Aircraft control system based on sparse set of simulation data
A flight control system is disclosed. In various embodiments, a flight control system includes a data storage device configured to store an aerodynamic model; and a processor coupled to the data storage device and configured to use the aerodynamic model to determine a set of actuators and for each actuator in the set a corresponding set of one or more actuator parameters to achieve a desired set of forces and moments. The aerodynamic model provides for each actuator in the set of actuator corresponding force and moment data for each of a first set of operating conditions based on a first set of simulations performed by varying one or more actuator parameters while holding other actuators at a baseline value and a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions.
1. A flight control system, comprising:
a data storage device configured to store an aerodynamic model; and
a processor coupled to the data storage device and configured to use the aerodynamic model to determine a set of actuators and for each actuator in the set a corresponding set of one or more actuator parameters to achieve a desired set of forces and moments and to operate the actuators in the determined optimal set of actuators using the determined actuator parameters;
wherein the aerodynamic model provides for each actuator in the set of actuator corresponding force and moment data for each of a first set of operating conditions based on a first set of simulations performed by varying one or more actuator parameters of the actuator through an operating range of the actuator while holding other actuators in the set steady at a baseline value and a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions.
2. The flight control system of claim 1 , wherein the data storage device comprises a memory device.
3. The flight control system of claim 1 , further comprising one or more sensors and wherein the processor is coupled to the one or more sensors and configured to use respective sensor outputs of the one or more sensors to determine the set of actuators and for each actuator in the set the corresponding set of one or more actuator parameters.
4. The flight control system of claim 1 , wherein the first set of operating conditions includes a full operating range of conditions.
5. The flight control system of claim 4 , wherein the conditions include an aircraft angle of attack α.
6. The flight control system of claim 4 , wherein the conditions include a side wind direction β.
7. The flight control system of claim 4 , wherein the second set of operating conditions comprises a subset of the first set of operating conditions.
8. The flight control system of claim 7 , wherein the second set of operating conditions comprises fewer than ten elements of the first set of operating conditions.
9. The flight control system of claim 7 , wherein the second set of operating conditions comprises two elements of the first set of operating conditions.
10. The flight control system of claim 7 , wherein the aerodynamic model is based at least in part on interaction factors determined by one or both of interpolation and extrapolation for operating points included in the first set of operating conditions but not included in the second set of operating conditions.
11. The flight control system of claim 1 , wherein the aerodynamic model comprises a lookup table.
12. A computer system, comprising:
a memory configured to store geometry data representing a plurality of actuators and one or more aerodynamic structures of an aircraft; and
a processor coupled to the memory and configured to use the geometry data to generate an aerodynamic model of the aircraft, including by performing for each actuator in the plurality of actuators a first set of simulations by varying one or more actuator parameters of the actuator through an operating range of the actuator while holding other actuators in the set steady at a baseline value and a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions;
wherein the aircraft includes a flight control system configured to use the aerodynamic model to determine an optimal set of actuators included in the plurality of actuators, and for each actuator a corresponding actuator parameter, to achieve a desired set of forces and moments, and to operate the actuators in the determined optimal set of actuators using the determined actuator parameters.
13. The computer system of claim 12 , wherein the processor is configured to perform the second set of simulations with respect to a subset of operating conditions in a range of operating conditions with which the aerodynamic model is associated.
14. The computer system of claim 13 , wherein the processor is configured to do one or both of interpolate and extrapolate to generate interaction data for operating conditions not simulated in the second set of simulations.
15. The computer system of claim 12 , wherein the aerodynamic model comprises a lookup table and the processor is configured to populate the lookup table at least in part based on combined results of the first set of simulations and the second set of simulations.