Tactile cueing apparatus

Patent metadata

Field	Value
Publication number	US-9381998-B2
Application number	US-201013502213-A
Country	US
Kind code	B2
Filing date	Oct 8, 2010
Priority date	Oct 19, 2009
Publication date	Jul 5, 2016
Grant date	Jul 5, 2016

Abstract

A tactile cueing apparatus for incorporation in an aircraft flight control system comprising a flight control surface, and a pilots inceptor ( 12 ) for moving the surface via a servo-assisted mechanical linkage ( 28 ) connecting the inceptor to the control surface, the apparatus comprising a force sensor for sensing a force applied to the inceptor by the pilot to move the control surface, an electromechanical actuator ( 34 ) configured to be installed with the mechanical linkage between the inceptor and means in the system providing said servo-assistance, and control means programmed to cause the actuator (i) to move so that the linkage moves to a position determined by said force according to a predetermined relationship, (ii) to apply to the inceptor a resisting force according to a predetermined relationship and which when the linkage has moved to its commanded position is equal and opposite to the force sensed by the force sensor.

First claim

The invention claimed is:

1. A tactile cueing apparatus to augment an aircraft control system, the aircraft control system comprising a controlled element and an operator's inceptor for moving the controlled element via a mechanical linkage connected to the inceptor and linked to the controlled element, wherein the tactile cueing apparatus comprises:
a force sensor for sensing a control input to the inceptor by the operator to move the mechanical linkage, the force sensor providing an output;
a controllable actuator arranged to be configured to move the mechanical linkage;
a position sensor for sensing a position of the mechanical linkage, the position sensor providing an output; and
control means programmed to cause the actuator, based upon a predetermined force-position relationship that defines a required effect upon the position of the mechanical linkage for a given combination of a force as sensed by the force sensor and a generated resisting force, to:
(i) move the mechanical linkage to a position determined by the output of the force sensor and the force-position relationship, wherein the actuator moves the mechanical linkage when the output of the position sensor does not conform to a given position indicated by the force-position relationship at a given input force applied to the inceptor; and
(ii) apply to the inceptor the generated resisting force determined by the output of the position sensor and the force-position relationship wherein the generated resisting force is equal and opposite to the force applied to the inceptor by the operator when the mechanical linkage has moved to a position determined by the force sensor output according to the force-position relationship.

2. The apparatus of claim 1 wherein the force-position relationship comprises a non-linear relationship between the generated resisting force and the inceptor position.

3. The apparatus of claim 2 , wherein the force-position relationship comprises at least one range of force values in which a change in the force produces no movement of the mechanical linkage.

4. The apparatus of claim 1 wherein the control means is programmed to change the force-position relationship with a change in the aircraft's flight conditions.

5. The apparatus of claim 1 wherein the actuator is a rotary actuator.

6. The apparatus of claim 1 further comprising a clutch or other disengaging means operable in the event of failure of the apparatus for disengaging the apparatus from the mechanical linkage.

7. The apparatus of claim 6 in which the disengaging means when operative applies a passive resisting force to the inceptor against movement thereof.

8. The apparatus of claim 1 wherein the controlled element is a flight control surface.

9. An aircraft provided with the tactile cueing apparatus of claim 1 .

10. The apparatus of claim 1 , wherein the control means is further programmed to cause the actuator to permit the mechanical linkage to move to a position determined by the control input according to the force-position relationship.

11. The apparatus of claim 1 , wherein the apparatus is configured to be retrofit into the aircraft such that the mechanical linkage between the inceptor and the controlled element remains undisturbed.

12. A tactile cueing system comprising a plurality of tactile cueing apparatus to augment an aircraft control system, the aircraft control system comprising a plurality of controlled elements and an operator's inceptor for moving each controlled element via a respective mechanical linkage connected to the inceptor and linked to the respective controlled element, wherein each of the plurality of tactile cueing apparatus comprises:
a force sensor for sensing a control input to the inceptor by the operator to move the respective mechanical linkage, the force sensor providing an output;
a controllable actuator arranged to be configured to move the respective mechanical linkage;
a position sensor for sensing a position of the respective mechanical linkage, the position sensor providing an output; and
control means programmed to cause the actuator, based upon a respective predetermined force-position relationship that defines a required effect upon the position of the respective mechanical linkage for a given combination of a force as sensed by the force sensor and a generated resisting force, to:
(i) move the respective mechanical linkage to a position determined by the output of the force sensor and the respective force-position relationship, wherein the actuator moves the respective mechanical linkage when the output of the position sensor does not conform to a given position indicated by the respective force-position relationship at a given input force applied to the inceptor; and
(ii) apply to the inceptor the generated resisting force determined by the output of the position sensor and the respective force-position relationship; wherein the generated resisting force is equal and opposite to the force applied to the inceptor by the operator when the respective mechanical linkage has moved to a position determined by the force sensor output according to the respective force-position relationship;
each tactile cueing apparatus configured to be installed to move the respective mechanical linkage, a said control means of a first said apparatus being arranged to monitor the operation of a said control means of a second said apparatus.

13. The system of claim 12 further comprising feedback means for supplying a feedback signal indicative of a respective mechanical linkage position controlled by the second said apparatus to the control means of the first said apparatus and thence to the control means of the second said apparatus.

14. The system of claim 12 wherein a said actuator is arranged to be controlled in parallel by two said control means.

15. An aircraft provided with the tactile cueing system of claim 12 .

16. The system of claim 12 , wherein each control means is further programmed to cause the respective actuator to permit the respective mechanical linkage to move to a position determined by the control input according to the respective force-position relationship.

17. The system of claim 12 , wherein the system is configured to be retrofit into the aircraft such that each respective mechanical linkage between the inceptor and each respective controlled element remains undisturbed.

Assignees

• Taylor Adam
• Bae Systems Plc

Inventors

• Taylor Adam

Classifications

• B64C13/46 Primary

  with artificial feel · CPC title

• B64C13/10 Primary

  comprising warning devices · CPC title