ELECTRONIC CONTROL DEVICE FOR A PILOTING MEMBER WITH MULTIFUNCTIONAL MICROCONTROLLERS, PILOTING DEVICE AND AIRCRAFT

• US 20110112705A1
• Filed: 11/08/2010
• Published: 05/12/2011
• Est. Priority Date: 11/06/2009
• Status: Abandoned Application

• Current Assignee: Ratier Figeac (Rtx Corporation)
• Original Assignee: Ratier Figeac (Rtx Corporation)
• Inventors: ANTRAYGUE, Cédric
• Application Number:
  US12/941,346
• Publication Number:
  US 20110112705A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

An electronic control device for an aircraft piloting member mounted on an electromechanical supporting box (23, 24) includes at least one actuating motor on at least one degree of freedom, and sensors associated with the piloting member to detect at least the position thereof on each degree of freedom. A command/monitoring unit (47, 48) of the piloting member has at least one electronic microcontroller (52 to 55) adapted to:

• • command at least one motor on one degree of freedom,
  • receive signals of sensors (83, 93) on another degree of freedom,
  • carry out monitoring of the signals to detect any deviation thereof. A piloting device and an aircraft including such an electronic control device are also disclosed.

Claims

1. Electronic control device for an aircraft piloting member, called the controlled piloting member, connected to at least one flying member of the aircraft, said controlled piloting member being mounted and guided on an electromechanical supporting box on at least one degree of freedom, said electro-mechanical supporting box comprising:

for each degree of freedom of the controlled piloting member with respect to said electromechanical supporting box, at least one motor for actuating the controlled piloting member on said degree of freedom,

sensors associated with the controlled piloting member to detect at least the position thereof on said at least one degree of freedom,

characterised in that it comprises a command/monitoring unit of the controlled piloting member, in that said command/monitoring unit comprises at least one electronic microcontroller, and in that each of said at least one electronic microcontroller is adapted to;

deliver command signals for at least one actuating motor on one degree of freedom, called commanded degree of freedom of the controlled piloting member,

receive signals, called monitored signals, delivered by sensors chosen from

sensors associated with at least a second degree of freedom, called the monitored degree of freedom, of the controlled piloting member, said monitored degree of freedom of the controlled piloting member being distinct from said commanded degree of freedom,

and sensors associated with at least one monitored degree of freedom of another piloting member distinct from said controlled piloting member, said monitored degree of freedom of said another piloting member being distinct from said commanded degree of freedom of the controlled piloting member,

carry out a monitoring digital processing of said monitored signals, said monitoring digital processing being adapted to detect any deviation of said monitored signals corresponding to an operating fault and to generate a signal representing such an operating fault.

2. Device according to claim 1, characterised in that said electromechanical supporting box comprises force sensors associated with the controlled piloting member to detect the forces imparted thereto on each commanded degree of freedom, and in that said command/monitoring unit comprises inputs for receiving the signals delivered by said force sensors, and each of said at least one electronic microcontroller is adapted to receive said signals, and to deliver command signals for at least one actuating motor so as to create an electrically simulated variable force feedback sensation in the piloting member.

3. Device according to claim 1, characterised in that the controlled piloting member belongs to a piloting device comprising said controlled piloting member and another piloting member, called the other piloting member, both piloting members being connected to at least one same flying member of the aircraft, and in that said command/monitoring unit of the controlled piloting member comprises:

inputs, called cross-monitoring inputs, for receiving monitored signals, said cross-monitored signals, delivered by sensors associated with said other piloting member,

for each degree of freedom, at least one electronic microcontroller receiving said cross-monitored signals received at the cross-monitoring inputs, and said microcontroller being adapted to deliver command signals for at least one actuating motor on said commanded degree of freedom of the controlled piloting member so as to carry out electronic servo coupling of the two piloting members.

4. Device according to claim 1, characterised in that the controlled piloting member belongs to a piloting device comprising said piloting members being mounted on two respective electromechanical boxes with the same degrees of freedom and both connected to at least one same flying member of the aircraft, and in that said command/monitoring unit comprises:

for each of said monitored degree of freedom of the controlled piloting member, an electronic microcontroller, called main monitoring microcontroller, for digital processing of said monitored signals delivered by sensors associated with the controlled piloting member, and adapted to detect any deviation of these signals corresponding to an operating fault and to generate a signal representing such an operating fault,

inputs, called cross-monitoring inputs, for receiving monitored signals, said cross-monitored signals, delivered by sensors associated with said other piloting member,

for each monitored degree of freedom of said other piloting member, one and only one electronic microcontroller, called the cross-monitoring microcontroller, specific to this degree of freedom, said cross-monitoring microcontroller being adapted to carry out digital processing of said cross-monitored signals received at said cross-monitoring inputs, and to detect any deviation of these signals corresponding to a fault and to generate a signal representing such an operating fault.

5. Device according to claim 3, characterised in that said cross-monitoring inputs comprise at least one input for receiving at least one cross-monitored position signal of said other piloting member, delivered by a position sensor associated with said other piloting member.

6. Device according to claim 5, characterised in that said cross-monitoring inputs comprise at least one input for receiving at least one cross-monitored force signal representing forces actually exerted on the other piloting member, delivered by at least one force sensor associated with said other piloting member, and in that, for each degree of freedom, said cross-monitoring electronic microcontroller is adapted to compare a value, called the force measured value, determined at least from said cross-monitored force signal, with a reference value calculated according to a predetermined law from at least one position signal of said other piloting member.

7. Device according to claim 6, characterised in that said cross-monitoring electronic microcontroller is adapted to compare the difference between said force measured value and said reference value with a predetermined threshold value, and to generate a signal representing a fault when this difference exceeds said predetermined threshold value.

8. Device according to claim 1, characterised in that the controlled piloting member belongs to a piloting device comprising, said piloting member being mounted on two respective electromechanical boxes with the two same degrees of freedom and both connected to at least one same flying member of the aircraft, said command/monitoring unit comprises:

a first electronic microcontroller having the functions;

of delivering master command signals for a first actuating motor on a first degree of freedom of the controlled piloting member,

of delivering slave command signals for a first actuating motor on a second degree of freedom of the controlled piloting member,

of carrying out main monitoring of the controlled piloting member on the second degree of freedom,

of carrying out cross-monitoring of the other piloting member on one of the two degrees of freedom, in particular the second degree of freedom,

a second electronic microcontroller having the functions;

of delivering master command signals for a second actuating motor on a second degree of freedom of the controlled piloting member,

of delivering slave command signals for a second actuating motor on the first degree of freedom of the controlled piloting member,

of carrying out main monitoring of the controlled piloting member on the first degree of freedom,

of carrying out cross-monitoring of the other piloting member on the other of the two degrees of freedom, in particular the first degree of freedom.

9. Device according to claim 1, characterised in that said command/monitoring unit is encapsulated in a box which can be mounted on the electromechanical supporting box of the controlled piloting member.

10. Piloting device of an aircraft comprising at least one piloting member connected to at least one flying member of the aircraft, characterised in that it comprises an electronic control device according to claim 1 for a piloting member.

11. Piloting device according to claim 10 comprising two piloting members both connected to at least one same flying member of the aircraft, characterised in that it comprises, for each piloting member, an electronic control device specific to each piloting member.

12. Piloting device according to claim 11, characterised in that the two electronic control devices are identical.

13. Aircraft characterised in that it comprises at least one piloting device according to claim 10.