Control system with loadfeel and backdrive

• US 5,489,830 A
• Filed: 09/09/1994
• Issued: 02/06/1996
• Est. Priority Date: 09/09/1994
• Status: Expired due to Term

• Current Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Original Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Fernandez, Carlos P.
• Primary Examiner(s): Ip, Paul
• Application Number:
  US08/303,421
• Time in Patent Office: 515 Days
• Field of Search: 318/560-646, 244/17, 244/13, 244/181, 244/234, 244/195, 244/177, 244/194, 244/223, 244/178, 244/76 R, 244/194, 244/179, 244/2, 244/6, 244/221, 244/188, 244/76 C, 244/135 A, 244/87 , 244/75 R, 244/228, 74/469, 74/471 XY, 74/862.05, 74/470
• US Class Current: 318/628
• CPC Class Codes: B64C 13/18 using automatic pilot
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa

Abstract

The control system includes a control member connected to a control centering device which resists operational control member movement and returns it to a neutral position upon release thereof. Force and position sensors connected to the control member determine operator force exerted thereon as well as the position thereof. Output from the sensors is transmitted to a computer which also receives data relating to position of aircraft controlled surfaces and aerodynamic forces acting on the aircraft as well as flight data, etc. The computer combines and compares that data with other data relating to frictional forces produced by movement of the mechanical control system and data relating to desired control member resistive forces under predetermined operational conditions. The computer thereby determines the magnitude of the control member resistive forces required to produce the desired tactile feel and provides an output based thereon to an actuator which applies these forces to the control member. When in automatic pilot mode, the computer provides an output to the actuator to move the control member to a position representing the command output that the computer provides to the controlled surfaces to control the position thereof.

Claims

1. A control system comprising:

a control member;

a control centering means connected to said member, said control centering means resisting operational movement of said member;

a control force sensor connected to said control member to sense operational forces applied to said member, said control force sensor having an output containing force data relating to the operational forces;

a control position sensor connected to said control member to sense the position of said control member, said control position sensor having an output containing position data relating to the position of the control member;

a control actuator electrically interconnecting said member and controlled structures for applying resistive forces to said member and operative forces to the structures;

a first databank having first data relating to frictional forces resisting operational movement of the controlled structures in response to operational movement of said member;

a second databank having second data relating to desired magnitude of forces resisting operational movement of said member under predetermined operational conditions; and

a computer processor unit for receiving the data from said databanks and receiving information from said control force sensor and said position sensor and utilizing said data to control said actuator in order to provide a desired resistive force to said member.

2. The system of claim 1 wherein said first databank includes data relating to frictional forces of mechanical control subsystem connected to the controlled structures.

3. The system of claim 1 further including a controlled structure position sensor connected to said controlled structure for providing data to said computer processor unit relating to position of the controlled structures.

4. The system of claim 1 further including an accelerometer for providing data to said computer processor unit for determination of aerodynamic forces acting on aircraft controlled by the control system.

5. The system of claim 1 wherein said actuator positions said member in response to command signals of the computer processor unit data when the controlled structures are under automatic pilot operation.

6. The system of claim 1 wherein said control centering means positions said member in a generally neutral position in the absence of manual forces applied thereto when not in automatic pilot operation mode.

7. The system of claim 1 wherein said control centering means includes a double acting bungee.

8. The system of claim 1 wherein said control centering means includes a loadfeel structure connected to said member for applying resistive forces to said member.

9. The system of claim 8 wherein said loadfeel includes a double-acting bungee.

10. The system of claim 8 wherein the resistive forces applied by said loadfeel and said control actuator are selectively either positive or negative.

11. The system of claim 1 wherein said actuator fncludes a reversible actuator for selectively driving said member and the controlled structures in response to output from said computer processor unit.

12. The system of claim 1 wherein said control member includes a steering wheel.

13. The system of claim 1 wherein said control member includes a column.

14. The system of claim 1 wherein said control member includes a pair of pedals.

15. The system of claim 1 wherein said position sensor includes a linear variable differential transformer.

16. The system of claim 1 wherein said computer processor unit includes software for comparing the force data relating to the operational force applied to said control member with the second data from said second databank relating to the desired magnitude of the operational force applied to said member under predetermined operational conditions and for providing an output to said actuator to apply a desired resistive force to said member in order to produce the desired magnitude of forces resisting operational movement of said control member.

17. The system of claim 1 wherein said software compares the force data relating to the operational force applied to said control member with the first data from said first databank relating to the frictional resistive forces which result from operation of the control system and with the second data from said second databank relating to desired magnitude of the operational force applied to said member under predetermined operational conditions for providing an output to said control actuator to apply a resistive force to said member to produce the desired magnitude of forces resisting operational movement of said control member.

18. The system of claim 1 wherein the control actuator is reversible.