Hybrid electric power distribution and control for an aircraft
A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density, power draw characteristics and/or dissimilar configuration. A primary power unit includes an aircraft engine coupled to an electric motor and a first generator. A secondary power unit is coupled to a second generator. A bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator. A power management controller is configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine.
1. A power system of an aircraft, the power system comprising:
a hybrid energy storage system comprising at least two energy storage subsystems each having a different power-energy density, power draw characteristics and/or dissimilar configuration;
a primary power unit comprising an aircraft engine coupled to an electric motor and a first generator;
a secondary power unit coupled to a second generator;
a bidirectional power converter coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator; and
a power management controller configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine and perform predictive power management by closing one or more contactors based on load predictions for the one or more electric power flows.
2. The power system of claim 1 , wherein the power management controller is operable to detect one or more conditions of the at least two energy storage subsystems and configure the one or more electric power flows.
3. The power system of claim 2 , wherein the power management controller is operable to configure at least one of the one or more electric power flows from a first energy storage subsystem of the at least two energy storage subsystems to charge a second energy storage subsystem of the at least two energy storage subsystems.
4. The power system of claim 3 , wherein the first energy storage subsystem comprises a battery system and a battery management system, the second energy storage subsystem comprises a super/ultra-capacitor, and the bidirectional power converter is operably coupled to the super/ultra-capacitor and the battery management system.
5. The power system of claim 4 , wherein the hybrid energy storage system comprises a third energy storage system comprising an isolated battery pack accessible by the power management controller based on determining that a mode of operation of the aircraft is a ground-based mode of operation or an emergency power mode of operation.
6. The power system of claim 1 , wherein a plurality of aircraft electrical subsystems is operably coupled to the bidirectional power converter and the power management controller is configured to extract power from or provide power to the aircraft electrical subsystems, and the model predictive control is further based on one or more aircraft subsystem power demands.
7. The power system of claim 6 , wherein the aircraft electrical subsystems comprise one or more of an engine subsystem, an aircraft low-voltage DC subsystem, an aircraft high-voltage DC subsystem, and an aircraft AC subsystem.
8. The power system of claim 7 , wherein the power management controller is operable to monitor a state of charge of the hybrid energy storage system, a power request of an engine subsystem control of the engine subsystem, an aircraft subsystem control, and the one or more controllers of the electric motor, the first generator, and the second generator.
9. The power system of claim 8 , wherein the power management controller is operable to:
determine a current status and constraints from the engine subsystem control, the aircraft subsystem control, and the one or more controllers of the electric motor, the first generator, and the second generator;
receive the engine propulsion power demand and data from a plurality of engine sensors;
determine a plurality of desired values for electrical power levels; and
communicate the desired values for electrical power levels to the engine subsystem control, the aircraft subsystem control, and the one or more controllers of the electric motor, the first generator, and the second generator.
10. The power system of claim 9 , wherein the model predictive control determines the electrical power levels by computing a plurality of future step values using a plurality of dynamic equations that model a plurality of subsystems, the current status and constraints, and an objective function based on an error between a requested and an allocation power level or thrust.
11. A method comprising:
interfacing a power management controller with a hybrid energy storage system and one or more controllers of an electric motor, a first generator, and a second generator, wherein the hybrid energy storage system comprises at least two energy storage subsystems each having a different power-energy density and power draw characteristics, and the electric motor and the first generator are coupled to an aircraft engine of a primary power unit and the second generator is coupled to a secondary power unit;
receiving, at the power management controller, an engine propulsion power demand for the aircraft engine; and
performing a model predictive control to dynamically adjust one or more electric power flows through a bidirectional power converter based on the engine propulsion power demand, and perform predictive power management by closing one or more contactors based on load predictions for the one or more electric power flows, wherein the bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator.
12. The method of claim 11 , further comprising:
detecting one or more conditions of the at least two energy storage subsystems; and
configuring the one or more electric power flows based on the one or more conditions of the at least two energy storage subsystems.
13. The method of claim 12 , further comprising:
configuring at least one of the one or more electric power flows from a first energy storage subsystem of the at least two energy storage subsystems to charge a second energy storage subsystem of the at least two energy storage subsystems.
14. The method of claim 13 , wherein the first energy storage subsystem comprises a battery system and a battery management system, the second energy storage subsystem comprises a super/ultra-capacitor, and the bidirectional power converter is operably coupled to the super/ultra-capacitor and the battery management system.
15. The method of claim 14 , wherein the hybrid energy storage system comprises a third energy storage system comprising an isolated battery pack accessible by the power management controller based on determining that a mode of operation of the aircraft is a ground-based mode of operation or an emergency power mode of operation.
16. The method of claim 11 , wherein a plurality of aircraft electrical subsystems is operably coupled to the bidirectional power converter and the power management controller is configured to extract power from or provide power to the aircraft electrical subsystems, and the model predictive control is further based on one or more aircraft subsystem power demands.
17. The method of claim 16 , wherein the aircraft electrical subsystems comprise one or more of an engine subsystem, an aircraft low-voltage DC subsystem, an aircraft high-voltage DC subsystem, and an aircraft AC subsystem.
18. The method of claim 17 , wherein the power management controller is operable to monitor a state of charge of the hybrid energy storage system, a power request of an engine subsystem control of the engine subsystem, an aircraft subsystem control, and the one or more controllers of the electric motor, the first generator, and the second generator.
19. The method of claim 18 , further comprising:
determining a current status and constraints from the engine subsystem control, the aircraft subsystem control, and the one or more controllers of the electric motor, the first generator, and the second generator;
receiving the engine propulsion power demand and data from a plurality of engine sensors;
determining a plurality of desired values for electrical power levels; and
communicating the desired values for electrical power levels to the engine subsystem control, the aircraft subsystem control, and the one or more controllers of the electric motor, the first generator, and the second generator.
20. The method of claim 19 , further comprising:
determining the electrical power levels by computing a plurality of future step values using a plurality of dynamic equations that model a plurality of subsystems, the current status and constraints, historical energy consumption, and an objective function based on an error between a requested and an allocation power level or thrust.