System and method for stabilizing aircraft electrical systems
First Claim
Patent Images
1. An electric system stabilizing system for aircraft, comprising at least:
- an electric system including a DC power supply and an AC power supply as an electric power supply device, and an AC power supply bus connected to the AC power supply, the electric system being configured to supply electric power to at least one electric device mounted in the aircraft; and
a power stabilizing device connected to the AC power supply bus and to the DC power supply, to stabilize an output of the electric power supply device;
wherein the DC power supply is configured to absorb regenerative power from the electric device and transiently supply electric power to the electric device;
wherein the power stabilizing device includes;
a power converter section including a PWM converter; and
a power stabilizing control section for controlling the power converter section;
wherein the power stabilizing control section monitors at least one of a change in a voltage and a change in a frequency in the AC power supply bus, and controls charging/discharging of the DC power supply according to a result of the monitoring, to stabilize the AC power supply bus; and
wherein, when regenerative power occurs in the electric device, the power stabilizing control section causes the electric power to be supplied from the AC power supply bus toward the DC power supply, and charges the DC power supply with the regenerative power to stabilize the AC power supply bus;
wherein the power stabilizing control section measures at least one of the voltage and the frequency in the AC power supply bus and determines that a first-order lag value of a measurement value of at least one of the voltage and the frequency is a target value in control; and
the power stabilizing control section controls charging/discharging of the DC power supply based on a difference between the target value and the measurement value.
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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.
80 Citations
17 Claims
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1. An electric system stabilizing system for aircraft, comprising at least:
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an electric system including a DC power supply and an AC power supply as an electric power supply device, and an AC power supply bus connected to the AC power supply, the electric system being configured to supply electric power to at least one electric device mounted in the aircraft; and a power stabilizing device connected to the AC power supply bus and to the DC power supply, to stabilize an output of the electric power supply device; wherein the DC power supply is configured to absorb regenerative power from the electric device and transiently supply electric power to the electric device; wherein the power stabilizing device includes; a power converter section including a PWM converter; and a power stabilizing control section for controlling the power converter section; wherein the power stabilizing control section monitors at least one of a change in a voltage and a change in a frequency in the AC power supply bus, and controls charging/discharging of the DC power supply according to a result of the monitoring, to stabilize the AC power supply bus; and wherein, when regenerative power occurs in the electric device, the power stabilizing control section causes the electric power to be supplied from the AC power supply bus toward the DC power supply, and charges the DC power supply with the regenerative power to stabilize the AC power supply bus; wherein the power stabilizing control section measures at least one of the voltage and the frequency in the AC power supply bus and determines that a first-order lag value of a measurement value of at least one of the voltage and the frequency is a target value in control; and the power stabilizing control section controls charging/discharging of the DC power supply based on a difference between the target value and the measurement value. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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17. A method of stabilizing an electric system for aircraft, the electric system including a DC power supply and an AC power supply as an electric power supply device, and an AC power supply bus connected to the AC power supply, the electric system being configured to supply electric power to at least one electric device mounted in the aircraft;
- the method comprising;
using as the DC power supply, a DC power supply configured to absorb regenerative power from the electric device and transiently supply electric power to the electric device; monitoring at least one of a change in a voltage and a change in a frequency in the AC power supply bus and controlling charging/discharging of the DC power supply based on a result of the monitoring, thereby stabilizing the AC power supply bus; and when regenerative power occurs in the electric device, causing the electric power to be supplied from the AC power supply bus toward the DC power supply, and charging the DC power supply with the regenerative power to stabilize the AC power supply bus, wherein at least one of the voltage and the frequency in the AC power supply bus is measured and it is determined that a first-order lag value of a measurement value of at least one of the voltage and the frequency is a target value in control; and wherein the charging/discharging of the DC power supply is controlled based on a difference between the target value and the measurement value.
- the method comprising;
Specification