CONTROL SYSTEM INCLUDING TWO CONTROL COLUMNS THAT ARE COUPLED TO ENABLE CONTROLLED MEMBERS TO BE PLACED IN REQUIRED POSITIONS

• US 20090314901A1
• Filed: 06/29/2006
• Published: 12/24/2009
• Est. Priority Date: 06/30/2005
• Status: Active Grant

• Current Assignee: Dassault Aviation (Groupe Industriel Marcel Dassault)
• Original Assignee: Dassault Aviation (Groupe Industriel Marcel Dassault)
• Inventors: Guerard, Jeremie, Granier, Eric, Viet, Max-Maurice
• Granted Patent: US 7,648,106 B2
• Time in Patent Office: Days
• US Class Current: 244/76.R
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: G05G 11/00 Manually-actuated control mechanisms provided with two or more controlling members co-operating with one single controlled member
• CPC Class Codes: G05G 2009/04718 with cardan or gimbal type joint
• CPC Class Codes: G05G 2009/04766 providing feel, e.g. indexing means, means to create counterforce
• CPC Class Codes: G05G 9/047 the controlling member being movable by hand about orthogonal axes, e.g. joysticks for switches H01H25/04

Abstract

A control system for placing controlled members in required positions including two control columns assigned to the controlled members to be moved, each control column having two degrees of freedom. Two actuators controlled by two control circuits apply to their associated control column either a resisting torque or a displacement torque. Each control column is provided with a mechanical spring system spring-loading the associated control column into its neutral position and adapted to provide, in the event of manipulation of the corresponding control column, a resisting torque in support of the resisting torque supplied by the associated actuator.

Claims

1. A control system for placing controlled members in required positions, comprising two control columns, each of which is mounted on a gimbal and has two degrees of freedom assigned to the respective controlled members to be moved, and, for each of said control columns, and assigned to said respective degrees of freedom:

a) two actuators for applying to their associated control column either a resisting torque or a displacement torque for the associated degree of freedom,

b) two control circuits each of which is adapted

on the one hand, to control the actuator for the associated degree of freedom so that the actuator supplies a resisting torque opposing each manipulation of a first of the control columns exerted for that degree of freedom, and

on the other hand, to bring about, as a function of said manipulation of the first control column, a displacement of the second control column of the same amplitude, in the same direction and for the same degree of freedom,

c) two control column position sensors for supplying to the respective control circuits an associated control column position signal,

said control system further comprising

d) a mechanism for controlling displacement of said controlled members as a function of signals supplied by said control column position sensors,

wherein each control column is further provided with a mechanical spring system comprising for each of said degrees of freedom a return spring assembly for spring-loading the associated control column into its neutral position and adapted to provide, in the event of manipulation of the corresponding control column, a resisting torque in support of the resisting torque supplied by the associated actuator.

2. The control system according to claim 1, wherein said return spring assemblies are configured so that in an absence of resisting torques supplied by said actuators said assemblies generate approximately 90% of the respective total resisting torques that are applied to the control columns when said actuators supply their corresponding resisting torques.

3. The control system according to claim 1, wherein said control circuits are adapted to control said associated actuators in such a manner as to generate at least one end of travel stopping point felt when manipulating said control columns in both directions of displacement thereof for each of said degrees of freedom.

4. The control system according to claim 3, wherein the control circuit associated with at least one of said degrees of freedom is adapted to control said associated actuators in such a manner as to generate two successive mechanical stopping points of which one is a stopping point that can be overridden and the other is an end of travel stopping point, these stopping points being felt when manipulating the control column in at least one direction for the degree of freedom concerned.

5. The control system according to claim 3, wherein each of said control circuits comprises two interconnected control loops assigned to a degree of freedom of each of said control columns and each comprising an amplifier for supplying a drive signal to said actuators and an adder that are connected to the input of the amplifier and to which said control column position sensors for each control column assigned to the same degree of freedom are connected, the control column position signals of said sensors being applied to said adder with opposite signs.

6. The control system according to claim 5, wherein each of said control loops includes a first variable gain amplifier and a second variable gain amplifier respectively connected between said sensors and said adder, said variable gain amplifiers determining in said control loop for respective movements of the control columns on either side of a neutral point predetermined laws of variation of the resisting torque generated by the actuator controlled by that loop as a function of the displacement of the respective control column concerned.

7. The control system according to claim 6, wherein said predetermined variation laws are linear or quasi-linear.

8. The control system according to claim 7, wherein the linear or quasi-linear variation laws respectively associated with each degree of freedom of the control columns have different slopes for displacements of those control columns to either side of the neutral point.

9. The control system according to claim 8, wherein the variable gain amplifiers of the control loops assigned to at least one of the degrees of freedom can be switched to reverse the slopes of the corresponding variation laws according to whether the control column concerned is to the left or to the right of a user, a memory being provided in each of the control loops assigned to the same degree of freedom to maintain the slopes of the variation laws until the direction of displacement of the control column is reversed.

10. The control system according to claim 5, wherein each of said control loops includes electronic filters to produce a damping effect in the control of the movements of the control columns.

11. The control system according to claim 1, also comprising a mechanism for rendering said control circuits inoperative if the control column position signals supplied by said sensors assigned to the same degree of freedom differ from each other by a predetermined amount.

12. The control system according to claim 1, wherein said actuators are three-phase electric motors controlled by sinusoidal currents.

13. The control system according to claim 12, comprising a switching device for short-circuiting the windings of said motors.

14. A system for controlling the positioning of pitch and roll control surfaces, of an aircraft having a cockpit with dual controls, comprising a control system for placing controlled members in required positions, said control system including two control columns, each of which is mounted on a gimbal and has two degrees of freedom assigned to the respective controlled members to be moved, and, for each of said control columns, and assigned to said respective degrees of freedom a) two actuators for applying to their associated control column either a resisting torque or a displacement torque for the associated degree of freedom, b) two control circuits each of which is adapted on the one hand, to control the actuator for the associated degree of freedom so that the actuator supplies a resisting torque opposing each manipulation of a first of the control columns exerted for that degree of freedom, and on the other hand, to bring about, as a function of said manipulation of the first control column, a displacement of the second control column of the same amplitude, in the same direction and for the same degree of freedom, c) two control column position sensors for supplying to the respective control circuits an associated control column position signal, and d) a mechanism for controlling displacement of said controlled members as a function of signals supplied by said control column position sensors, wherein each control column is further provided with a mechanical spring system comprising for each of said degrees of freedom a return spring assembly for spring-loading the associated control column into its neutral position and adapted to provide, in the event of manipulation of the corresponding control column, a resisting torque in support of the resisting torque supplied by the associated actuator.

15. The system according to claim 14, wherein, said aircraft being equipped with an automatic pilot installation, each of said control circuits comprises a switching mechanism for selectively applying to said control circuits either said control column position signal or an output signal of said automatic pilot installation.