Aircraft power supply control system

Abstract

The invention relates to an aircraft power supply control system, which belongs to the technical field of aircraft electrical systems and comprises a control device, a first relay, a second relay, an external power supply, a main battery, a first generator armature output power supply, a second generator armature output power supply and a direct current bus, the external power supply, the main battery and the first generator armature output power supply all supply power to the DC bus; the direct-current bus is directly connected with a stable working condition load; an armature output power supply of the second generator is connected with the high-power variable-working-condition load; coil control ends of the first relay and the second relay are connected with the control equipment and are used for realizing switching actions according to a control instruction sent by the control equipment; the first relay is connected between the DC bus anode and the second generator armature output power supply anode, and the second relay is connected between the DC bus cathode and the second generator armature output power supply cathode. According to the control system, stable power supply is realized, and detection of the rotating speed signal acquisition circuit is facilitated.

Description

technical field [0001] The invention relates to the technical field of aircraft electrical systems, in particular to an aircraft power supply control system. Background technique [0002] During the long-time flight of the aircraft in the air cruise stage, a continuous power supply is required to supply power to the electronic equipment on the aircraft. During long-duration flights, in order to solve the uninterrupted power supply of key equipment and realize the power supply quality control in the stage of heavy load energy supplementation, a power supply control system solution is required. In order to solve the above requirements, the usual power supply system scheme is to use the engine to drive the generator to generate power to realize the power supply of the power bus. In order to meet the requirements of reliability redundancy and total power capacity expansion, two sets of generator armature windings are usually used for the same generator to output power. Two set...

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Problems solved by technology

[0006] In view of the above analysis, the embodiment of the present invention aims to provide an aircraft power supply control system, which is used to solve the problem that the existing aircraft power supply is disturbed by high-power variable working condition loads, the power supply is unstable, and the rotational speed acquisition circuit cannot be detected during the ground test phase. The problem

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