ELECTRIC POWER SUPPLY METHOD FOR SPACE VEHICLE Russian patent published in 2016 - IPC H02J7/34 

FIELD: electricity.

SUBSTANCE: invention relates to power supply systems (PSS) of spacecrafts (SC). The invention suggests method of spacecraft power supply from solar battery connected by its positive and negative buses to voltage stabiliser, from accumulator battery connected by its positive and negative buses to input of charger and output of discharger. Voltage stabiliser of the solar battery and discharger of the accumulator battery are made as bridge inverters with common transformer with n output windings, where n≥2, and input of the charger is connected to one of output windings of the transformer, while to other (n-1) output windings of the transformer transition communication devices are connected with loads and rated values of output voltage. The solar battery is selected with output voltage in the operating point at the end of life time on the following condition: U_sb≥U_el·m·100/Δ_ess, where U_el is voltage of one photoconverter in the operating point at the end of life time of the solar battery, V; m is a number (permitted) of failed photoconverters in one series circuit; Δ_ess is value of inessential voltage reduction due to failure of certain photoconverters in any series circuit of photoconverters in regard to good-running circuits, %, and lithium-ion battery is selected as the accumulator battery. Besides the accumulator battery is selected with a number of accumulators in the circuit on the basis of the following ratio: W>P_eclipse/(C_acc·U_acc.av)+w, where P_eclipse is maximum power consumption by the load during orbital eclipse period, W·h; C_acc is capacitance of the selected accumulator, A·h; U_acc.av is average discharging voltage of the accumulator, V; w is number (permitted) of failed accumulators in series circuit of accumulators for the accumulator battery. Invention substance is explained by drawings, where in the figure 1, functional power supply diagram for SC with one accumulator battery is provided for implementation of the claimed method.

EFFECT: improvement of specific energy performance and reliability of autonomous power supply system for spacecrafts.

2 cl, 1 dwg