Aircraft power source control device

Abstract

The invention relates to a power supply source control device for aircraft, which belongs to the field of aviation electrics, and includes a casing, a generator arranged in the casing, an excitation control module, an excitation storage battery, a current-limiting insurance 5A, and a main control device arranged outside the casing ;The main control device includes battery interface, ground power interface, relay J1~relay J3 and bus bar; the coils of relay J1 and relay J2 are connected in parallel between the battery interface and ground, and the normally open contact J1‑1 of relay J1 is connected to the bus The bus bar is connected to the coil of the relay J3 and one of the power terminals of the bus bar is connected to the excitation control module through the excitation control protection switch K1; the excitation control module is connected to the corresponding pin of the generator, the excitation battery and the working indicator light L It is connected in series with the current-limiting fuse 5A and then connected to the power supply terminal of the excitation control module; the positive pole of the power supply of the generator is connected to the normally open contact J3-1 of the relay J3 through the switch S1. The invention has the advantages of low cost, high reliability, good heat dissipation and safety and stability.

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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