Abstract: A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.

Abstract: A fuel metering system for a combustion section of a turbo machine is provided. The turbo machine includes a main fuel line configured to provide a flow of fuel and a zone fuel line split from the main fuel line through which at least a portion of the flow of fuel is provided. A fuel valve is disposed at the zone fuel line and is configured to obtain and receive a present fuel valve area value and a present valve position value. A first pressure sensor is disposed upstream of the fuel valve, in which the first pressure sensor is configured to obtain a first pressure value. A second pressure sensor is disposed downstream of the fuel valve, in which the second pressure sensor is configured to obtain a second pressure value. A flow meter is disposed downstream of the fuel valve.

Abstract: A distributed control system having at least a distributed control module is disclosed. The distributed control module may be configured to determine a fault state associated with a control loop using a built-in test module. The built-in test module may be incorporated into the distributed control module. The fault state may include no faults, a communication fault, a sensor operation fault, or a controllable component fault. The distributed control module may be configured to transmit a closed-loop control command from the distributed control module to a controllable component when the fault state comprises no faults, or transmit an augmented control command from the distributed control module to the controllable component when the fault state comprises a communication fault or a sensor operation fault, or transmit a disconnect control command from the distributed control module to a controllable component when the fault state comprises a controllable component fault.

Abstract: A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to determine a fault state associated with a control loop using a built-in test module. The built-in test module may be incorporated into the distributed control module. The fault state may include no faults, a communication fault, a sensor operation fault, or a controllable component fault. The distributed control module may be configured to transmit a closed-loop control command from the distributed control module to a controllable component when the fault state comprises no faults, or transmit an augmented control command from the distributed control module to the controllable component when the fault state comprises a communication fault or a sensor operation fault, or transmit a disconnect control command from the distributed control module to the controllable component when the fault state comprises a controllable component fault.

Abstract: A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.

Abstract: A fuel metering system for a combustion section of a turbo machine is provided. The turbo machine includes a main fuel line configured to provide a flow of fuel and a zone fuel line split from the main fuel line through which at least a portion of the flow of fuel is provided. A fuel valve is disposed at the zone fuel line and is configured to obtain and receive a present fuel valve area value and a present valve position value. A first pressure sensor is disposed upstream of the fuel valve, in which the first pressure sensor is configured to obtain a first pressure value. A second pressure sensor is disposed downstream of the fuel valve, in which the second pressure sensor is configured to obtain a second pressure value. A flow meter is disposed downstream of the fuel valve.

Abstract: A method and system for controlling a plant having a plurality of actuators, a plurality of inputs corresponding to the operational state of the actuators and plurality of outputs corresponding to an operating condition of the plant according to a model-based control and a plant model. The plant model is on-line reconfigured and the model-based control is built such that the model-based control adapts to the reconfigured plant model.

Abstract: A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.

Abstract: A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided.

Abstract: A method for controlling a gas turbine engine includes receiving, with a controller, a thrust reverse command to activate a thrust reverse feature of the gas turbine engine. The method also includes determining the thrust reverse feature is in a starting position, confirming a gas turbine engine condition is at a first value, and moving the thrust reverse feature to a middle position. The method also includes confirming the gas turbine engine condition is at a second value in coordination with moving the thrust reverse feature to the middle position. Additionally, after moving the thrust reverse feature to the middle position and confirming the gas turbine engine condition is that a second value in coordination with such movement, the method includes moving the thrust reverse feature to a maximum position.

Abstract: A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided.

Abstract: A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.

Abstract: A method and system for controlling a plant having a plurality of actuators, a plurality of inputs corresponding to the operational state of the actuators and plurality of outputs corresponding to an operating condition of the plant according to a model-based control and a plant model. The plant model is on-line reconfigured and the model-based control is built such that the model-based control adapts to the reconfigured plant model.

Abstract: A method and apparatus for multiple variable control of a physical plant with high dimension multiple constraints, includes: mathematically decoupling primary controlled outputs of a controlled physical plant from one another and shaping the pseudo inputs/controlled outputs desired plant dynamics; tracking primary control references and providing pseudo inputs generated by desired primary output tracking for selection; mathematically decoupling constraints from one another; mathematically decoupling constraints from non-traded off primary controlled outputs of the controlled physical plant; shaping the pseudo inputs/constraint outputs desired plant dynamics; tracking constraint control limits; providing pseudo inputs generated by desired constraint output tracking for selection; selecting the most limiting constraints and providing the smooth pseudo inputs for the decoupled primary control; and controlling the physical plant using the decoupled non-traded off primary controlled outputs and the decoupled selec

Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.

Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.

Abstract: A method and apparatus for providing large transient identification for advanced control with multiple constraints. A request to change a current operating condition of a controlled plant is detected. A value of a control constraint corresponding to the request to change the current operating condition of the controlled plant is determined. A magnitude of a transient error corresponding to the request relative to the value of the control constraint is determined and the current operating condition of the controlled plant is adjusted based on the determined magnitude of the transient error.

Abstract: A method and apparatus for providing large transient identification for advanced control with multiple constraints. A request to change a current operating condition of a controlled plant is detected. A value of a control constraint corresponding to the request to change the current operating condition of the controlled plant is determined. A magnitude of a transient error corresponding to the request relative to the value of the control constraint is determined and the current operating condition of the controlled plant is adjusted based on the determined magnitude of the transient error.

Abstract: A vehicle stability enhancement (VSE) system that is adapted for driver skill level. The system includes a driver skill recognition processor that determines the driver skill level based on a driver model that uses certain parameters, such as a steering gain factor and a time delay factor. The driver skill level is used to adjust the damping ratio and natural frequency in dynamic filters in a dynamic command generator to adjust a desired yaw rate signal and a desired side-slip signal. The driver skill level is also used to generate a yaw rate multiplication factor and a side-slip multiplication factor that modify a yaw rate stability signal and a side-slip stability signal in a dynamic control computation processor that generates a stability control signal.

Abstract: A vehicle stability enhancement (VSE) system that is adapted for driver skill level. The system includes a driver skill recognition processor that determines the driver skill level based on a driver model that uses certain parameters, such as a steering gain factor and a time delay factor. The driver skill level is used to adjust the damping ratio and natural frequency in dynamic filters in a dynamic command generator to adjust a desired yaw rate signal and a desired side-slip signal. The driver skill level is also used to generate a yaw rate multiplication factor and a side-slip multiplication factor that modify a yaw rate stability signal and a side-slip stability signal in a dynamic control computation processor that generates a stability control signal.