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.

An example method includes: determining a throttle command for a servomotor configured to control a position of a throttle lever, where the position of the throttle lever indicates a commanded thrust for the first engine of the aircraft; determining a trim command for the first engine to equalize the thrust of the first engine with the respective thrust of the second engine; determining that a magnitude of the throttle command is less than a magnitude of a threshold throttle command indicative of a dead zone of the servomotor, where the servomotor is irresponsive to a given throttle command within the dead zone; modifying the trim command based on the throttle command to generate a modified trim command that compensates for irresponsiveness of the servomotor to the throttle command; and changing the thrust generated by the first engine based on the modified trim command.

A system and method for controlling the operations of a vehicle in response to an analysis of the vehicle's status and performance compared to a set of external performance parameters. The vehicle may be operable to adjust its performance in response to the analysis in order to comply with the performance parameters. The vehicle may further be operable to prevent activation or continued operation of one or more components in response to the analysis.

A system may include at least one processor configured to receive a fuel signal indicative of an amount of fuel supplied to a cylinder of an internal combustion engine, receive an air signal indicative of a quantity of air supplied to the cylinder, and estimate a mean effective pressure in the cylinder based at least in part on the fuel signal and the air signal. The system may estimate an exhaust gas temperature for exhaust gas entering an exhaust manifold associated with the internal combustion engine, generate a rate of temperature change value for the exhaust manifold based at least in part on the exhaust gas temperature, generate an estimated exhaust manifold temperature based at least in part on the rate of temperature change value for the exhaust manifold, and estimate an exhaust gas temperature for exhaust gas exiting the exhaust manifold and entering a turbine of a turbocharger.

A system may include at least one processor configured to receive a fuel signal indicative of an amount of fuel supplied to a cylinder of an internal combustion engine, receive an air signal indicative of a quantity of air supplied to the cylinder, and estimate a mean effective pressure in the cylinder based at least in part on the fuel signal and the air signal. The system may estimate an exhaust gas temperature for exhaust gas entering an exhaust manifold associated with the internal combustion engine, generate a rate of temperature change value for the exhaust manifold based at least in part on the exhaust gas temperature, generate an estimated exhaust manifold temperature based at least in part on the rate of temperature change value for the exhaust manifold, and estimate an exhaust gas temperature for exhaust gas exiting the exhaust manifold and entering a turbine of a turbocharger.

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.

An engine breather filter assembly for monitoring an internal combustion comprises: a filter cavity configured to accommodate a breather filter element; a processor; and a sensor module configured to sense a characteristic of the internal combustion engine and output data representative of the sensed characteristic to the processor. The engine breather filter assembly is configured to provide a housing for the processor. The processor is configured to determine a value representative of the firing frequency of the internal combustion engine based on the output data.

An operation management device includes a state acquiring unit that acquires a measurement value of a first state amount indicating an operation state of a power generation plant, a state updating unit that updates an estimation value of a second state amount, which indicates the operation state of the power generation plant and is a state amount different from the first state amount, based on the measurement value of the first state amount, and a managing unit that manages the operation state of the power generation plant based on the estimation value of the second state amount.

Provided is a compressor capable of calculating the correct time remaining before maintenance. The compressor is provided with: a compressor body that compresses fluid; a motor that drives the compressor body; a temperature sensor that detects the temperature of the compressor; a pressure sensor that detects the pressure of the compressed fluid outputted from the compressor body; and a calculation unit that calculates the time remaining before maintenance for the compressor body, using the temperature of the compressor and the pressure of the compressed fluid assigned with respective predetermined weights. The calculation unit changes the weighting of the temperature according to the pressure of the compressed fluid or the operation rate of the compressor body.

The present teaching aims to provide: a cam angle sensor fault diagnosis apparatus for straddled vehicle, capable of detecting a fault of a cam angle sensor installed in a straddled vehicle and guessing a fault place; an engine system; and a straddled vehicle. A cam angle sensor fault diagnosis apparatus for straddled vehicle includes: a cam signal receiving unit connected to a signal output line through which a cam angle sensor outputs a cam signal in accordance with the rotation angle, the cam signal receiving unit being configured to receive a cam signal via the signal output line; a state determination unit that determines one or two fault states of the cam angle sensor from a disconnection state, a power supply fault state, and a ground fault state, distinguishably from the other fault states, in accordance with a signal level of a cam signal received by the cam signal receiving unit; and a signal output unit that outputs a fault signal representing the one or two fault states determined by the state determination unit, in such a manner that the fault signal representing the one or two fault states is different from a fault signal representing the other fault states.