Residual magnetism control expansion satellite solar wing and test verification method thereof

Abstract

The invention discloses a residual magnetism control expansion satellite solar wing and a test verification method thereof. The residual magnetism control expansion satellite solar wing comprises a solar battery power supply circuit including a solar wing frontage, a connection cable connected with a solar wing backside and an electric connector; serial-connection solar battery unit circuits are configured into a figure '8' structure, every four serial-connection solar battery unit circuits form a mapping unit with double mirror surfaces, and a current-dividing circuit formed by in parallel connecting multiple serial-connection solar battery unit circuits is symmetric about upper and lower parts of the solar wing frontage; positive and negative wires of each solar battery unit circuit are led out from the same point and paired contacts of positive and negative wires led out from the same current-dividing circuit are adjacently arranged on the electric connector on the solar wing backside. Test simulation specimens are manufactured, wherein the surface current of the serial-connection solar battery unit circuit is simulated by the line current of the lead and each lead is in series connected with two resistors with the resistance value of 2omega and the rated power of 1W, so that the current passing through each simulation lead in the same current-dividing circuit is balanced. The test result indicates that the magnetic induction intensity at the position which is 1m far away from the solar wing is about 1nT during electricity generation of the solar wing.

Description

technical field [0001] The invention relates to a deployable satellite solar wing designed with residual magnetism control and a test verification method, belonging to the field of satellite solar wing residual magnetism control. Background technique [0002] The satellite power supply system is generally composed of solar wings, battery packs, and other regulation and control circuits. The solar wing is the only power generation device for satellites in orbit. It supplies power to the load in the illuminated area and charges the battery pack at the same time. The excess output current is from the first stage. The shunt circuit begins to shunt the current sequentially step by step. Among them, the 7-stage shunt circuit and the 8-stage shunt circuit are connected to both ends of the battery pack through the switch tube as a fast charging array, and directly charge the battery pack during high-current charging. Turn on charging and restore power to the bus. [0003] Generally...

AI Technical Summary

Problems solved by technology

[0009] (1) When installing the solar cells on the front of the solar wing, the main considerations are reliability and safety, as well as improving the layout coefficient, that is, the area of ​​the solar cells installed on the solar wing substrate per unit area, and the surplus generated during on-orbit operation. (2) The design of the cables and electrical connectors on the back of the solar wing only considers reliability and safety, and the residual magnetism generated during orbital work is relatively large; (3) In previous models, due to the magnetic The cleanliness will not have high requirements, and due to the limitation of cost and test conditions, the magnetic test of the real product of the solar wing cannot be carried out. The remanent magnetic moment of the unfolded solar wing is only theoretically calculated, but the theoretical calculation does not represent the actual value.

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