Power supply source control device for airplane

Abstract

The invention relates to a power supply source control device for an airplane, and belongs to the field of aviation electronics. The power supply source control device comprises a shell, a generator arranged in the shell, an excitation control module, an excitation storage battery, a current-limiting insurance 5A and a master control device arranged outside the shell, wherein the master control device comprises a storage battery interface, a ground power interface, a relay J1, a relay J2 and a relay J3 and a bus bar; coils of the relay J1 and the relay J2 are connected between the storage battery interface and the ground in parallel; a normally open contact J1-1 of the relay J1 is connected to the bus bar; the bus bar is connected with the coil of the relay J3 and one of power supply ends of the bus bar is connected to the excitation control module through an excitation control protection switch K1; the excitation control module is connected with a corresponding pin of the generator; the excitation storage battery, a work indicating lamp L and the current-limiting insurance 5A are connected in series and then connected to the power supply end of the excitation control module; and a positive electrode of a power supply of the generator is connected with a normally open contact J3-1 of the relay J3 through a switch S1. The power supply source control device for the airplane has the advantages of being low in cost, high in reliability, good in heat dissipation performance, safe and stable.

Description

technical field [0001] The invention relates to a power supply source control device for aircraft, which belongs to the field of aviation electrics. Background technique [0002] The power consumption inside the aircraft is generally distributed by a special power control device. The internal structure of the original power control device is too compact, which makes it very difficult to replace components and has poor maintainability. The heat dissipation in the body is not smooth, and it is easy to be damaged, and the power control device is an imported part, the price is high, and frequent damages have caused great economic losses. In actual use, the excitation current of the power control device lacks relevant protection, and it does not have a separate power supply. With the failure of the internal power supply of the aircraft, it will not be able to be used, which makes the independence of each power supply circuit worse. Contents of the invention [0003] The techni...

AI Technical Summary

Problems solved by technology

[0002] The power consumption inside the aircraft is generally distributed by a special power control device. The internal structure of the original power control device is too compact, which makes it very difficult to replace components and has poor maintainability. The heat dissipation in the body is not smooth, and it is easy to be damaged, and the power control device is an imported part, the price is high, and frequent damages cause large economic losses

In the actual use process, the excitation current of the power control device lacks relevant protection, and it does not have a separate power supply. With the failure of the internal power supply of the aircraft, it will not be able to be used, which makes the independence of each power supply circuit worse.

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