aerodynamic flight control variables is a flap angle variable and one of the aerodynamic flight control commands is a flap angle command for controlling flaps of the aircraft in controlling the aircraft.

14. The fuzzy logic method for controlling an aircraft according to claim 11 wherein one of the aerodynamic flight control variables is an aileron angle variable and one of the aerodynamic flight control commands is an aileron angle command for controlling ailerons of the aircraft in controlling the aircraft.

15. The fuzzy logic method for controlling an aircraft according to claim 11 wherein one of the aerodynamic flight control variables is an engine thrust magnitude variable and one of the aerodynamic flight control commands is an engine thrust magnitude command for controlling engine thrust of at least one engine of the aircraft in controlling the aircraft in the emergency situation.