Method of driving a main rotor of a rotorcraft in the context of simulating a failure of one of the engines of the rotorcraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G09B-009/08
G09B-009/46
출원번호
US-0247459
(2014-04-08)
등록번호
US-9542855
(2017-01-10)
우선권정보
FR-13 00811 (2013-04-09)
발명자
/ 주소
Dumur, Guillaume
Rossotto, Regis
Vieira, Hilario
출원인 / 주소
AIRBUS HELICOPTERS
대리인 / 주소
Brooks Kushman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined
A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch maneuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.
대표청구항▼
1. A method of driving rotation of at least one main rotor of a rotorcraft fitted with a power plant comprising a plurality of engines, the method implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft in order to train a pilot of the rotorcraft for
1. A method of driving rotation of at least one main rotor of a rotorcraft fitted with a power plant comprising a plurality of engines, the method implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft in order to train a pilot of the rotorcraft for such a failure, in which simulation mode: at least two engines together deliver power in order to drive the main rotor at a setpoint speed of rotation, the power being shared evenly between the engines, that are all kept in synchronous engagement on a power transmission train interposed between the power plant and the main rotor;each of the at least two engines operating on the basis of a first setpoint that is predefined depending on a value of a second setpoint selected by a trainer from a plurality of second setpoints, each second setpoint defining a power that the engines are authorized to deliver for a given period when not in simulation mode in the event of a real failure of an engine, the first setpoint value corresponding to the second setpoint value that defines it being shared evenly between the engines that are all kept in synchronous engagement on said power transmission train in order to drive the main rotor in rotation in simulation mode; anda current speed of rotation of the main rotor detected as being lower than a predetermined threshold speed of rotation, spontaneously giving rise to an operation being performed whereby the engines deliver additional power within a limit imposed by a third setpoint;wherein the operation of delivering additional power is performed by actively maintaining the simulation mode and by generating a regulation command giving rise to a controlled operation of gradually increasing the power delivered by the engines by authorizing the limit imposed by the first setpoint to be exceeded, the controlled operation of gradually increasing the power being interrupted at a current power level at which the power delivered by the engines drives the main rotor at a speed of rotation that is greater than or equal to the predetermined threshold speed of rotation as a consequence of the pilot under training in simulation mode causing blades of the main rotor to perform a collective pitch maneuver, wherein, for any one of the first setpoints implemented in simulation mode, a value of the third setpoint is a value of any one of the second setpoints. 2. A method according to claim 1, wherein, for any one of the first setpoints implemented in simulation mode, the value of the third setpoint is the value of the second setpoint defining the value of the first setpoint implemented in simulation mode. 3. A method according to claim 1, wherein the current power level is maintained after the controlled operation of gradually increasing the power has been interrupted. 4. A method according to claim 1, wherein the controlled operation of gradually increasing the power is engaged using power variation that is linear. 5. A method according to claim 1, wherein the controlled operation of gradually increasing the power is engaged using variation in the power increase that is gradual. 6. A method according to claim 1, wherein the controlled operation of gradually increasing the power is engaged by issuing a first request relating to a gradual increase of the first setpoint until the at least one main rotor reaches a speed of rotation that is not greater than the setpoint speed of rotation. 7. A method according to claim 1, wherein the controlled operation of gradually increasing the power is engaged by issuing a second request relating to a predefined speed of rotation for driving the main rotor, the value of the predefined speed of rotation being less than the value of the setpoint speed of rotation and being greater than the value of the predetermined threshold speed of rotation. 8. A method according to claim 1, wherein the method includes an operation of displaying at least: first information relating to the current speed of rotation at which the main rotor is being driven; andsecond information relating to exceeding the value of the first setpoint. 9. A method of driving rotation of at least one main rotor of a rotorcraft fitted with a power plant comprising a plurality of engines, the method implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft in order to train a pilot of the rotorcraft for such a failure, in which simulation mode: at least two engines together deliver power in order to drive the main rotor at a setpoint speed of rotation, the power being shared evenly between the engines, that are all kept in synchronous engagement on a power transmission train interposed between the power plant and the main rotor;each of the at least two engines operating on the basis of a first setpoint that is predefined depending on a value of a second setpoint selected by a trainer from a plurality of second setpoints, each second setpoint defining a power that the engines are authorized to deliver for a given period when not in simulation mode in the event of a real failure of an engine, the first setpoint value corresponding to the second setpoint value that defines it being shared evenly between the engines that are all kept in synchronous engagement on said power transmission train in order to drive the main rotor in rotation in simulation mode; anda current speed of rotation of the main rotor detected as being lower than a predetermined threshold speed of rotation, spontaneously giving rise to an operation being performed whereby the engines deliver additional power within a limit imposed by a third setpoint;wherein the operation of delivering additional power is performed by actively maintaining the simulation mode and by generating a regulation command giving rise to a controlled operation of gradually increasing the power delivered by the engines by authorizing the limit imposed by the first setpoint to be exceeded, the controlled operation of gradually increasing the power being interrupted at a current power level at which the power delivered by the engines drives the main rotor at a speed of rotation that is greater than or equal to the predetermined threshold speed of rotation as a consequence of the pilot under training in simulation mode causing blades of the main rotor to perform a collective pitch maneuver;wherein the controlled operation of gradually increasing the power is engaged by issuing a second request relating to a predefined speed of rotation for driving the main rotor, the value of the predefined speed of rotation being less than the value of the setpoint speed of rotation and being greater than the value of the predetermined threshold speed of rotation. 10. A method according to claim 9, wherein, for any one of the first setpoints implemented in simulation mode, the value of the third setpoint is the value of the second setpoint defining the value of the first setpoint implemented in simulation mode. 11. A method according to claim 9, wherein the current power level is maintained after the controlled operation of gradually increasing the power has been interrupted. 12. A method according to claim 9, wherein the controlled operation of gradually increasing the power is engaged using variation in the power increase that is gradual. 13. A method according to claim 9, wherein the controlled operation of gradually increasing the power is engaged by issuing a first request relating to a gradual increase of the first setpoint until the at least one main rotor reaches a speed of rotation that is not greater than the setpoint speed of rotation. 14. A method according to claim 9, wherein the method includes an operation of displaying at least: first information relating to the current speed of rotation at which the main rotor is being driven; andsecond information relating to exceeding the value of the first setpoint. 15. A method of driving rotation of at least one main rotor of a rotorcraft fitted with a power plant comprising a plurality of engines, the method implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft in order to train a pilot of the rotorcraft for such a failure, in which simulation mode: at least two engines together deliver power in order to drive the main rotor at a setpoint speed of rotation, the power being shared evenly between the engines, that are all kept in synchronous engagement on a power transmission train interposed between the power plant and the main rotor;each of the at least two engines operating on the basis of a first setpoint that is predefined depending on a value of a second setpoint selected by a trainer from a plurality of second setpoints, each second setpoint defining a power that the engines are authorized to deliver for a given period when not in simulation mode in the event of a real failure of an engine, the first setpoint value corresponding to the second setpoint value that defines it being shared evenly between the engines that are all kept in synchronous engagement on said power transmission train in order to drive the main rotor in rotation in simulation mode; anda current speed of rotation of the main rotor detected as being lower than a predetermined threshold speed of rotation, spontaneously giving rise to an operation being performed whereby the engines deliver additional power within a limit imposed by a third setpoint;wherein the operation of delivering additional power is performed by actively maintaining the simulation mode and by generating a regulation command giving rise to a controlled operation of gradually increasing the power delivered by the engines by authorizing the limit imposed by the first setpoint to be exceeded, the controlled operation of gradually increasing the power being interrupted at a current power level at which the power delivered by the engines drives the main rotor at a speed of rotation that is greater than or equal to the predetermined threshold speed of rotation as a consequence of the pilot under training in simulation mode causing blades of the main rotor to perform a collective pitch maneuver;wherein the method includes an operation of displaying at least:first information relating to the current speed of rotation at which the main rotor is being driven; andsecond information relating to exceeding the value of the first setpoint. 16. A method according to claim 15, wherein, for any one of the first setpoints implemented in simulation mode, the value of the third setpoint is the value of the second setpoint defining the value of the first setpoint implemented in simulation mode. 17. A method according to claim 15, wherein the current power level is maintained after the controlled operation of gradually increasing the power has been interrupted. 18. A method according to claim 15, wherein the controlled operation of gradually increasing the power is engaged using power variation that is linear. 19. A method according to claim 15, wherein the controlled operation of gradually increasing the power is engaged using variation in the power increase that is gradual. 20. A method according to claim 1, wherein the controlled operation of gradually increasing the power is engaged by issuing a first request relating to a gradual increase of the first setpoint until the at least one main rotor reaches a speed of rotation that is not greater than the setpoint speed of rotation.
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이 특허에 인용된 특허 (7)
Rice Robert W. (Sandy Hook CT) Sweet David H. (Tequesta FL), Engine failure monitor for a multi-engine aircraft having partial engine failure and driveshaft failure detection.
Evans Charles W. ; Jenson David L. ; Kronsnoble John M. ; Greenberg Charles E., Monitoring and/or control system for a dual-engine helicopter for one engine inoperative flight operations.
Evans Charles W. ; Saal ; Jr. Karl W. ; Cole Jeffrey L., System and method for conducting one engine inoperative flight procedures training in a dual-engine helicopter.
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