Manual and computerized flight control system with natural feedback

• US 8,380,364 B2
• Filed: 05/17/2006
• Issued: 02/19/2013
• Est. Priority Date: 05/17/2006
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Textron Innovations Incorporated (Textron Inc)
• Inventors: Ciholas, Philippe A., Palmer, Mark W.
• Primary Examiner(s): Tran, Khoi
• Assistant Examiner(s): Kiswanto, Nicholas
• Application Number:
  US11/383,791
• Publication Number:
  US 20070271008A1
• Time in Patent Office: 2,470 Days
• Field of Search: 701/3, 244/75.1, 244/76.R, 244/195, 244/87, 244/227, 244/226, 244/228, 244/223, 244/229
• US Class Current: 701/3
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: B64C 13/044 operated by feet, e.g. pedals
• CPC Class Codes: B64C 13/30 using cable, chain, or rod mechanisms
• CPC Class Codes: B64C 13/38 with power amplification
• CPC Class Codes: B64C 9/04 with compound dependent movements
• CPC Class Codes: B64C 9/10 one surface adjusted by movement of another, e.g. servo tabs B64C9/04 takes precedence; adjusting surfaces of different type or function B64C9/12

Abstract

A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces.

Claims

1. A flight control system comprising:

at least one control surface having independent segments;

a control means having at least one force sensor located therein;

a manual linkage arrangement directly coupling the control means to a first independent segment of the at least one control surface thereby enabling a user to forcibly position the first independent segment during flight without the aid of any hydraulic system;

the linkage arrangement also adapted to directly receive feedback resulting from aerodynamic forces exerted on the first independent segment during flight, and transmit the aerodynamic forces back to the control means such that the at least one force sensor measures the force applied to the control means by the operator of the system in response to the aerodynamic forces;

a powered actuator coupled to a second independent segment of the at least one control surface; and

a signal connection for coupling the powered actuators to a computing device and the computing device to the control means, such that the computing device can provide commands to the powered actuators to position the second independent segment of the control surface according to a predetermined schedule based on force measured at the at least one force sensor;

wherein no feedback from the second independent segment is measured by the at least one force sensors.

2. The system of claim 1 wherein the at least one control surface is selected from the group comprising rudders, elevators, and ailerons.

3. The system of claim 1 wherein the control means comprises hand-operated and foot-operated controls.

4. The system of claim 1 wherein the manual linkage arrangement provides direct movement of the first independent segment corresponding to movement of the control means by the operator.

5. The system of claim 1 wherein the force sensors are located in a pair of vertical upright members in the control means.

6. The system of claim 1 wherein the computing device receives aircraft performance data and adjusts the position of the second independent segment to maintain operation within a desired flight envelope.

7. The system of claim 1 wherein aircraft movement as a result of control surface changes is a summation of the first independent segment which is not computer controlled and the powered actuator coupled independent segments which alone executes the automated trim, envelope protection, stability enhancing functions at the direction of the computing device during flight.

8. An apparatus comprising:

a control surface on one side of an aircraft being comprised of a first independently movable segment and a second independently movable segment;

a control means having a plurality of force sensors located therein;

a mechanical system directly manual coupling the control means to the first independently movable segment enabling pilot-initiated mechanical forces alone to position the first independently movable segment such that the plurality of force sensors measure the force applied to the control means by the operator of the apparatus in response to the aerodynamic forces acting against the first independently movable segment;

a powered servo actuator coupled to the second independently movable segment, the second independently movable segment not directly coupled by any mechanical linkage to the control means;

a signal connection for coupling the powered servo actuators to a computing device and the computing device to the control means, such that the computing device sends a signal to the powered servo actuators for the second independently movable segment coupled thereto to position the second independently movable segment according to a schedule based on force measured at the force sensors.

9. The apparatus of claim 8 wherein the control surface is selected from the group comprising rudders, elevators, and ailerons.

10. The apparatus of claim 9 wherein the control means comprises hand-operated and foot-operated controls.

11. The apparatus of claim 8 wherein the computing device receives aircraft performance data and causes the powered servo actuator to adjust a position of the second, independently movable segment to maintain operation within a desired flight envelope.

12. The system of claim 8 wherein aircraft movement as a result of control surface changes is a summation of the independent movements of the first and second independently movable segments.

13. A method of providing feedback from a control surface to a pilot through a pilot-operated flight control device of an aircraft, the method comprising:

splitting the control surface into first and second portions;

directly mechanically linking the first portion to the pilot-operated flight control device such that the pilot alone applies a direct force necessary to operate a corresponding direct movement of the first portion, and aerodynamic forces bearing on the first portion are reciprocated back to be felt by the pilot through the pilot-operated flight control device without interference by any power-related equipment;

electronically powering and positioning the second portion in response to force data received from the pilot-operated flight control device.

14. The method of claim 13 comprising:

including both hand and foot controls on the pilot-operated flight control device to receive physical inputs from the pilot; and

receiving the force data from sensors on the pilot-operated flight control device upon receiving the physical inputs from the pilot.