Spaceborne integrated storage battery discharge switching circuit

Abstract

The invention relates to a spaceborne integrated storage battery discharge switching circuit, which comprises a switching circuit, a signal control circuit and a surge current control circuit, and is characterized in that the switching circuit is connected between a storage battery pack and a discharge circuit in series, the switching circuit comprises a first discharge switch, a second discharge switch and a third discharge switch which are connected in parallel, a source electrode of each discharge switch is connected with the storage battery pack, and a drain electrode of each discharge switch is connected with the discharge circuit; an input end of the signal control circuit is connected with a switching control signal, an output end of the signal control circuit is connected with a grid electrode of the first discharge switch in the switching circuit, and the signal control circuit is used for controlling on-off of the first discharge switch in the switching circuit; and an input end of the surge current control circuit is connected with the discharge circuit, an output end of the surge current control circuit is connected with a grid electrode of the second discharge switch and a grid electrode of the third discharge switch in the switching circuit, and the surge current control circuit is used for controlling on-off of the second discharge switch and the third discharge switch in the switching circuit and eliminating surge current. The spaceborne integrated storage battery discharge switching circuit not only improves the reliability and the power mass ratio of a storage battery pack discharge switching circuit and reduces the volume and the weight of the system, but also improves the integrated design level of a power supply subsystem.

Description

technical field [0001] The invention relates to the field of aerospace power control, in particular to an integrated storage battery discharge switch circuit for space. Background technique [0002] The power controller is an important part of the power supply subsystem of satellites and other aerospace vehicles. It provides a stable primary bus for the entire star. Its main functions are: solar battery S3R switch shunt control; battery pack charging and discharging control; Acquisition and measurement of battery voltage, current, temperature and other parameters; power supply test interface; battery balance management. The weight of the satellite power supply generally accounts for 30%-40% of the weight of the entire satellite, which seriously restricts the carrying capacity of the satellite platform and cannot meet the demand for large loads. In order to support the application of new payload technology and products, and reduce the constraints on the payload in terms of p...

AI Technical Summary

Problems solved by technology

[0005] 1. Due to the inherent mechanical properties of the relay, failure modes such as contact disconnection, contact bonding, coil open circuit, and coil short circuit may occur in a mechanical environment, thereby reducing the reliability of the system

[0006] 2. With the continuous increase of the power demand of the whole star, the current flowing through the two ends of the BCRB relay contact is also continuously increased, which makes it difficult to select a relay that meets the reliability design requirements

[0007] 3. The volume and weight of the power relay are relatively large, which is not conducive to the miniaturization and integration design of the power subsystem

Images