Systems and methods for aircraft function prioritization and allocation
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.
1. A computer-implemented method for command prioritization in an aircraft, the method comprising:
receiving, using at least one hardware processor, a pilot command;
analyzing, using the at least one hardware processor, the pilot command to determine characteristics associated with the pilot command, the characteristics relating to airspeed and climb of an aircraft;
assigning, using the at least one hardware processor, weights to characteristics associated with the pilot command based on constraint data;
determining, using the at least one hardware processor, a priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command;
calculating, using the at least one hardware processor, a correction factor based on the determined priority;
updating, using the at least one hardware processor, the characteristics associated with the pilot command by applying the correction factor to the characteristics; and
generating, using the at least one hardware processor, at least one actuator command to control the aircraft based on the updated characteristics associated with the pilot command.
2. The computer-implemented method of claim 1 , wherein determining the priority of execution between airspeed and climb comprises:
performing, using the at least one hardware processor, at least one saturation check based on the pilot command; and
calculating, using the at least one hardware processor, a command limit base on the at least one saturation check.
3. The computer-implemented method of claim 2 , wherein determining the priority of execution between airspeed and climb is performed by a prioritization function configured to determine the priority of execution in response to a saturation detection based on the at least one saturation check.
4. The computer-implemented method of claim 3 , wherein executing the prioritization function is performed by an outer loop allocation system.
5. The computer-implemented method of claim 2 , wherein performing the at least one saturation check comprises determining if a thrust demand for at least one propeller of the aircraft is saturated.
6. The computer-implemented method of claim 1 , further comprising:
converting, using the at least one hardware processor, the pilot command into at least one of a pitch command, a force command, or a moment command.
7. The computer-implemented method of claim 1 , wherein the characteristics associated with the pilot command further relate to at least one of an acceleration of the aircraft, a pitch of the aircraft, a tilt angle of at least one propeller of the aircraft, an altitude of the aircraft, a rate of change of acceleration of the aircraft, a rate of change of a pitch of the aircraft, a rate of change of a tilt angle of at least one propeller of the aircraft, or rate of a change of altitude of the aircraft.
8. The computer-implemented method of claim 1 , wherein the constraint data is based on at least one of a current state of flight, an integrity threshold of at least one actuator, a failure scenario of at least one effector of the aircraft, or at least one limit from a flight envelope of the aircraft.
9. The computer-implemented method of claim 8 , wherein the current state of flight comprises at least one of an airspeed of the aircraft, an altitude of the aircraft, a propeller tilt angle of at least one propeller of the aircraft, or a pitch angle of the aircraft.
10. The computer-implemented method of claim 1 , wherein the constraint data is defined based on at least one of a flight safety envelope, a physical limit of operation of at least one actuator of the aircraft, a physical limit of operation of at least one effector of the aircraft, or a saturation check.
11. The computer-implemented method of claim 1 , wherein the weights assigned to the characteristics associated with the pilot command are used by an optimization algorithm.
12. The computer-implemented method of claim 1 , wherein the weights assigned to the characteristics associated with the pilot command comprise two weights that are negatively correlated with each other.
13. The computer-implemented method of claim 1 , wherein the priority of execution between airspeed and climb is expressed by a linear function or by a non-linear function.
14. The computer-implemented method of claim 1 , wherein the constraint data includes a minimum airspeed to prevent stall of the aircraft.
15. A system for command prioritization in an aircraft, the system comprising:
a plurality of actuators, each actuator coupled to at least one effector; and
at least one processor configured to:
receive a pilot command;
analyze the pilot command to determine characteristics associated with the pilot command, the characteristics relating to airspeed and climb of an aircraft;
assign weights to characteristics associated with the pilot command based on constraint data;
determine a priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command;
calculate a correction factor based on the determined priority;
update the characteristics associated with the pilot command by applying the correction factor to the characteristics; and
generate at least one actuator command to control the aircraft based on the updated characteristics associated with the pilot command.
16. The system of claim 15 , wherein the at least one processor is further configured to:
perform at least one saturation check on the pilot command; and
calculate a command limit base on the at least one saturation check.
17. The system of claim 16 , wherein the at least one processor is configured to execute a prioritization function to determine the priority of execution between airspeed and climb in response to a saturation detection based on the at least one saturation check.
18. The system of claim 16 , wherein the at least one processor is configured to perform the at least one saturation check by determining if a thrust demand for at least one propeller of the aircraft is saturated.
19. The system of claim 15 , wherein the at least one processor is configured to convert pilot command into at least one of a pitch command, a control input, a force command, or a moment command.
20. A computer-implemented method for controlling flight of an aircraft, the method comprising:
receiving, using at least one hardware processor, one or more control inputs;
determining, using the at least one hardware processor, one or more constraints based on an engine status of each engine of the aircraft and an aircraft configuration;
computing, using the at least one hardware processor, a weighting factor for each control input of the received one or more control inputs;
computing, using the at least one hardware processor, a set of actuator commands based on the received one or more control inputs, one or more constraints, and the weighting factor for each control input;
generating, using the at least one hardware processor, one or more state parameter commands based on the computed set of actuator commands, the one or more state parameter commands comprising at least one force command or attitude command; and
controlling, using the at least one hardware processor, one or more flight control effectors of the aircraft based on the generated one or more state parameter commands.
21. The computer-implemented method of claim 20 , wherein the weighting factor for each control input is based on a state of flight of the aircraft.
22. The computer-implemented method of claim 20 , wherein receiving at least one control input comprises receiving, using the at least one hardware processor, at least one of a longitudinal control input or a vertical control input.
23. The computer-implemented method of claim 20 , wherein the one or more constraints are dynamic and based on at least one of an integrity threshold of at least on actuator of the aircraft, a failure scenario of at least one effector of the aircraft, or at least one limit from a flight envelope of the aircraft.
24. The computer-implemented method of claim 20 , wherein the generating a set of actuator commands comprises:
computing, using the at least one hardware processor, a Jacobian matrix indicative of force and moment changes with respect to each control input;
generating, using the at least one hardware processor, a set of actuator displacement vectors using a pseudo-inverse matrix of the Jacobian matrix; and
solving, using the at least one hardware processor, a minimization problem to produce a set of optimized actuator commands for controlling the one or more flight control effectors.
25. The computer-implemented method of claim 24 , wherein the solving the minimization problem to produce the set of optimized actuator commands further comprises solving, using the at least one hardware processor, a quadratic programming problem to minimize a cost function output associated with the set of actuator commands.
26. The computer-implemented method of claim 24 , wherein the computing of the Jacobian matrix is based on at least one computerized aircraft model, wherein the at least one computerized aircraft model is based on an aircraft configuration and flight conditions of the aircraft.
27. The computer-implemented method of claim 20 , wherein the method is performed by at least one outer loop allocation function.
28. A flight control system for outer loop allocation in an aircraft, the system comprising:
a plurality of actuators, each actuator coupled to at least one effector; and
at least one processor configured to:
receive at least one control input;
determine one or more constraints based on an engine status of each engine of the aircraft and an aircraft configuration;
compute a weighting factor for each control input of the received one or more control inputs;
compute one or more forces and aircraft state parameters based on the received one or more control inputs, one or more constraints, and the weighting factor for each control input, the one or more aircraft state parameters comprising at least one force or aircraft attitude;
generate a set of actuator commands based on the computed one or more forces and aircraft state parameters; and
control one or more flight control effectors of the aircraft based on the generated set of actuator commands.
29. The system of claim 28 , further comprising memory configured to store an aircraft model database.
30. The system of claim 29 , wherein the at least one processor is further configured to:
compute a Jacobian matrix indicative of force and moment changes with respect to each control input;
generate a set of actuator displacement vectors using pseudo-inverse matrix of the Jacobian matrix; and
solve a minimization problem to produce a set of optimized actuator commands for controlling one or more flight control effectors.