Rudder bar system with force gradient for a helicopter

• US 5,738,310 A
• Filed: 12/22/1995
• Issued: 04/14/1998
• Est. Priority Date: 12/22/1994
• Status: Expired due to Term

• Current Assignee: Societe Anonyme DITE Eurocopter France
• Original Assignee: Eurocopter France
• Inventors: Bellera, Jacques Serge Louis, Rollet, Philippe Alain Jean
• Primary Examiner(s): GRANT, WILLIAM ALEXANDER
• Application Number:
  US08/577,131
• Time in Patent Office: 844 Days
• Field of Search: 244/76 R, 244/175, 244/181, 244/194, 244/195, 244/196, 244/221, 244/223, 244/234, 244/235, 318/586, 318/628
• US Class Current: 244/195
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

A rudder bar system for a helicopter controlled in yaw by acting on the tail rotor or an equivalent device has a capability, as a function of the parameters representative of the current flight status of the helicopter, of either automatically continuously recentering the forces on the rudder bar, which cancels out the residual static forces and gives the pilot a tactile sensation close to that given by a friction-type rudder bar, or allowing the pilot fully to feel the countering action of an elastic return device such as a spring.

Claims

1. A rudder bar system for a helicopter which has a yaw axis, the helicopter comprising a control device on the yaw axis for piloting the helicopter in yaw and sensor means for continuously delivering parameters representative of a current flight status of said helicopter, said system comprising:

a rudder bar, receiving an actuation from a pilot, for controlling said control device on the yaw axis to pilot the helicopter in said yaw;

elastic means for exerting an actuation on the rudder bar counter to the actuation exerted by said pilot on said rudder bar;

a movable member attached to the elastic means at an attachment point;

a motor for displacing the movable member;

first position sensing means for sensing a position of the rudder bar and for outputting a first electrical signal indicating the position of the rudder bar;

second position sensing means for sensing a position of the attachment point and for outputting a second electrical signal indicating the position of the attachment point;

difference calculating means for calculating a difference between the first electrical signal and the second electrical signal;

link means for supplying a signal representing said difference to said motor to control the motor to displace the movable member to cancel out the actuation exerted on the rudder bar by the elastic means;

a first controllable switch for selectively opening and closing so as to prevent said link means from supplying the signal representing the difference to the motor when the first controllable switch is open and to allow said link means to supply the signal representing the difference to the motor when the first controllable switch is closed; and

switch controlling means, receiving the parameters representative of the current flight status from said sensor means, for controlling the first controllable switch to open or close in accordance with the parameters.

2. The rudder bar system as claimed in claim 1,

wherein the difference calculating means comprises a subtractor for forming the difference between said first and second electrical signals to form said signal representing said difference;

and

wherein said link means comprises means for receiving said signal representing said difference from the subtractor and for supplying said signal representing said difference to said motor.

3. The rudder bar system as claimed in claim 1, wherein said link means comprises adjustment means for adjusting said signal representing said difference to adjust a tactile sensation felt by the pilot actuating said rudder bar.

4. The rudder bar system as claimed in claim 1, wherein:

said parameters representative of the current flight status of said helicopter comprise at least an air speed, a yaw angular speed and a lateral acceleration; and

said switch controlling means comprises;

comparison means for continuously comparing the air speed, the yaw angular speed and the lateral acceleration with a reference threshold air speed, a reference threshold angular speed and a reference threshold lateral acceleration, respectively; and

switch actuating means for actuating said first controllable switch

(i) to close when, with the air speed being below the reference threshold air speed, the yaw angular speed is below the reference threshold angular speed, or when, with the air speed being above the reference threshold air speed, the lateral acceleration is below the reference threshold lateral acceleration; and

(ii) to open when, with the air speed being below the reference threshold air speed, the yaw angular speed is above the threshold angular speed, or when, with the air speed being above the reference threshold air speed, the lateral acceleration is above the reference threshold lateral acceleration.

5. The rudder bar system as claimed in claim 4, wherein the comparison means comprises:

a first comparator for comparing the air speed with the reference threshold air speed and outputting a first comparison result;

a second comparator for comparing the yaw angular speed with the reference threshold angular speed and outputting a second comparison result; and

a third comparator for comparing the lateral acceleration with the reference threshold lateral acceleration and outputting a third comparison result.

6. The rudder bar system as claimed in claim 5, wherein said switch actuating means comprises a first two-channel router for routing, in accordance with said first comparison result, one of the second comparison result and the third comparison result to said first controllable switch as a control signal for said first controllable switch.

7. The rudder bar system as claimed in claim 1, wherein:

the helicopter comprises fly-by-wire means, receiving the parameters from the sensor means, for piloting the helicopter by controlling at least the control device on the yaw axis; and

said rudder bar system is at least partly integrated into said fly-by-wire means.

8. The rudder bar system as claimed in claim 7, wherein:

said fly-by-wire means comprises automatic piloting means for providing automatic hold of said helicopter in said yaw; and

the rudder bar system further comprises;

a detector for detecting whether said helicopter is being piloted in said yaw by the pilot or by the automatic piloting means; and

a second two-channel router, interposed between said first switch and said motor, for selectively connecting either said link means or said automatic piloting means to said motor in accordance with a detection result of said detector.

9. The rudder bar system as claimed in claim 8, wherein said detector comprises:

difference comparison means for continuously comparing said difference between said first and second electrical signals with a reference threshold difference to produce a difference comparison result; and

means for controlling said second two-channel router in accordance with the difference comparison result (i) to connect said link means to said motor when said difference between said first and second electrical signals is above said reference threshold difference and (ii) to connect said automatic piloting means to said motor when said difference between said first and second electrical signals is below said reference threshold difference.

10. The rudder bar system as claimed in claim 1, further comprising:

displacement comparison means for comparing said second electrical signal with at least one reference threshold displacement signal representative of at least one position of an end stop of the rudder bar and outputting a displacement comparison result; and

a second controllable switch, interposed between said first controllable switch and said motor and receiving said displacement comparison result, for opening to prevent the signal representing the difference from reaching the motor when the second electrical signal reaches said reference threshold displacement signal.

11. The rudder bar system as claimed in claim 1, wherein the switch controlling means comprises means for controlling the first controllable switch (i) to close when the parameters are less than reference thresholds and (ii) to open when the parameters are greater than the reference thresholds.