Flight control system especially suited for VTOL vehicles

• US 7,946,528 B2
• Filed: 04/17/2006
• Issued: 05/24/2011
• Est. Priority Date: 04/15/2005
• Status: Active Grant

• Current Assignee: Urban Aeronautics Ltd.
• Original Assignee: Urban Aeronautics Ltd.
• Inventors: Yoeli, Raphael
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US11/405,003
• Publication Number:
  US 20070034734A1
• Time in Patent Office: 1,863 Days
• Field of Search: 244/23.A, 244/23.B, 244/23.C, 244/23.D, 244/76.R, 244/195, 244/194
• US Class Current: 244/76.00R
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms

Abstract

Flight control systems have plural control subsystems with redundancies organized so as to provide continued but degraded control power over critical aircraft flight operating parameters even if any one complete control subsystem catastrophically fails. One example described in detail for a VTOL craft includes four groups of controls, each group comprising inputs relating to six degrees of freedom of the vehicle, at least one control computer and a plurality of actuators; each group utilizing 25% of required flight control power for the vehicle.

Claims

1. An aircraft flight control system having plural control subsystems with redundancies organized so as to provide continued but degraded control power over critical aircraft flight operating parameters even if any one complete control subsystem catastrophically fails, said system comprising:

a plurality of pilot controlled input sensors associated with each of a plurality of degrees of freedom in aircraft flight movement;

a plurality of aircraft flight control actuators associated with each of the plurality of degrees of freedom in aircraft flight movement;

a plurality of aircraft flight state sensors associated with each of a plurality of aircraft flight state conditions including at least altitude and speed;

the plural control subsystems, each having at least one control computer subsystem connected to;

(a) receive inputs from at least one of said pilot controlled input sensors for each of said plurality of degrees of freedom, (b) receive inputs from at least one of said flight state sensors for each of said plurality of aircraft flight conditions, and (c) provide outputs to at least one of said flight control actuators associated with each of said plural degrees of freedom;

said inputs and outputs to the control computer subsystem of each of said plural control subsystems being selected such that a catastrophic and complete failure of any one of said plural control subsystems causes continued control power over critical aircraft flight parameters by remaining unfailed ones of said plural control subsystems, degraded to less than 100% of total available control power, but sufficient to permit controlled aircraft descent to a landing.

2. An aircraft flight control system as in claim 1 comprising N of said plural control subsystems, each of said plural control subsystems providing 1/N of the total available control power over said critical aircraft flight parameters when all of said plural control subsystems are functioning without impairment, and wherein N is a positive integer.

3. An aircraft flight control system as in claim 2 wherein N=4.

4. An aircraft flight control system as in claim 3 wherein:

there are at least four pilot controlled input sensors associated with each of (a) pitch/push, (b) roll/slide, (c) pedals/yaw and (d) speed.

5. An aircraft flight control system as in claim 4 wherein said aircraft flight state sensors comprise at least four flight condition detection subsystems each of which independently monitors vehicle inertial position, rate and acceleration, altitude and airspeed.

6. An aircraft flight control system as in claim 2 for a VTOL aircraft having fore and aft lift air passage ducts with plural groups of directional control vanes disposed at each duct and wherein said control vanes are divided into groups, each group of vanes being independently controlled by one of said N control subsystems.

7. An aircraft flight control system as in claim 6 wherein each of said air passage ducts has a rotatable lift air generating fan there-within and plural control inputs associated therewith, said inputs to the control computer subsystem being grouped and connected for control by different respective ones of said N control subsystems.

8. An aircraft flight control system as in claim 7 wherein said VTOL aircraft also has at least one forward force generating propeller with plural control inputs that are connected for control by different respective ones of said N control subsystems.

9. An aircraft incorporating an aircraft flight control system as in claim 1.

10. A method for providing aircraft flight control utilizing plural control subsystems with redundancies organized so as to provide continued but degraded control power over critical aircraft flight operating parameters even if any one complete control subsystem catastrophically fails, said method comprising:

providing a plurality of pilot controlled input sensors associated with each of a plurality of degrees of freedom in aircraft flight movement;

providing a plurality of aircraft flight control actuators associated with each of a plurality of degrees of freedom in aircraft flight movement;

providing a plurality of aircraft flight state sensors associated with each of a plurality of aircraft flight state conditions including at least altitude and speed;

providing each of the plural control subsystems with at least one control computer subsystem, and connecting the at least one control computer subsystem in each of the plural control subsystems so as to;

(a) receive inputs from at least one of said pilot controlled input sensors for each of said plurality of degrees of freedom, (b) receive inputs from at least one of said flight state sensors for each of said plurality of aircraft flight conditions, and (c) provide outputs to at least one of said flight control actuators associated with each of said plural degrees of freedom;

selecting said inputs and outputs to the control computer subsystem of each of said plural control subsystems such that a catastrophic and complete failure of any one of said plural control subsystems causes continued control power over critical aircraft flight parameters by remaining unfailed ones of said plural control subsystems, degraded to less than 100% of total available control power, but sufficient to permit controlled aircraft descent to a landing.

11. A method as in claim 10 comprising providing N of said plural, control subsystems, each of said plural control subsystems independently providing 1/N of the total available control power over said critical aircraft flight parameters when all of said plural control subsystems are functioning without impairment, and where N is a positive integer.

12. A method as in claim 11 wherein N=4.

13. A method as in claim 12 wherein:

there are at least four pilot controlled input sensors associated with each of (a) pitch/push, (b) roll/slide, (c) pedals/yaw and (d) speed.

14. A method as in claim 13 wherein said aircraft flight state sensors comprise at least four flight condition detection subsystems each of which independently monitors vehicle inertial position, rate and acceleration, altitude and airspeed.

15. A method as in claim 11 for use in a VTOL aircraft having fore and aft lift air passage ducts with plural groups of directional control vanes disposed at each duct and wherein said control vanes are divided into groups, each group of vanes being independently controlled by one of said N control subsystems.

16. A method as in claim 15 wherein each of said air passage ducts has a rotatable air generating fan there-within and plural control inputs associated therewith, said lift control inputs being grouped and connected for control by different respective ones of said N control subsystems.

17. A method as in claim 16 wherein said VTOL aircraft also has at least one forward force generating propeller with plural control inputs that are connected for control by different respective ones of said N control subsystems.

18. A method as in claim 10 wherein there is provision for sharing of data between said plural control subsystems.