Compact aero-thermo model based engine power control
Systems and methods for controlling a fluid based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, wherein the open loop model generates current state derivatives, solver state errors, synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based on a series, of utilities that are based on mathematical abstractions of physical laws that govern behavior of the component. The model processor may include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.
1. A control system, comprising:
an actuator for positioning a control device comprising a control surface, wherein the actuator positions the control surface;
a processing circuit configured to execute a control law, the control law configured to direct the actuator as a function of a model output, the model output including an estimated thrust value for the control device; and
a model processor configured to generate the model output, the model processor comprising:
an input object for processing a model input vector and setting a model operating mode;
a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;
wherein the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, a constraint on the current state derivatives and solver state errors being based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control device and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;
an estimate state module configured to determine an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters; and
an output object for processing at least the synthesized parameters of the model to determine the model output.
2. The control system of claim 1 , wherein the control law compares the estimated thrust value with a goal value to determine a thrust control request, the thrust control request received by the actuator to control the thrust of the control device.
3. The control system of claim 1 , wherein the control law applies control error to the estimated thrust signal to account for error in the control device.
4. The control system of claim 3 , wherein the error in the control device is based on at least one of control law error, wear in the control device, customer power extraction, customer bleed extraction, humidity levels, and fuel quality.
5. The control system of claim 1 , wherein the estimated thrust value of the control device is based on, at least, a spool speed of a spool of the control device.
6. The control system of claim 1 , wherein at least one of the utilities is a configurable utility comprising one or more sub-utilities.
7. The control system of claim 1 , wherein the model input vector includes one or more of raw effector data, boundary conditions, engine sensing data, unit conversion information, range limiting information, rate limiting information, dynamic compensation determinations, and synthesized lacking inputs.
8. The control system of claim 1 , wherein the control device is a gas turbine engine.
9. The control system of claim 8 , wherein the one or more cycle synthesis modules are based on one or more mathematical abstractions of physical processes associated with components of a thermodynamic cycle of the gas turbine engine.
10. A method for controlling a control device, the method comprising:
generating, by a computer processor a model output using a model processor;
processing a model input vector and setting a model operating mode;
setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;
generating current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control device and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;
determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters; and
processing at least the synthesized parameters of the model to determine the model output;
directing an actuator associated with the control device as a function of a model output, the model output including an estimated thrust value for the control device, using a control law; and
positioning a control device comprising a control surface using the actuator, wherein the actuator positions the control surface.
11. The method claim 10 , wherein the control law compares the estimated thrust value with a goal value to determine a thrust control request, the thrust control request received by the actuator to control the thrust of the control device.
12. The method of claim 10 , wherein the control law applies control error to the estimated thrust signal to account for error in the control device.
13. The method of claim 12 , wherein the error in the control device is based on at least one of control law error, wear in the control device, customer power extraction, customer bleed extraction, humidity levels, or fuel quality.
14. The method of claim 10 , wherein the estimated thrust value of the control device is based on, at least, a spool speed of a spool of the control device.
15. The method of claim 10 , wherein the control device is a gas turbine engine and the one or more cycle synthesis modules are based on one or more mathematical abstractions of physical processes associated with components of a thermodynamic cycle of the gas turbine engine.
16. A gas turbine engine comprising:
an actuator for positioning the gas turbine engine comprising a control surface, wherein the actuator positions a control surface of an element of the gas turbine engine;
a processing circuit configured to execute a control law configured to direct the actuator as a function of a model output, the model output including an estimated thrust value for the gas turbine engine;
a model processor configured to generate the model output, the model processor comprising:
an input object for processing a model input vector and setting a model operating mode;
a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;
wherein the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the gas turbine engine and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;
an estimate state module configured to determine an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters; and
an output object for processing at least the synthesized parameters of the model to determine the model output.
17. The gas turbine engine of claim 16 , wherein the control law compares the estimated thrust value with a goal value to determine a thrust control request, the thrust control request received by the actuator to control the thrust of the gas turbine engine.
18. The gas turbine engine of claim 16 , wherein the control law applies control error to the estimated thrust signal to account for error in the gas turbine engine.
19. The gas turbine engine of claim 16 , further comprising a spool, wherein the estimated thrust value of the gas turbine engine is based on, at least, a spool speed of the spool.
20. The gas turbine engine of claim 16 , wherein the element of a cycle of the gas turbine engine is an element of at least one of: a duct, a bleed, a pressure loss at a location, a turbine, a compressor, a diffusor, a burner, an exit guide vane, a nozzle, a fan, an efficiency loss module, a fan gear box, or a torque measurement.