Torque control system

Claim 2

Apparatus for providing a signal for controlling the output torque of a prime mover driving a load in a system having rotating parts of known rotational inertia including an output shaft controlled at a commanded torque value, the output shaft controlled at a commanded angular velocity by controlling the load absorbing capacity of the load, the system having signals associated therewith having magnitudes indicative of the actual angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to changes in the actual angular velocity signal for providing a load torque transient signal indicative of the presence of a changing load torque, said load torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing a prime mover output torque error signal compensated for load torque transients for controlling the output torque of the prime mover.

Claim 3

The apparatus of claim 1, wherein said means responsive to changes in the actual velocity signal includes: means for determining the time derivative of the actual angular velocity signal for providing a derivative signal having a magnitude indicative thereof; and means responsive to said derivative signal for multiplying the present value thereof by a factor indicative of the total rotational inertia of the prime mover and driven load, thereby providing said load torque transient signal.

Claim 4

Apparatus for providing a fuel flow signal for controlling the output torque of an aircraft single shaft turboprop engine of known rotational inertial at a commanded torque value by controlling engine fuel flow, the engine output shaft having a propeller and shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the propeller blades, the aircraft having signals associated therewith having magnitudes indicative of the actual propeller angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual propeller angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the propeller shaft, said load torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 5

Apparatus for providing a fuel flow signal for controlling the output torque of an aircraft single shaft turboprop engine of known rotational inertial at a commanded torque value by controlling engine fuel flow, the engine output shaft having a propeller and shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the propeller blades, the aircraft having signals associated therewith having magnitudes indicative of the actual propeller angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual propeller angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the propeller shaft, said load torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 6

The apparatus of claim 3, wherein said means responsive to the signal indicative of actual propeller angular velocity includes: means for determining the time derivative of the actual propeller angular velocity signal and providing a derivative signal having a magnitude indicative thereof; and means responsive to said derivative signal for multiplying the present value thereof by a factor indicative of the total rotational inertia of the single shaft turboprop engine, the rotating gears, the propeller and shaft, thereby providing said load torque transient signal.

Claim 7

Apparatus for providing a fuel flow signal for controlling the output torque of an aircraft two-shaft turboprop engine having a gas generator with a free turbine for driving a compressor on an outer shaft, and having a power turbine on an inner output shaft fluidly coupled to said gas generator for driving the inner shaft at a commanded output torque value by controlling engine fuel flow, the power turbine and inner shaft having a known rotational inertia, the engine output shaft having a propeller and shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the propeller blades, the aircraft having signals associated therewith having magnitudes indicative of the actual propeller angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual propeller angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the propeller shaft, said load torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 8

Apparatus for providing a fuel flow signal for controlling the output torque of an aircraft two-shaft turboprop engine having a gas generator with a free turbine for driving a compressor on an outer shaft, and having a power turbine on an inner output shaft fluidly coupled to said gas generator for driving the inner shaft at a commanded output torque value by controlling engine fuel flow, the power turbine and inner shaft having a known rotational inertia, the engine output shaft having a propeller and shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the propeller blades, the aircraft having signals associated therewith having magnitudes indicative of the actual propeller angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual propeller angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the propeller shaft, said load torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 9

The apparatus of claim 5, wherein said means responsive to the signal indicative of actual propeller angular velocity includes: means for determining the time derivative of the actual propeller angular velocity signal and providing a derivative signal having a magnitude indicative thereof; and means responsive to said derivative signal for multiplying the present value thereof by a factor indicative of the total rotational inertia of the power turbine, the inner shaft, the rotating gears, and the propeller and shaft, thereby providing said load torque transient signal.

Claim 10

Apparatus for providing a fuel flow signal for controlling the output torque of an helicopter single shaft turboprop engine of known rotational inertia at a commanded torque value by controlling engine fuel flow, the engine having a rotor and rotor shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the rotor blades, the helicopter having signals associated therewith having magnitudes indicative of the actual rotor angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual rotor angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the rotor shaft, said torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 11

Apparatus for providing a fuel flow signal for controlling the output torque of an helicopter single shaft turboprop engine of known rotational inertia at a commanded torque value by controlling engine fuel flow, the engine having a rotor and rotor shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the rotor blades, the helicopter having signals associated therewith having magnitudes indicative of the actual rotor angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual rotor angular velocity for providing a load torque transient signal indicative of the presence of a changing load torque exerted on the rotor shaft, said torque transient signal having a present value indicative of the present value of said changing load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 12

The apparatus of claim 7, wherein said means responsive to the signal indicative of actual rotor angular velocity includes: means for determining the time derivative of the actual rotor angular velocity signal and providing a derivative signal having a magnitude indicative thereof; and means responsive to said derivative signal for multiplying the present value thereof by a factor indicative of the total rotational inertia of the single shaft turboprop engine, the rotating gears, and the rotor and rotor shaft, thereby providing said load torque transient signal.

Claim 13

Apparatus for providing a fuel flow signal for controlling the output torque of a helicopter two-shaft turboprop engine having a gas generator with a free turbine for driving a compressor on an outer shaft and a power tubine on an inner output shaft fluidly coupled to said gas generator for driving the inner shaft at a commanded output torque value by controlling engine fuel flow, the power turbine and inner shaft having a known rotational inertia, the engine output shaft having a rotor and rotor shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the rotor blades, the helicopter having signals associated therewith having magnitudes indicative of the actual rotor angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual rotor angular velocity for providing a load torque transient signal indicative of the presence of a change in the load torque exerted on the rotor shaft, said torque transient signal having a present value indicative of the present value of said change in load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 14

Apparatus for providing a fuel flow signal for controlling the output torque of a helicopter two-shaft turboprop engine having a gas generator with a free turbine for driving a compressor on an outer shaft and a power tubine on an inner output shaft fluidly coupled to said gas generator for driving the inner shaft at a commanded output torque value by controlling engine fuel flow, the power turbine and inner shaft having a known rotational inertia, the engine output shaft having a rotor and rotor shaft of known rotational inertia attached by means of gears thereto controlled at a commanded angular velocity by controlling the pitch of the rotor blades, the helicopter having signals associated therewith having magnitudes indicative of the actual rotor angular velocity, a commanded torque value and an actual sensed torque value, comprising: means responsive to the signal indicative of actual rotor angular velocity for providing a load torque transient signal indicative of the presence of a change in the load torque exerted on the rotor shaft, said torque transient signal having a present value indicative of the present value of said change in load torque; and summing means, responsive to said load torque transient signal, to the commanded torque signal and to the sensed torque signal for adding the present values thereof for providing an engine output torque error signal as a fuel flow signal compensated for load torque transients for controlling the fuel flow and hence the output torque of the engine.

Claim 15

The apparatus of claim 9, wherein said means responsive to the angular velocity signal includes: means for determining the time derivative of the actual rotor angular velocity signal and providing a derivative signal having a magnitude indicative thereof; and means responsive to said derivative signal for multiplying the present value thereof by a factor indicative of the total rotational inertia of the power turbine, the inner shaft, the rotating gears, and the rotor and rotor shaft, thereby providing said load torque transient signal.

Claim 16

Apparatus for controlling the output torque of an engine in a system in which the output speed of the engine is controlled at a selected speed, comprising: means responsive to a sensed engine output speed signal for providing a load torque transient signal indicative of the magnitude of any load torque transients present; and summing means, responsive to the load torque transient signal, to a commanded engine output torque signal and to a sensed engine output torque signal for adding the load torque transient signal, the commanded engine output torque signal and the sensed engine output torque signal for providing a compensated engine output torque error signal for controlling the output torque of the engine.

Claim 17

Apparatus for controlling the output torque of an engine in a system in which the output speed of the engine is controlled at a selected speed, comprising: means responsive to a sensed engine output speed signal for providing a load torque transient signal indicative of the magnitude of any load torque transients present; and summing means, responsive to the load torque transient signal, to a commanded engine output torque signal and to a sensed engine output torque signal for adding the load torque transient signal, the commanded engine output torque signal and the sensed engine output torque signal for providing a compensated engine output torque error signal for controlling the output torque of the engine.

Claim 18

The apparatus of claim 11, wherein the means responsive to a sensed engine output speed signal comprises a differentiator for providing an acceleration signal and further comprises a gain proportional to the total rotational inertia of the engine and load, the gain responsive to the acceleration signal for providing the load torque transient signal.

Claim 19

The apparatus of claim 11, wherein the summing means comprises: first summing means responsive to the sensed engine output torque signal and to the load torque transient signal for providing a summed signal having a magnitude indicative of the summation of the sensed engine output torque and any load torque transient present; and second summing means responsive to the summed signal and the commanded engine output torque signal for providing the engine output torque error signal.