Singular value decomposition-based method for constrained control of gas turbine engines
A disclosed method for controlling an aircraft propulsion system includes modeling dynamics of a propulsion system, formulating a problem for achieving the target output as system of linear equations constrained by physical limits of the propulsion system, and generating a solution to the system of linear equations with a singular value decomposition solver module that utilizes Jacobi's singular value decomposition. A control command is generated based on the solution that includes instructions for adjusting a propulsion system operating parameter toward a target output and the propulsion system us operated according to the control command.
1 . A method for controlling an aircraft propulsion system with a controller, the method comprising:
receiving a target output for at least one propulsion system operating parameter;
receiving operation information indicative of at least one measured engine operating parameter;
modeling dynamics of the propulsion system with a system model;
determining an output designation of the target output to be one of a Type I or a Type II, wherein the Type I designation comprises a target output that directly affects the at least one propulsion system operating parameter and the Type II designation comprises a target output that takes additional time steps to propagate to affect the at least one propulsion system operating parameter;
formulating a problem for achieving the target output as a system of equations constrained by physical limits of the propulsion system based in part on the determination of the output designation being one of the Type I or Type II;
generating a solution to the system of equations with a singular value decomposition solver module utilizing Jacobi's singular value decomposition;
generating at least one control command based on the generated solution, the at least one control command includes instructions for adjusting that at least one propulsion system operating parameter toward the target output; and
operating the propulsion system according to the at least one control command.
2 . The method as recited in claim 1 , further comprising generating the solution by determining a factorization of a sensitivity matrix and a conditioned error vector.
3 . The method as recited in claim 2 , further comprising determining an inverse matrix and a first degeneracy index with an inverse matrix calculator.
4 . The method as recited in claim 3 , further comprising generating the solution at least partially based on a conditioned error vector.
5 . The method as recited in claim 4 , further comprising solving an input sensitivity matrix with the Jacobi's singular value decomposition.
6 . The method as recited in claim 5 , wherein the system model utilizes information indicative of the at least one measured engine operating parameter, ambient conditions actuator requests, aircraft conditions and sensor measurements.
7 . The method as recited in claim 6 , wherein formulating the problem further comprises receiving the target output, system limits, system schedules and the system model.
8 . A control system for an aircraft propulsion system comprising:
a controller including a processor and a memory for storing a control logic for generating control commands for operating a propulsion system, wherein the controller is programmed to:
receive a target output for at least one propulsion system operating parameter;
receive operation information indicative of at least one measured engine operating parameter;
model dynamics of the propulsion system with a system model;
determine an output designation of the target output to be one of a Type I or a Type II, wherein the Type I designation comprises a target output that directly affects the at least one propulsion system operating parameter and the Type II designation comprises a target output that takes additional time steps to propagate to affect the at least one propulsion system operating parameter;
formulate a problem for achieving the target output as a system of equations constrained by physical limits of the propulsion system based in part on the determination of the output designation being one of the Type I or Type II;
generate a solution to the system of equations with a singular value decomposition solver module utilizing Jacobi's singular value decomposition;
generate at least one control command based on the generated solution, the at least one control command includes instructions for adjusting that at least one propulsion system operating parameter toward the target output; and
operate the propulsion system according to the at least one control command.
9 . The control system as recited in claim 8 , wherein the controller comprises a constrained model-based controller having a system model module, an optimization formulation module and a solver module.
10 . The control system as recited in claim 9 , wherein the controller is further programed for generating the solution by determining a factorization of a sensitivity matrix and a conditioned error vector.
11 . The control system as recited in claim 10 , wherein the controller is further programmed for determining an inverse matrix and a first degeneracy index with an inverse matrix calculator.
12 . The control system as recited in claim 11 , wherein the controller is further programmed to generate the solution at least partially based on a conditioned error Vector.
13 . The control system as recited in claim 12 , wherein the controller is further programmed for solving an input sensitivity matrix with the Jacobi's singular value decomposition.
14 . The control system as recited in claim 13 , wherein the system model utilizes information indicative of the at least one measured engine operating parameter, ambient conditions actuator requests, aircraft conditions and sensor measurements.
15 . The control system as recited in claim 14 , wherein the controller is further programmed to formulate the problem for achieving the target output by receiving the target output, system limits, system schedules and the system model.
16 . An aircraft propulsion system comprising:
a turbine engine configured to generate a propulsive thrust based on at least one performance target; and
a controller including a processor and a memory for storing a constrained model-based control system for generating control commands for operating the turbine engine, wherein the constrained model-based control system includes an engine model, an optimization formulation module and a solver module, the controller is programmed to:
receive a target output for at least one turbine engine operating parameter;
receive operation information indicative of at least one measured engine operating parameter;
model dynamics of the turbine engine with a system model;
determine an output designation of the target output to be one of a Type I or a Type II, wherein the Type I designation comprises a target output that directly affects the at least one propulsion system operating parameter and the Type II designation comprises a target output that takes additional time steps to propagate to affect the at least one propulsion system operating parameter;
formulate a problem for achieving the target output as a system of linear equations constrained by physical limits of the turbine engine based in part on the determination of the output designation being one of the Type I or Type II;
generate a solution to the system of linear equations with a singular value decomposition solver module utilizing Jacobi's singular value decomposition;
generate at least one control command based on the generated solution, the at least one control command includes instructions for adjusting that at least one turbine engine operating parameter toward the target output; and
operate the turbine engine according to the at least one control command.
17 . The aircraft propulsion system as recited in claim 16 , wherein the controller is further programed to generate the solution by determining a factorization of a sensitivity matrix and a conditioned error vector, determining an inverse matrix and a first degeneracy index with an inverse matrix calculator and to solve an input sensitivity matrix with the Jacobi's singular value decomposition.
18 . The aircraft propulsion system as recited in claim 17 , wherein the engine model utilizes information indicative of the at least one measured engine operating parameter, ambient conditions, actuator requests, aircraft conditions and sensor measurements.
19 . The aircraft propulsion system as recited in claim 18 , wherein the control system is further programmed to formulate the problem for achieving the target output by receiving the target output, system limits, system schedules and the engine model.