Tilting stick control device, especially for an aircraft, and system comprising two such devices

• US 5,125,602 A
• Filed: 02/20/1990
• Issued: 06/30/1992
• Est. Priority Date: 02/20/1989
• Status: Expired due to Term

• Current Assignee: Airbus France
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Vauvelle, Bernard
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Mojica, Virna Lissi
• Application Number:
  US07/481,245
• Time in Patent Office: 861 Days
• Field of Search: 244/75 R, 244/76 A, 244/175, 244/220, 244/221, 244/223, 244/228, 244/229, 244/236, 244/237, 74/471
• US Class Current: 244/223
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: B64C 13/12 Dual control apparatus
• CPC Class Codes: G05G 2009/04718 with cardan or gimbal type joint
• CPC Class Codes: G05G 2009/04748 Position sensor for rotary movement, e.g. potentiometer
• CPC Class Codes: G05G 2009/04766 providing feel, e.g. indexing means, means to create counterforce
• CPC Class Codes: G05G 2009/04774 with additional switches or sensors on the handle
• CPC Class Codes: G05G 9/047 the controlling member being movable by hand about orthogonal axes, e.g. joysticks for switches H01H25/04
• CPC Class Codes: H01H 2003/008 with a haptic or a tactile feedback controlled by electrical means, e.g. a motor or magnetofriction

Abstract

Device for the control of the elements of a machine having a stick (6,7) designed to be activated by one hand of an operator and mounted tilting around at least one axis (X--X) transverse to the stick. The stick is associated with at least one position sensor (17) which deliver an electric signal representing the tilting of the stick around said axis on both sides of a neutral position, the electric signal controlling at least one of the elements of the machine by a calculation device (30). The device also includes at least one torque motor (12,13) associated to said axis (X--X) so that the tilting of the stick (6,70 drives a relative rotation between the rotor and the stator of the torque motor and in that the torque motor is fed by the calculation device (30).

Claims

1. System for piloting an aircraft, comprising:

(a) a control stick designed to be activated by the single hand of a pilot and mounted tilting around two crosswise axes transverse to said control stick;

(b) position sensors provided to deliver electric signals respectively representative of the tilting of said control stick around said axes on both sides of a neutral position;

(c) calculation means receiving said electric signals and controlling accordingly the aerodynamical surfaces of said aircraft; and

(d) torque motors arranged such that the tilting of said control stick around each of said axes drives a relative rotation between the rotor and the stator of the corresponding torque motor, said torque motors respectively receiving electric signals from said calculation means dependent upon the relative rotation of said rotor and stator.

2. Device according to claim 1, wherein said torque motors are samarium-cobalt permanent magnet type torque motors.

3. System according to claim 1, further comprising:

(e) an auxiliary control stick designed to be activated by the single hand of a copilot and mounted tilting around a second set of crosswise axes transverse to said control auxiliary stick;

(f) auxiliary position sensors provided to deliver a second set of electric signals respectively representative of the tilting of said auxiliary control stick around said second pair of axes on both sides of a neutral position; and

(g) said control stick and said control auxiliary stick being arranged such that when one the control sticks is hand activated and the other one is free, said calculation means delivers said electric signals to said free control stick so that said free control stick recopies the position of said hand activated control stick.

4. System according to claim 1, wherein the delivering of said electric signals to said torque motors by said calculation means simulates a viscous damping.

5. System according to claim 1 comprising an automatic pilot, wherein said calculation means delivers said electric signals to the torque motors so that the position of said stick corresponds with the activator signals given by said automatic pilot to said aerodynamical surfaces.

6. System according to claim 1, wherein the delivering of electric signals to the torque motors by said calculations means is alternative so as to cause said control stick to vibrate.

7. System for piloting an aircraft, comprising:

(a) a control stick designed to be tilted by a single hand of a pilot and mounted to be tiltable around two crosswise axes transverse to said control stick;

(b) position sensors for delivering electric signals respectively representative of the tilting of said control stick around said axes on both sides of a neutral position;

(c) calculation means for receiving said electric signals and controlling accordingly the aerodynamical surfaces of said aircraft; and

(d) torque motors arranged such that the tilting of said control stick around each of said axes drives a relative rotation between the rotor and the stator of the corresponding torque motor, said torque motors being respectively controlled by said calculation means so that the movement of said torque motors is in direct reaction to said electric signals, whereby said torque motors produce a mechanical effect upon the motion of said control stick.

8. System according to claim 7, wherein said mechanical effect causes a viscous damping upon the motion of said control stick.

9. System according to claim 7, wherein said mechanical effect causes a vibration of said control stick.