Control system and method for an aircraft

Patent metadata

Field	Value
Publication number	US-9994303-B2
Application number	US-201514808453-A
Country	US
Kind code	B2
Filing date	Jul 24, 2015
Priority date	Jul 25, 2014
Publication date	Jun 12, 2018
Grant date	Jun 12, 2018

Abstract

A control system and method for an aircraft configured to operate according to a first mode of operation corresponding to an automatic piloting of the aircraft and a second mode of operation corresponding to a manual piloting of the aircraft, the system including a selection member. The system is configured to operate according to the first mode of operation when the selection member is not actuated continuously and to operate according to the second mode of operation when the selection member is actuated continuously.

First claim

The invention claimed is:

1. A control system for an aircraft configured to operate according to a first mode of operation corresponding to an automatic piloting of the aircraft and a second mode of operation corresponding to a manual piloting of the aircraft, the control system comprising a selection member that is configured to be actuated by a pilot of the aircraft,
wherein the control system is configured to operate according to the first mode of operation when the selection member is not actuated continuously;
wherein the control system is configured to operate according to the second mode of operation when the selection member is actuated continuously;
wherein the control system is configured to control attitude or roll angles of the aircraft or control both attitude and roll angles of the aircraft; and
wherein the control system is further configured such that, upon switching from the first mode of operation to the second mode of operation because of an actuation of the selection member, the control system continues to control attitude or roll angles of the aircraft, or control both attitude and roll angles of the aircraft, that are unchanged until the control system receives a control signal originating from a control member of the aircraft and corresponding to a modification of a value of at least one of the attitude or roll angles.

2. The control system as claimed in claim 1 , configured such that, when the control system operates according to the first mode of operation, the control system enables a display of a flight director on a screen of a cockpit of the aircraft and, when the control system operates according to the second mode of operation, the control system disables the display of the flight director.

3. The control system as claimed in claim 1 , configured to display information on a screen of a cockpit of the aircraft when the control system operates according to the second mode of operation, the information corresponding to a guidance of the aircraft which would be produced by the control system if the control system were to revert to the first mode of operation because the actuation of the selection member was stopped.

4. The control system as claimed in claim 1 , configured to store at least one current guidance objective upon switching from the first mode of operation to the second mode of operation because of an actuation of the selection member, then to guide the aircraft according to the this at least one stored guidance objective, following a return to the first mode of operation because the actuation of the selection member was stopped.

5. The control system as claimed in claim 4 , wherein the guidance objective corresponds to at least one guidance mode or to guidance setpoints previously selected by a pilot of the aircraft.

6. The control system as claimed in claim 1 , further comprising an objective selector configured to be activated by a pilot of the aircraft, the control system being further configured to store at least one current guidance objective upon switching from the first mode of operation to the second mode of operation because of an actuation of the selection member, then upon a return to the first mode of operation because the actuation of the selection member was stopped, to guide the aircraft according to:
a trajectory corresponding to a current trajectory of the aircraft upon the return to the first mode of operation, as long as the objective selector is not activated after this return to the first mode of operation; and
the at least one stored guidance objective, after an activation of the objective selector after the return to the first mode of operation.

7. An aircraft comprising a control system, the control system comprising:
a first mode of operation corresponding to an automatic piloting of the aircraft;
a second mode of operation corresponding to a manual piloting of the aircraft; and
a selection member that is configured to be actuated by a pilot of the aircraft;
wherein the control system is configured to operate according to the first mode of operation when the selection member is not actuated continuously;
wherein the control system is configured to operate according to the second mode of operation when the selection member is actuated continuously;
wherein the control system is configured to control attitude or roll angles of the aircraft or control both attitude and roll angles of the aircraft; and
wherein the control system is further configured such that, upon switching from the first mode of operation to the second mode of operation because of an actuation of the selection member, the control system continues to control attitude or roll angles of the aircraft, or control both attitude and roll angles of the aircraft, that are unchanged until the control system receives a control signal originating from a control member of the aircraft and corresponding to a modification of a value of at least one of the attitude or roll angles.

8. A method for controlling an aircraft, the method comprising:
operating a control system onboard the aircraft according to a first mode of operation corresponding to an automatic piloting of the aircraft; and
operating the control system onboard the aircraft according to a second mode of operation corresponding to a manual piloting of the aircraft, the control system comprising a selection member that is actuated by a pilot of the aircraft;
wherein when the selection member is not actuated continuously, the control system operates according to the first mode of operation;
wherein when the selection member is actuated continuously, the control system operates according to the second mode of operation;
wherein the control system is configured to control attitude or roll angles of the aircraft or control both attitude and roll angles of the aircraft; and
wherein the control system is further configured such that, upon switching from the first mode of operation to the second mode of operation because of an actuation of the selection member, the control system continues to control attitude or roll angles of the aircraft, or control both attitude and roll angles of the aircraft, that are unchanged until the control system receives a control signal originating from a control member of the aircraft and corresponding to a modification of a value of at least one of the attitude or roll angles.

9. The control system as claimed in claim 4 , wherein the guidance objective corresponds to at least one guidance mode and to guidance setpoints previously selected by a pilot of the aircraft.

Assignees

• Airbus Operations Sas

Inventors

• Scacchi Pierre
• Bourret Thierry
• Laine Franck
• Mayolle Matthieu
• Betton Sabrina
• Puissacq Cécile
• Sapin Olivier

Classifications

• B64C13/22 Primary

  readily revertible to personal control · CPC title

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• B64C13/0421

  control sticks for primary flight controls · CPC title

• B64C13/18

  using automatic pilot · CPC title

• B64C13/042

  operated by hand · CPC title