Multi-functional LRM performing SSPC and ELCU functions
AssigneeHoneywell International Inc.
InventorsRandy J. Fuller, Zhenning Z. Liu, Milind Ghanekar, Ted J. Gayowsky
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Abstract
On an aircraft, primary power distribution control and secondary power distribution control may be performed with a single line replaceable module (LRM) having an integrated architecture. The LRM may be provided with trip engines that are based on digital signal processors (DSP's). The DSP's may be programmed to allow the trip engines to perform either ELCU functions or SSPC functions. Use of the single LRM precludes a need for complex circuitry that might otherwise be required to coordinate prior-art independent ELCU and SSPC controls.
Claims12
A power distribution control module comprising:
- at least two channels for performing power distribution control;
- at least two outputs from the power distribution control module, each of the at least two outputs corresponding to each of the at least two channels;
- at least one of the channels configured to perform primary power distribution control to supply power, via a first of the at least two outputs, at a first amperage;
- at least one of the channels configured to perform secondary power distribution control to supply power, via a second of the at least two outputs, at a second amperage, the second amperage being lower than the first amperage;
- a primary power distribution contactor in a primary power feeder;
- a first power switch connected to directly interrupt current in a secondary power feeder;
- and
- a second power switch connected to indirectly interrupt current in a primary power feeder by disconnecting the primary power distribution contactor.
A line replaceable module (LRM) for controlling power distribution in an aircraft comprising;
- a trip engine for controlling secondary power distribution in the aircraft;
- and
- a trip engine for controlling primary power distribution in the aircraft;
- wherein
- the trip engines having the same electronic architecture, and wherein
- at least one of the trip engines comprises a microprocessor device comprising;
- a trip engine logic block;
- and
- a configuration block;
- the configuration block being programmed with aircraft electrical load parameters;
- the trip engine logic block being programmed with a trip algorithm and being interconnected to a current feedback connector;
- the trip engine being interconnected with a solid state power switch;
- the solid state power switch being connected to directly interrupt current in a secondary power feeder;
- the solid state power switch being operated responsively to a determination, by the microprocessor device, that current flow in the power feeder exceeds at least one of the aircraft electrical load parameters programmed in the configuration block;
- whereby the trip engine provides circuit breaker functionality that is coordinated with the aircraft load parameter.
A method for controlling power distribution in a vehicle, comprising the steps of:
- monitoring primary and secondary power load information;
- collecting the primary and secondary power load information in processors having a common architecture;
- comparing the collected load information with desired parameters in the processors;
- controlling primary power distribution with a primary power distribution trip engine in response to the comparison;
- controlling secondary power distribution with a secondary power distribution trip engine in response to the comparison;
- directly interrupting current in a secondary power feeder with a secondary power distribution solid state power switch interconnected with the secondary power distribution trip engine;
- and
- indirectly interrupting current in a primary power feeder with a primary power distribution contactor interconnected with the primary power distribution trip engine.
Dependencies are inferred from the claim text.