Abstract A power management system is disclosed for an advanced helicoptor having h lift and thrust propulsion units and at least one power plant which comprises, a signal generator for generating a first signal which is proportional to the power available from the power plant, a power use gage connected to the lift propulsion unit which has an output that varies according to the amount of power used by that propulsion unit and a circuit which is connected to the power use gage and which receives the first signal for generating a second signal which is proportional to the amount of power remaining. The circuit is either used to power an indicator which indicates to the pilot the amount of power remaining for the thrust propulsion unit, or can be connected directly to a limit actuator for limiting the amount of power the pilot can apply to the thrust propulsion unit.
In the operation of a helicopter engine wherein operating conditions change power demands, such as wherein under flight conditions an increase in rotor blade pitch causes a demand for increased engine power, a process for making excess power available for a thrusting device of the helicopter when no such demand for increased power is made, comprising generating a first signal which is proportional to the total amount of engine power available, continuously sensing the amount of engine power utilized under the flight conditions, generating a second signal proportional to the amount of excess power remaining for the thrusting device, and utilizing said second signal for physically limiting to that excess the amount of power which can be applied to the thrusting device.
Claim 2
Dependent Claim
122 words
In the operation of a helicopter engine wherein operating conditions change power demands, such as wherein under flight conditions an increase in rotor blade pitch causes a demand for increased engine power, a process for making excess power available for a thrusting device of the helicopter when no such demand for increased power is made, comprising generating a first signal which is proportional to the total amount of engine power available, continuously sensing the amount of engine power utilized under the flight conditions, generating a second signal proportional to the amount of excess power remaining for the thrusting device, and utilizing said second signal for physically limiting to that excess the amount of power which can be applied to the thrusting device.