Distributive redundancy type automatic power distribution control system for airplane

Abstract

The invention provides a distributive redundancy type automatic power distribution control system for an airplane. According to the distributive redundancy type automatic power distribution control system, a left power controller is used for monitoring and controlling a left alternating-current power distribution board, a left direct-current power distribution board and an emergency power distribution board through a digital and analog interface; a right power controller is used for monitoring and controlling a right alternating-current power distribution board, a right direct-current power distribution board and an emergency power distribution board through a digital and analog interface; the left and right power controllers feed an operating state of the system back to an upper computer through a 1553B communication data bus and a CAN (Controller Area Network) communication data bus; the left and right power controllers interact information of respective controlled power distribution boards through an ARINC429 bus; and an electric generator controller and a remote power controller transmit operating states of components respectively controlled by the electric generator controller and the remote power controller to the left and right power controllers. The distributive redundancy type automatic power distribution control system has the advantages that a health consultation function is achieved, the reliability and real-time property are improved; and power supply without interruption, fault-tolerant power supply and automatic management of load are realized by a power supply system.

Description

technical field [0001] The invention belongs to the technical field of automatic control, in particular to a distributed redundant aircraft automatic power distribution control system. Background technique [0002] The aircraft automatic power distribution system is mainly composed of the aircraft power distribution network composed of bus bars and terminals, and the power distribution control unit composed of corresponding processors and controllers. The primary power distribution is the part from the generator to the power supply bus bar, and its control unit is the power controller PCU (Power Control Unit); the secondary power distribution is the part from the power supply bus bar to the power distribution bus bar and the load, and its control unit is It is RPDU (Remote Power Distribution Unit). [0003] At present, the automatic power distribution control methods of aircraft are mainly centralized, distributed and centralized and distributed. The centralized au...

AI Technical Summary

Problems solved by technology

The centralized automatic power distribution control system has only one central processor. If the central processor fails, the entire aircraft power supply system will not operate normally, so the reliability and stability of the system are poor; in the distributed automatic power distribution control system Without a unified central processor, it is impossible to regulate the aircraft power system from the system level, and it will be difficult to coordinate and coordinate between remote power distribution units; when the centralized distributed control system centrally controls the complex aircraft power grid, due to the system The large size and complex control algorithm will lead to reduced real-time performance

In the general control mode, it is difficult to achieve a higher level of reliability guarantee for the control of the emergency power distribution center

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