Method of optimizing the noise generated in flight by a rotorcraft
A method of optimizing the noise generated by a hybrid power plant of a rotorcraft in flight, the hybrid power plant driving a main rotor of the rotorcraft in rotation and being provided with at least one engine, with at least one electric machine, and with at least one electrical energy source that electrically powers the electric machine. The method includes a determination step for determining a required power delivered by the hybrid power plant and that is required for the flight phase, and a distribution step for distributing the required power between the at least one engine and the electric machine as a function of a target noise level and of the required power for the flight phase, as well as of a model for the noise generated by the at least one engine as a function of one of its parameters.
1 . A method of optimizing noise generated by a hybrid power plant of a rotorcraft during a flight phase, the hybrid power plant being provided with at least one engine and with at least one electric machine;
wherein the method includes the following steps:
a determination step for determining a required power to be delivered by the hybrid power plant for the flight phase; and
a distribution step for distributing the required power between the engine(s) and the electric machine(s) as a function of a target noise level, the required power, and a model for a noise generated by the engine(s) depending on an operating parameter of the engine(s),
wherein the distribution step includes the following sub-steps:
a first control sub-step for controlling the electric machine(s) to progressively increase a supplementary power delivered by the electric machine(s); and
a second control sub-step for controlling the engine(s) to reduce a main power delivered by the engine(s) so that the hybrid power plant delivers the required power; and
wherein the model for the noise generated by the engine(s) includes a first increase zone in which the model models the noise generated by the engine(s) increasing as the operating parameter increases followed by a decrease zone in which the model models the noise generated by the engine(s) decreasing as the operating parameter further increases followed by a second increase zone in which the model models the noise generated by the engine(s) increasing as the operating parameter further increases, and while, during the distribution step, the main power delivered by the engine(s) leads to the engine(s) operating in the decrease zone, the distribution step further includes controlling the engine(s) to increase the operating parameter of the engine(s) and thereby increase the main power delivered by the engine(s) and cause the engine(s) to cease operating in the decrease zone and to instead operate in the second increase zone, and controlling the electric machine(s) to reduce the supplementary power delivered by the electric machine(s) so that the hybrid power plant delivers the required power.
2 . The method according to claim 1 ,
wherein the supplementary power delivered by the electric machine(s) increases so long as the operating parameter of the engine(s) is greater than a value corresponding to the target noise level, the operating parameter decreasing in parallel, and when the supplementary power is equal to an available power, the supplementary power ceases to increase.
3 . The method according to claim 1 ,
wherein, while a power delivered by the hybrid power plant is greater than the required power, the electric machine(s) operate(s) in generator mode to transform surplus power delivered by the engine(s) into electrical energy.
4 . The method according to claim 1 ,
wherein the method further includes the following steps:
a first monitoring step for monitoring the engine(s) to determine whether the engine(s) is/are in an on state, in an off state, or in a state making it possible to drive a rotor of the rotorcraft;
a second monitoring step for monitoring the electric machine(s) to determine whether the electric machine(s) is/are in an on state or in an off state;
a third monitoring step for monitoring an electrical network of the rotorcraft that powers the electric machine(s) to check that the electrical network can power the electric machine(s); and
an anticipated switch-on step for switching on the electric machine(s) in anticipation as soon as a powering authorization is issued whenever a powering authorization is issued following the third monitoring step, and if the second monitoring step determines that the electric machine(s) is/are in an off state.
5 . The method according to claim 1 ,
wherein the target noise level is a function of the environment overflown by the rotorcraft and/or of a height of flight of the rotorcraft relative to the ground of the overflown environment.
6 . The method according to claim 1 ,
wherein the method further includes an inhibition step for inhibiting the distribution step for distributing the required power when, during the flight phase, the engine(s) is/are not a predominant noise source.
7 . The method according to claim 6 ,
wherein the flight phase, in which the engine(s) is/are not the predominant noise source, is a level cruising flight phase or an approach flight phase.
8 . The method according to claim 1 ,
wherein the method further includes a protection step made up of the following sub-steps:
a determination sub-step for determining a speed of rotation of a rotor of the rotorcraft; and
a reduction sub-step for reducing the supplementary power delivered by the electric machine(s) so that the hybrid power plant delivers the required power, if the speed of rotation is greater than a predetermined speed.
9 . The method according to claim 1 ,
wherein the operating parameter of the engine(s) is a speed of rotation of the engine(s), an operating temperature of the engine(s), or a torque delivered by the engine(s).
10 . The method according to claim 1 ,
wherein, the engine(s) is/are turboshaft engine(s) comprising a gas generator and a free turbine, the operating parameter of the engine(s) is a speed of rotation of the gas generator, a temperature of the gases at an outlet of a combustion chamber of the gas generator, or a torque delivered by the free turbine or by the gas generator.
11 . A system for optimizing noise generated by a hybrid power plant of a rotorcraft during a flight phase, the hybrid power plant being provided with at least one engine and with at least one electric machine, the system comprising:
a controller configured to determine a required power to be delivered by the hybrid power plant for the flight phase, and to distribute the required power between the engine(s) and the electric machine(s) as a function of a target noise level, the required power, and a model for a noise generated by the engine(s) depending on an operating parameter of the engine(s);
wherein to distribute the required power between the engine(s) and the electric machine(s) the controller is further configured to control the electric machine(s) to progressively increase a supplementary power delivered by the electric machine(s) and control the engine(s) to reduce a main power delivered by the engine(s) so that the hybrid power plant delivers the required power; and
the model for the noise generated by the engine(s) includes a first increase zone in which the model models the noise generated by the engine(s) increasing as the operating parameter increases followed by a decrease zone in which the model models the noise generated by the engine(s) decreasing as the operating parameter further increases followed by a second increase zone in which the model models the noise generated by the engine(s) increasing as the operating parameter further increases, and while the main power delivered by the engine(s) leads to the engine(s) operating in the decrease zone, the controller is further configured to control the engine(s) to increase the operating parameter of the engine(s) and thereby increase the main power delivered by the engine(s) and cause the engine(s) to cease operating in the decrease zone and to instead operate in the second increase zone, and control the electric machine(s) to reduce the supplementary power delivered by the electric machine(s) so that the hybrid power plant delivers the required power.
12 . The system of claim 11 ,
wherein the operating parameter of the engine(s) is a speed of rotation of the engine(s), an operating temperature of the engine(s), or a torque delivered by the engine(s).
13 . A rotorcraft comprising:
a hybrid power plant provided with at least one engine and with at least one electric machine; and
a system for optimizing noise generated by the hybrid power plant during a flight phase, the system including a controller configured to determine a required power to be delivered by the hybrid power plant for the flight phase, and to distribute the required power between the engine(s) and the electric machine(s) as a function of a target noise level, the required power, and a model for a noise generated by the engine(s) depending on an operating parameter of the engine(s); and
wherein to distribute the required power between the engine(s) and the electric machine(s) the controller is further configured to control the electric machine(s) to progressively increase a supplementary power delivered by the electric machine(s) and control the engine(s) to reduce a main power delivered by the engine(s) so that the hybrid power plant delivers the required power; and
the model for the noise generated by the engine(s) includes a first increase zone in which the model models the noise generated by the engine(s) increasing as the operating parameter increases followed by a decrease zone in which the model models the noise generated by the engine(s) decreasing as the operating parameter further increases followed by a second increase zone in which the model models the noise generated by the engine(s) increasing as the operating parameter further increases, and while the main power delivered by the engine(s) leads to the engine(s) operating in the decrease zone, the controller is further configured to control the engine(s) to increase the operating parameter of the engine(s) and thereby increase the main power delivered by the engine(s) and cause the engine(s) to cease operating in the decrease zone and to instead operate in the second increase zone, and control the electric machine(s) to reduce the supplementary power delivered by the electric machine(s) so that the hybrid power plant delivers the required power.
14 . The rotorcraft of claim 13 ,
wherein the operating parameter of the engine(s) is a speed of rotation of the engine(s), an operating temperature of the engine(s), or a torque delivered by the engine(s).