Electric system stabilizing system for aircraft

Abstract

An electric system of an aircraft includes a power stabilizing device connected to a primary AC bus and a secondary battery. The secondary battery has a rated voltage which allows the secondary battery to absorb regenerative power from a control surface actuator. Based on a voltage and a frequency in the primary AC bus, charging / discharging of the secondary battery is controlled to stabilize the electric system.

Description

BACKGROUND OF THE INVENTION[0001]1. Field of the Invention[0002]The present invention relates to an electric system stabilizing system for an aircraft. Particularly, the present invention relates to an electric system stabilizing system for an aircraft, which is capable of stabilizing an electric system which includes an AC power supply and a DC power supply and is electrically driven mainly by AC power.[0003]2. Description of the Related Art[0004]Typically, as power systems for an aircraft, three kinds of systems, which are a hydraulic system, a breed air system, and an electric system, are incorporated into the aircraft. The hydraulic system is employed for the operation of landing gears, control surfaces, etc. The breed air system is employed for the operation of air conditioning devices, pressure application devices, de-icing devices, and others, in the interior of the aircraft. The electric system is employed for the operation of electric devices and electronic devices. In rece...

AI Technical Summary

Benefits of technology

The present invention provides an electric system stabilizing system for aircraft that can stabilize the electric system without adding too much weight. The system uses a DC power supply and an AC power supply to supply power to electric devices in the aircraft. The system monitors changes in voltage and frequency in the AC power supply bus and controls the charging and discharging of the DC power supply to stabilize the electric system. This technology is effective at preventing instability in the electrical system of aircraft while avoiding excessive weight.

Problems solved by technology

It is known that with a progress of the MEA, a change (fluctuation) in a power supply voltage tends to occur, and the electric system tends to be unstable.

In addition, the electric power is returned to a generator provided in an engine, and thereby an engine gear box might be adversely affected due to back rush.

Or, if power loads supplied with the electric power from the electric system (devices mounted in the aircraft and supplied with electric power from the electric system) increase temporarily, a significant voltage decrease (drop) might be generated.

However, in the above stated conventional configurations, a weight of the aircraft might probably increase.

Therefore, the size of the controller of the actuator increases and heat generated increases, which causes a need for a large-sized heat radiator.

Because of incorporation of the large-sized controller and the large-sized heat radiator into the aircraft, the weight of the aircraft increases.

In the latter configuration, the size of the AC power generator increases due to the increase in the power generation capacity, and therefore, the weight of the aircraft increases.

Moreover, in the former configuration, although the heat radiator is provided, unnecessary heat generation occurs.

Therefore, the electric system disclosed in Patent Literature 1 intended for an electric system which is electrically driven mainly by DC cannot be applied without some modification to an electric system which is electrically driven mainly by AC.

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