A dual-bus solar array power redundancy expansion device
By establishing a power interconnection channel between the satellite's dual-bus solar arrays and utilizing a redundant extended control system and step-down interconnection technology, the problem of platform malfunction caused by abnormal power of the solar arrays during satellite operation in orbit was solved, thereby improving the power supply reliability and power redundancy expansion capability of the satellite platform.
CN115714578BActive Publication Date: 2026-05-26AEROSPACE DONGFANGHONG DEV LTD
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AEROSPACE DONGFANGHONG DEV LTD
- Filing Date
- 2022-11-02
- Publication Date
- 2026-05-26
Smart Images
Figure CN115714578B_ABST
Abstract
This invention provides a dual-bus solar array power redundancy expansion device, comprising solar array SAS1, solar array SAS2, a first shunt module, a first push-pull circuit, a redundancy expansion control system, a first voltage divider circuit, a second shunt module, a second push-pull circuit, a second voltage divider circuit, a hysteresis comparator, a fourth transistor, a first operational amplifier, and a second operational amplifier. One end of solar array SAS1 is grounded, and the other end of solar array SAS1 is connected to the first shunt module, the redundancy expansion control system, the first voltage divider circuit, and the +42V power bus. One end of solar array SAS2 is grounded, and the other end of solar array SAS2 is connected to the second shunt module, the redundancy expansion control system, the second voltage divider circuit, and the +28V power bus. The beneficial effect of this invention is that it establishes a power interconnection path between two bus systems, improving the reliability of the satellite power system.
Need to check novelty before this filing date? Find Prior Art
Citation Information
Patent Citations
Dynamically reconfigurable photovoltaic system
CN104781744A
Spaceborne solar battery array output power shunt control circuit
CN109710019A