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 method to generate an aerodynamic model, comprising:
performing for each actuator in a plurality of actuators comprising an aircraft 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;
performing a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions; and
combining respective results of the first and second sets of simulations to generate the aerodynamic model.
2. The method of claim 1 , wherein the second set of simulations is performed with respect to a subset of operating conditions in a range of operating conditions with which the aerodynamic model is associated.
3. The method of claim 2 , further comprising doing one or both of interpolating and extrapolating to generate interaction data for operating conditions not simulated in the second set of simulations.
4. The method of claim 2 , wherein the operating conditions include an aircraft angle of attack α.
5. The method of claim 2 , wherein the operating conditions include a side wind direction β.
6. The method of claim 2 , wherein the subset of operating conditions comprises a subset of the range of operating conditions.
7. The method of claim 2 , wherein the subset of operating conditions comprises fewer than ten elements of the range set of operating conditions.
8. The method of claim 2 , wherein the subset of operating conditions comprises two elements of the range of operating conditions.
9. The method of claim 2 , 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.
10. The method of claim 1 , wherein the aerodynamic model comprises a lookup table.
11. A computer program product to generate an aerodynamic model, the computer program product being embodied in a tangible computer readable storage medium and comprising computer instructions for:
performing for each actuator in a plurality of actuators comprising an aircraft 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;
performing a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions; and
combining respective results of the first and second sets of simulations to generate the aerodynamic model.
12. The computer program product of claim 11 , wherein the second set of simulations is performed with respect to a subset of operating conditions in a range of operating conditions with which the aerodynamic model is associated.
13. The computer program product of claim 12 , further comprising computer instructions for doing one or both of interpolating and extrapolating to generate interaction data for operating conditions not simulated in the second set of simulations.
14. The computer program product of claim 12 , wherein the operating conditions include an aircraft angle of attack α.
15. The computer program product of claim 12 , wherein the operating conditions include a side wind direction β.
16. The computer program product of claim 12 , wherein the subset of operating conditions comprises a subset of the range of operating conditions.
17. The computer program product of claim 12 , wherein the subset of operating conditions comprises fewer than ten elements of the range set of operating conditions.
18. The computer program product of claim 12 , wherein the subset of operating conditions comprises two elements of the range of operating conditions.
19. The computer program product of claim 12 , 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.
20. The computer program product of claim 12 , wherein the aerodynamic model comprises a lookup table.