Spacecraft power supply system and control method thereof

Abstract

The invention discloses a spacecraft power supply system and a control method thereof, the spacecraft system comprises a power supply module, a storage battery, a charging adjustment module, a discharging adjustment module, a voltage error amplification circuit and a battery charging management circuit, and the voltage error amplification circuit is used for controlling the adjustment of bus voltage. The battery charging management circuit is used for controlling the adjustment of the output power of the charging adjustment circuit; according to the control method of the spacecraft power supply system, voltage ranges of main error amplification signals MEA output by a voltage error amplification circuit are different; and the power supply system works in three different modes: an illuminator shunt regulation circuit stabilized bus voltage function working domain, a shadow period discharge regulation circuit stabilized bus voltage function working domain and a dead zone. The novel spacecraft power supply system only experiences one dead zone range, the bus dynamic response speed of the power supply system can be effectively improved, and the design complexity of a control system ofa charging adjustment circuit is greatly simplified.

Description

technical field [0001] The invention relates to the field of space power supplies, in particular to a spacecraft power supply system and a control method thereof. Background technique [0002] At present, most spacecraft power systems still use the solar array-battery power system. When the spacecraft is in the light period, it relies on solar panels to absorb solar energy to supply power to the spacecraft load and charge the battery. At the same time, the excess energy is shunted and adjusted through the power system. The circuit is short-circuited and returned to the solar battery array. When the spacecraft is in the shadow period, it relies on the discharge of the battery to supply power to the spacecraft load. [0003] In order to improve the control accuracy and response speed of the spacecraft power system bus, most power systems adopt a unified MEA control strategy, and the power system works in different modes according to the voltage range of the MEA. It is general...

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Problems solved by technology

[0006] 1) The design of the charge regulation circuit control system is complex and has certain requirements for the characteristics of the power topology. In addition to meeting the general battery constant current and constant voltage charge control system, when the power supply system works in the charging domain, the charge regulation circuit needs to design a separate For the control system loop of the stable bus function, the design of the charging control system is relatively complicated;

[0007] 2) When the spacecraft power system transitions between the light period and the shadow period, the 3-domain transition experiences 2 dead zone voltages, and the dynamic response speed of the bus voltage of the power system is relatively slow

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