Method of load shedding in aircraft and controller

Patent metadata

Field	Value
Publication number	US-9735578-B2
Application number	US-201414339012-A
Country	US
Kind code	B2
Filing date	Jul 23, 2014
Priority date	Aug 7, 2013
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

To properly execute load shedding in an aircraft to maintain power supply to more devices. A method of load shedding includes a failure detection step of detecting a failure in a generator, and a load-shedding step. The load-shedding step includes determination step, and execution step, respectively, the determination step in which the load shedding is determined to be needed if the state where a power consumption exceeds a power-generation capacity continues for a monitoring time, and the execution step in which the load shedding is executed step-by-step while advancing a priority given to a target device until the power consumption falls below the power-generation capacity.

First claim

What is claimed is:

1. A method of load shedding in an aircraft, being a method of load shedding to cut off supply of power to a plurality of target devices selected from a device group, the power generated by generators included in the aircraft and supplied to the device group, the method of load shedding comprising:
a failure detection step of detecting a failure hindering the generator from generating; and
a load-shedding step, after the failure is detected in the failure detection step, of executing the load shedding on the basis of determination of necessity of the load shedding, wherein
the load-shedding step includes:
a first period load-shedding step, a processing time of which is in units of a predetermined first period;
a second period load-shedding step, a processing time of which is in units of a second period longer than the first period;
a determination step of determining that the load shedding is needed on the basis that a state where power consumption consumed by the devices exceeds a predetermined power-generation capacity continues for a predetermined monitoring time; and
an execution step of executing, if the load shedding is determined to be needed in the determination step, the load shedding step-by-step while advancing a priority given to the target devices until the power consumption falls below the power-generation capacity;
wherein in the first period load-shedding step, the power-generation capacity is set at a capacity in accordance with a property of the generators associated with the second period, and
in the second period load-shedding step, the power-generation capacity is set at a capacity in accordance with a stationary property of the generators.

2. The method of load shedding in the aircraft according to claim 1 , wherein
in the execution step,
the load shedding is executed until the power consumption falls below a failure period capacity set at a value lower than the power-generation capacity.

3. The method of load shedding in the aircraft according to claim 1 , the method of load shedding further comprising
an auxiliary power unit activation step, after the failure is detected in the failure detection step, of activating an auxiliary power unit including a generator, wherein
a process of the load-shedding step is interrupted when the generator of the auxiliary power unit starts generating power upon completion of an activation of the auxiliary power unit.

4. The method of load shedding in the aircraft according to claim 1 , wherein
the power supply to the target devices that have already been subjected to the load shedding is resumed when a capacity of the power is recovered.

5. The method of load shedding in the aircraft according to claim 1 , further comprising a monitoring step for monitoring the power consumption consumed by the devices,
wherein the monitoring step is conducted after the failure hindering the generator from generating is detected in the failure detection step and prior to the load-shedding step.

6. A method of load shedding in an aircraft, being a method of load shedding to cut off supply of power to a plurality of target devices selected from a device group, the power generated by generators included in the aircraft and supplied to the device group, the method of load shedding comprising:
a failure detection step of detecting a failure hindering the generator from generating; and
a load-shedding step, after the failure is detected in the failure detection step, of executing the load shedding on the basis of determination of necessity of the load shedding, wherein
the load-shedding step includes:
a first period load-shedding step, a processing time of which is in units of a predetermined first period;
a second period load-shedding step, a processing time of which is in units of a second period longer than the first period;
a determination step of determining that the load shedding is needed on the basis that a state where power consumption consumed by the devices exceeds a predetermined power-generation capacity continues for a predetermined monitoring time; and
an execution step of executing, if the load shedding is determined to be needed in the determination step, the load shedding step-by-step while advancing a priority given to the target devices until the power consumption falls below the power-generation capacity;
wherein in the first period load-shedding step, the power-generation capacity is set at a capacity in accordance with a property of the generators associated with the second period, and
in the second period load-shedding step, the power-generation capacity is set at a capacity in accordance with a stationary property of the generators, wherein
in the first period load-shedding step,
the monitoring time is set at a time obtained by subtracting a time defined as a time taken for cutting off the power supply to the target devices, from the first period, and
in the second period load-shedding step,
the monitoring time is set at a time obtained by subtracting a time defined as a time taken for cutting off the power supply to the target devices, from the second period.

7. A controller for executing load shedding to cut off supply of power to a plurality of target devices selected from a device group, the power generated by generators included in an aircraft and supplied to the device group, the controller comprising:
a failure detecting section for detecting a failure hindering the generator from generating the power;
a storage section for storing a first monitoring time and a second monitoring time, which correspond to a first predetermined capacity and a second predetermined capacity, respectively, said second monitoring time being longer than said first monitoring time; and
a load shedding section for operating when the failure detecting section detects the failure, wherein the load shedding section includes:
a determining section for determining that the load shedding is needed on the basis that the state where power consumption consumed by the devices exceeds the first or second predetermined power-generation capacity continues for the first or second monitoring time, respectively; and
an executing section for executing, if the determining section determines that the load shedding is needed, the load shedding step-by-step while advancing a priority given to the target devices until the power consumption falls below the power-generation capacity;
wherein, the power-generation capacity corresponding to the first monitoring time is set at a capacity in accordance with a property of the generators associated with the second monitoring time, and
the power-generation capacity corresponding to the second monitoring time is set at a capacity in accordance with a stationary property of the generators.

8. An aircraft comprising the controller according to claim 7 .

9. The controller according to claim 7 , further comprising:
a measuring section for measuring the power consumption consumed by the devices, and
a timer for clocking the predetermined monitoring time.

10. The controller according to claim 9 , wherein
the determining section is configured to monitor the power consumption that is continuously obtained from the measuring section ( 401 ).

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Yoshiguchi Takuya
• Goto Makoto
• Sato Daisuke

Classifications

• H02J3/14 Primary

  by switching loads on to, or off from, the networks, e.g. progressively balanced loading · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• G05F5/00 Primary

  Systems for regulating electric variables by detecting deviations in the electric input to the system and thereby controlling a device within the system to obtain a regulated output · CPC title