Flight control systems

• US 8,401,716 B2
• Filed: 01/31/2007
• Issued: 03/19/2013
• 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:
  US11/669,565
• Publication Number:
  US 20070267548A1
• Time in Patent Office: 2,239 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 13/38 with power amplification
• CPC Class Codes: B64C 13/507 with artificial feel
• 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 method of operating a control surface on an aircraft, said control surface having a first independent section and a second independent section, said method comprising:

providing a device which receives inputs from a user via a mechanical system and angularly displaces said first section using a hydraulic device which is acted on by the mechanical system without any computer-aided correction;

receiving readings including (i) force measurements representative of operator effort from force sensors located on a pilot-operated control means which is a part of the mechanical system, and (ii) acceleration, airspeed, and altitude parameters into a computer system, the computer system using the readings to electronically control said second section and angularly displace said second section, the second section compensating for the lack of computer-aided correction given to the first section, the aerodynamic sum of effects caused by positions of the first section and second section together resulting in a desired aircraft response; and

providing an artificial feel system in the mechanical, system which provides variable resistance to the control means based either on aircraft performance parameters or nonlinear force curves.

2. A flight control system for an aircraft, said system comprising:

a control stick having two upright portions, each upright portion having a handle on top and a force sensor below the handle to receive pilot inputs;

a control surface split into three portions including a middle portion and two lateral portions, one lateral portion on each side of the middle portion, the lateral portions being operable independently from the middle portion;

a mechanical linkage connected to the control stick by a lever, and running to a power control unit, the power control unit being coupled to the middle portion of the control surface, the linkage translating movements of the control stick to operate the power control unit to position the middle portion;

an electronically controlled actuator coupled to each of the lateral portions for controllably positioning the lateral portions according to pilot inputs recognized by the force sensors, the force sensors transmitting signals to a computer, the computer then using the force sensor signals along with avionics data to control the lateral portions using the actuators and move the lateral portions such that they compensate for an angular position of the middle portion to maintain the control surface within a desired flight envelope; and

an artificial feel system attached to the lever from an opposite side of the control stick from the mechanical linkage, the artificial feel system giving the pilot feedback, and simulating the feel of a purely mechanical system, the artificial feel system providing variable resistance based on one of aircraft performance parameters and non-linear three curves.

3. The flight control system of claim 2 wherein the artificial feel system includes a bungee arrangement.

4. The flight control system of claim 2 wherein the artificial feel system provides variable resistance based on aircraft performance parameters.

5. The flight control system of claim 2 wherein the artificial feel system provides variable resistance based on nonlinear force curves.

6. The flight control system of claim 2 wherein the artificial feel system is a bungee system attached directly to the control stick.

7. The flight control system of claim 2 wherein the artificial feel system provides variable resistance based on aircraft performance parameters.

8. The flight control system of claim 2 wherein the artificial feel system provides variable resistance based on nonlinear force curves.