High-reliability solar cell array shunting adjusting system and method
A technology of solar cell array and shunt adjustment, which is applied in the power supply system of aerospace vehicles, equipment for space navigation, and aircraft for space navigation, etc. It can solve problems affecting the safety of the entire star, overcharging of battery packs, and affecting mission safety, etc. To achieve the effect of ensuring safety, bus voltage stability and high reliability
Active Publication Date: 2021-07-09
AEROSPACE DONGFANGHONG DEV LTD
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Problems solved by technology
[0003] However, due to the timing requirements of the control logic, there will be some single-point situations in the shunt regulation circuit. Once a single-point failure occurs, the stability of the primary power bus will not be guaranteed, and it will even affect the safety of the entire star. Therefore, generally the solar battery The array is divided into multiple sub-arrays to reduce the impact of single point failures. For spacecraft with low long-term power consumption, there is still the danger of battery pack overcharging; for spacecraft with insufficient output power margin of solar arrays, May affect mission safety
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[0030] The present invention will be further described below in conjunction with the description of the drawings and specific embodiments.
[0031] Such as Figure 1 to Figure 5As shown, a highly reliable shunt adjustment system for solar cell arrays includes a forced shunt signal shielding circuit 101, a forced shunt signal generating circuit 102, a shunt drive circuit 103, and a shunt circuit 104. The output terminals of the forced shunt signal shielding circuit 101 are respectively connected to The input ends of the forced shunt signal generating circuit 102 and the shunt driving circuit 103 are connected, and the output ends of the forced shunt signal generating circuit 102 and the shunt driving circuit 103 are connected to the input end of the shunt circuit 104 .
[0032] The function of the shunt circuit 104 is to shunt and adjust the output power of the solar battery array when the bus voltage rises to a set value, so as to ensure the stability of the bus voltage.
[0...
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The invention provides a high-reliability solar cell array shunting adjusting system. The system comprises a forced shunting signal shielding circuit, a forced shunting signal generating circuit, a shunting driving circuit and a shunting circuit, and is characterized in that the output end of the forced shunting signal shielding circuit is respectively connected with the input ends of the forced shunting signal generating circuit and the shunting driving circuit, and the output ends of the forced shunting signal generating circuit and the shunting driving circuit are both connected with the input end of the shunting circuit. The invention further provides a high-reliability solar cell array shunting adjusting method. The system has the advantages that: under the condition that the solar cell array shunting regulation electric control circuit breaks down, the stability of the bus voltage can still be guaranteed, the storage battery pack cannot be overcharged, and then the safety of a spacecraft is guaranteed.
Description
technical field [0001] The invention relates to a solar battery array, in particular to a highly reliable solar battery array shunt regulation system and method. Background technique [0002] The solar battery array is the main power supply of the spacecraft. When the sun shines, the output power supplies power to the spacecraft’s electrical load on the one hand, and charges the battery pack on the other hand. When the battery pack is fully charged, the solar battery array Enter the shunt adjustment state, thus ensuring the stability of the primary power bus. [0003] However, due to the timing requirements of the control logic, there will be some single-point situations in the shunt regulation circuit. Once a single-point failure occurs, the stability of the primary power bus will not be guaranteed, and it will even affect the safety of the entire star. Therefore, generally the solar battery The array is divided into multiple sub-arrays to reduce the impact of single point...
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IPC IPC(8): B64G1/44
CPCB64G1/443
Inventor 吕红强张博温田贤樟郭泉良王妍郭苗苗
Owner AEROSPACE DONGFANGHONG DEV LTD