Aircraft electrical system
A voltage converter for an aircraft electrical system includes an input power line configured to receive input electrical power, an output power line configured to supply output electrical power to aircraft loads, conversion circuitry, and a controller. The conversion circuitry is configured to convert the input electrical power to supply the output electrical power based on one or more control parameters. The controller is configured to receive data relating to the aircraft loads and modify at least one control parameter based on the data.
1. A voltage converter for an aircraft electrical system, comprising:
an input power line configured to receive input electrical power;
an output power line configured to supply output electrical power to aircraft loads;
conversion circuitry; and
a controller;
wherein the conversion circuitry is configured to convert the input electrical power to supply the output electrical power based on one or more control parameters;
wherein the controller is configured to receive data relating to the aircraft loads and modify at least one control parameter based on the data;
wherein the controller is configured to receive the data relating to the aircraft loads from a central computer of the aircraft electrical system.
2. The voltage converter of claim 1 , wherein the data includes the state of the aircraft loads, wherein the state is either connected or disconnected.
3. The voltage converter of claim 1 , wherein the aircraft loads comprise an electric propulsion load.
4. The voltage converter of claim 1 , wherein the aircraft loads comprise an ancillary load.
5. The voltage converter of claim 1 , wherein the controller is configured to determine the capacitance of the aircraft loads based on the data and modify at least one control parameter based on the determined capacitance.
6. The voltage converter of claim 1 , wherein the at least one control parameters comprises at least one of: a proportional constant value, an integral constant value, and a differential constant value.
7. The voltage converter of claim 1 , wherein the controller is further configured to determine the at least one control parameter by using the data and a lookup table.
8. The voltage converter of claim 1 , wherein the input electrical power is an alternating current supplied by a generator, and the conversion circuitry is configured to rectify the alternating current into direct current to convert the input electrical power to supply the output electrical power.
9. The voltage converter of claim 1 , wherein the input electrical power is an input direct current supplied by a battery, and the conversion circuitry is configured to regulate the input direct current to an output direct current to convert the input electrical power to supply the output electrical power.
10. The voltage converter of claim 1 , wherein the aircraft loads are one or more of: a fan configured to propel the aircraft, an flight control surface, and a heating system.
11. The voltage converter of claim 1 , wherein the data relating to the aircraft loads comprises a state of a circuit breaker connected between one of the aircraft loads and the output power line, the circuit breaker configured to activate in the event of a failure of the respective aircraft load.
12. An aircraft electrical system comprising:
a voltage converter as claimed in claim 1 .
13. A hybrid electric aircraft comprising:
an aircraft electrical system as claimed in claim 12 .
14. A method of controlling a voltage converter for an aircraft electrical system, the method comprising:
receiving input electrical power on an input power line;
supplying output electrical power to aircraft loads on an output power line;
converting the input electrical power using conversion circuitry to supply the output electrical power based on one or more control parameters; and
receiving data relating to the aircraft loads and modifying at least one of the control parameters based on the said data;
wherein the data relating to the aircraft loads comprises a state of a circuit breaker connected between one of the aircraft loads and the output power line, the circuit breaker configured to activate in the event of a failure of the respective aircraft load.
15. A voltage converter for an aircraft electrical system, comprising:
an input power line configured to receive input electrical power;
an output power line configured to supply output electrical power to aircraft loads;
conversion circuitry; and
a controller;
wherein the conversion circuitry is configured to convert the input electrical power to supply the output electrical power based on one or more control parameters;
wherein the controller is configured to receive data relating to the aircraft loads and modify at least one control parameter based on the data;
wherein the controller is configured to determine the capacitance of the aircraft loads based on the data and modify at least one control parameter based on the determined capacitance.
16. An aircraft electrical system comprising:
a voltage converter as claimed in claim 15 .
17. A hybrid electric aircraft comprising:
an aircraft electrical system as claimed in claim 15 .
18. The voltage converter of claim 15 , wherein the data includes the state of the aircraft loads, wherein the state is either connected or disconnected.
19. The voltage converter of claim 18 , wherein the aircraft loads comprise an electric propulsion load.
20. The voltage converter of claim 15 , wherein the aircraft loads comprise an ancillary load.