Device and a method of controlling engagement between the engine and a main power transmission gearbox of an aircraft

Patent metadata

Field	Value
Publication number	US-10106271-B2
Application number	US-201715434296-A
Country	US
Kind code	B2
Filing date	Feb 16, 2017
Priority date	Feb 18, 2016
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.

First claim

What is claimed is:

1. A control method for controlling a coupling mechanism between an engine and a main mechanical power transmission gearbox MGB for an aircraft, the coupling mechanism enabling an outlet shaft of the engine to be engaged with an inlet shaft of the MGB, wherein the control method comprises the following steps:
determining the state of an engine including taking a first measurement giving the speed of rotation of the engine;
determining a “ready to engage” state for the coupling mechanism associated with the engine;
engaging the coupling mechanism associated with the engine;
determining a maximum torque acceptable by the MGB; and
regulating the engine so that the speed of rotation of the engine is regulated on a setpoint speed of rotation for the engine, while controlling the torque delivered by the engine so that it is less than or equal to the maximum torque acceptable by the MGB during the step of engaging the coupling mechanism.

2. A method according to claim 1 , wherein the method includes an additional step of supplying “ready to engage” information as soon as the “ready to engage” state is determined, the step of supplying “ready to engage” information being performed between the step of determining a “ready to engage” state and the step of engaging the coupling mechanism, the step of engaging the coupling mechanism then being performed manually by a pilot using an engagement lever arranged in a cockpit of the aircraft.

3. A method according to claim 1 , wherein the method includes various additional steps situated between the step of determining a “ready to engage” state and the step of engaging the coupling mechanism, the additional steps comprising:
information means of the aircraft supplying “ready to engage” information as soon as the “ready to engage” state is determined; and
a pilot activating an engagement order for the coupling mechanism, the engagement of the coupling mechanism then being performed automatically.

4. A method according to claim 1 , wherein the step of engaging the coupling mechanism is performed automatically as soon as the “ready to engage” state is determined.

5. A method according to claim 4 , wherein the step of engaging the coupling mechanism is performed by regulating a speed of engagement as a function of the first measurement giving the first speed of rotation of the engine and as a function of the setpoint speed of rotation for the engine.

6. A method according to claim 4 , wherein the step of engaging the coupling mechanism is performed by regulating a speed of engagement as a function of the torque delivered by the engine and of the maximum torque acceptable by the MGB.

7. A method according to claim 1 , wherein the step of determining a “ready to engage” state for the coupling mechanism delivers the “ready to engage” state when the difference between the first measurement giving the first speed of rotation of the engine and the setpoint speed of rotation for the engine is less than or equal to a first threshold.

8. A method according to claim 1 , wherein the step of determining a state of an engine includes taking a second measurement giving the temperature of a cooling liquid of the engine and a third measurement giving the temperature of a lubrication liquid of the engine, and the step of determining a “ready to engage” state for the coupling mechanism delivers the “ready to engage” state when the difference between the first measurement giving the speed of rotation of the engine and a setpoint speed of rotation of the engine is less than or equal to a first threshold, the second measurement giving the temperature of the cooling liquid of the engine is situated in a first range of operating temperatures, and the third measurement giving the temperature of the lubrication liquid of the engine is situated in a second range of operating temperatures.

9. A method according to claim 1 , wherein during the step of determining the maximum torque acceptable by the MGB, a fourth measurement is taken giving the temperature of a lubrication liquid of the MGB, and a fifth measurement is taken giving the pressure of the lubrication liquid of the MGB, and the maximum acceptable torque is determined as a function of the fourth measurement giving the temperature of the lubrication liquid of the MGB, of the fifth measurement giving the pressure of the lubrication liquid of the MGB, and of the results of tests.

10. A method according to claim 1 , wherein during the step of determining the maximum torque acceptable by the MGB, a fourth measurement is taken giving the temperature of a lubrication liquid of the MGB, and a sixth measurement is taken giving a speed of rotation of the MGB, and then the maximum acceptable torque is determined as a function of the fourth measurement giving the temperature of the lubrication liquid of the MGB, of the sixth measurement giving the speed of rotation of the MGB, and of the results of tests.

11. A method according to claim 1 , wherein during the step of determining the maximum torque acceptable by the MGB, a fifth measurement is taken giving the pressure of the lubrication liquid of the MGB, and then the maximum acceptable torque is determined as a function of the fifth measurement giving the pressure of the lubrication liquid of the MGB, the maximum acceptable torque being equal to a reduced torque if the fifth measurement giving the pressure of the lubrication liquid of the MGB is less than or equal to a fourth threshold and the maximum acceptable torque being equal to a maximum torque if the fifth measurement giving the pressure of the lubrication liquid of the MGB is greater than the fourth threshold.

12. A device for controlling a coupling mechanism between an engine and a main mechanical power transmission gearbox MGB for an aircraft, the aircraft having at least one engine, a respective control system for each engine, an MGB, and at least one coupling mechanism, there being a respective coupling mechanism arranged between each engine and the MGB for engaging an outlet shaft of the engine with a respective inlet shaft of the MGB, the device for controlling the coupling mechanism comprising:
first determination means for determining the state of the engine and having a first sensor for taking a first measurement giving the speed of rotation of the engine;
second determination means for determining a “ready to engage” state for the coupling mechanism;
third determination means for determining a maximum torque that can be accepted by the MGB; and
control means for controlling the engagement of the coupling mechanism associated with the engine;
each control system of the engine being designed to regulate the speed of rotation of the engine on a setpoint speed of rotation for the engine while controlling the torque delivered by the engine so that it is less than or equal to the maximum torque acceptable by the MGB during the engagement of the coupling mechanism.

13. A device according to claim 12 , wherein the control means enable the coupling mechanism to be engaged automatically as soon as the “ready to engage” state is determined.

14. A device according to claim 12 , wherein the device includes information means and action means arranged in a cockpit of the aircraft, the information means providing “ready to engage” information as soon as the “ready to engage” state is determined, the control means engaging the coupling mechanism to be engaged automatically as soon as the “ready to engage” state is determined and as soon as the action means are actuated.

15. A device according to claim 12 , wherein the device includes information mean

Assignees

• Airbus Helicopters

Inventors

• Dumur Guillaume

Classifications

• B64D31/14 Primary

  Transmitting means between initiating means and power plants · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• B64D31/04

  actuated personally · CPC title

• B64D31/06

  actuated automatically · CPC title

• B64D35/08

  characterised by the transmission being driven by a plurality of power plants (for hybrid-electric power plants B64D35/022) · CPC title