Aircraft electric power system
An aircraft electric power system provided in an aircraft includes a predetermined DC power supply bus for supplying electric power to a load. The DC power supply bus is configured to always be connected to two or more types of power supply devices having different forms.
1. An aircraft electric power system provided in an aircraft, comprising:
a predetermined DC power supply bus for supplying electric power to a load,
wherein the DC power supply bus is configured to always be connected to two or more types of power supply devices having different forms;
a main power unit which is provided in one of the power supply devices and is driven by an engine for applying a thrust force to the aircraft;
an electricity storage control device which is provided in another of the power supply devices and is capable of storing and discharging electricity;
an electricity storage control device which controls the electricity storage device,
wherein the electricity storage control device controls an operation of the electricity storage device in accordance with a state of power consumption by one or more loads connected to the DC power supply bus.
2. The aircraft electric power system according to claim 1 ,
wherein the electricity storage control device can cause the electricity storage device to perform an electricity discharging operation if necessary electric power required by the one or more loads exceeds a predetermined value.
3. The aircraft electric power system according to claim 1 ,
wherein the electricity storage control device can cause the electricity storage device to perform an electricity storing operation if necessary electric power required by the one or more loads is smaller than or equal to a predetermined value.
4. The aircraft electric power system according to claim 1 ,
wherein a plurality of the predetermined DC power supply buses are provided, and
one of the predetermined DC power supply buses and another of the predetermined DC power supply buses are connected to each other such that electric power can be transmitted and received therebetween.
5. The aircraft electric power system according to claim 4 ,
wherein one of the predetermined DC power supply buses is a DC power supply bus that is connected only to a flight control system for supplying electric power to a flight control device for controlling a flight of the aircraft.
6. The aircraft electric power system according to claim 4 ,
wherein one of the predetermined DC power supply buses and another of the predetermined DC power supply buses are connected to each other such that electric power can be transmitted and received therebetween, via an electricity storage device capable of storing and discharging electricity.
7. The aircraft electric power system according to claim 6 ,
wherein the electricity storage device includes a flywheel battery.
8. The aircraft electric power system according to claim 6 ,
further comprising an electricity storage control device for controlling the electricity storage device,
wherein the electricity storage control device can operate the electricity storage device so as to distribute electric power from a DC power supply bus among the predetermined DC power supply buses that has a relatively larger reserve capacity of electric power distribution to the electricity storage device, and can also cause electric power to be output from the electricity storage device to a DC power supply bus among the predetermined DC power supply buses that has a relatively smaller reserve capacity of electric power distribution.
9. The aircraft electric power system according to claim 1 ,
wherein one of the power supply devices includes a plurality of main power units driven by an engine for applying a thrust force to the aircraft, and
the main power units are connected to the DC power supply bus.