Abstract: A method for operating a rotorcraft includes providing a power hold by performing monitoring one or more operational parameters of the rotorcraft during flight, determining whether operational parameters need adjustment according to a relationship between the operational parameters and operating limits associated with a power setting for the power hold, and determining a flight parameter for one or more flight control devices of the rotorcraft in response to determining that the operational parameters need adjustment. Providing the power hold further includes sending a position set signal to a trim assembly of the rotorcraft to set a first position of a pilot control connected to the trim assembly according to a pilot control setting generated according to the flight parameter, and controlling a flight control device control according to a second position of the pilot control.

Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.

Abstract: A method for operating a rotorcraft includes providing a power hold by performing monitoring one or more operational parameters of the rotorcraft during flight, determining whether operational parameters need adjustment according to a relationship between the operational parameters and operating limits associated with a power setting for the power hold, and determining a flight parameter for one or more flight control devices of the rotorcraft in response to determining that the operational parameters need adjustment. Providing the power hold further includes sending a position set signal to a trim assembly of the rotorcraft to set a first position of a pilot control connected to the trim assembly according to a pilot control setting generated according to the flight parameter, and controlling a flight control device control according to a second position of the pilot control.

Abstract: According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.

Abstract: A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.

Abstract: A method of limiting vertical axis augmentation in a rotorcraft, the method comprising: measuring a torque with a sensor; deriving a comparison of the torque to a lower torque limit, using a computer processor; and adjusting a vertical axis control command based upon the comparison of the torque to the lower torque limit.

Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.

Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.

Abstract: A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.

Abstract: According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.

Abstract: A flight control system uses a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade, and a limiter configured to selectively remove the threshold limit of the governor when the collective pitch control exceeds a threshold limit, so as to permit a pilot full command of the collective above the threshold limit. The threshold limit is selectively removed and phased back in to provide temporary pilot control to “cushion” landing of an aircraft when an engine has failed.

Abstract: A flight control system having a control law, the control law operable to generate a modified pitch command, the modified pitch command representing a greater amount of collective pitch compared to an amount of collective pitch generated by a first pitch command, the modified pitch command being generated because a vertical descent speed of the rotorcraft at a given forward airspeed is greater than a threshold. A method of avoiding entry into an undesired vertical descent speed region during operation of a rotorcraft, including measuring a forward airspeed; evaluating a vertical descent of the rotorcraft; and generating a modified collective pitch command in respond to a first collective pitch command having a collective pitch value that would cause the rotorcraft to experience a vertical descent rate greater than a threshold value at the forward airspeed of the rotorcraft.

Abstract: The system for adaptively governing a speed of a rotor assembly in an aircraft can include a processor configured for comparing receivable data to limit data in an algorithm and subsequently making one or more commands that affect the speed of the rotor assembly, the algorithm being configured for analyzing power available during operation of the aircraft. The method can include calculating a first power available by comparing an actual transmission torque to a transmission torque limit; calculating a second power available by comparing an actual engine exhaust temperature to an engine exhaust temperature limit; and comparing the first power available to the second power available.

Abstract: A system for detecting degradation of a servo valve; having a controller, a servo valve, a position sensor, and a rate monitor. The controller receives inputs and transmits command data. The servo valve has an actuator and is conductively coupled to the controller to receive command data from the controller and move the actuator in response to the command data. The position sensor operably associated with the servo valve for measuring movement of the actuator and transmits corresponding movement data to the controller. The rate monitor coupled to the controller and position sensor for receiving the command data and the movement data as inputs respectively. The rate monitor processes the inputs to produce a steady state rate error signal. The rate monitor compares the steady state rate error signal to selected operational limits and produces a telemetry output when the operational limits are exceeded.

Abstract: A method of preserving rotor speed during a one engine inoperative operation of an rotorcraft, the method can include: detecting a failure of a first engine; monitoring an engine parameter associated with a second engine; using a computer processor to compare the engine parameter to an engine limit; and commanding a decrease collective pitch command when the engine parameter is within a predefined range of the engine limit.

Abstract: A method of limiting vertical axis augmentation in a rotorcraft, the method comprising: measuring a torque with a sensor; deriving a comparison of the torque to a lower torque limit, using a computer processor; and adjusting a vertical axis control command based upon the comparison of the torque to the lower torque limit.

Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate an increase collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.

Abstract: A flight control system uses a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade, and a limiter configured to selectively remove the threshold limit of the governor when the collective pitch control exceeds a threshold limit, so as to permit a pilot full command of the collective above the threshold limit. The threshold limit is selectively removed and phased back in to provide temporary pilot control to “cushion” landing of an aircraft when an engine has failed.

Abstract: The system for adaptively governing a speed of a rotor assembly in an aircraft can include a processor configured for comparing receivable data to limit data in an algorithm and subsequently making one or more commands that affect the speed of the rotor assembly, the algorithm being configured for analyzing power available during operation of the aircraft. The method can include calculating a first power available by comparing an actual transmission torque to a transmission torque limit; calculating a second power available by comparing an actual engine exhaust temperature to an engine exhaust temperature limit; and comparing the first power available to the second power available.

Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.