A deep space exploration aircraft power supply system

Abstract

A deep space exploration aircraft power supply system includes a solar battery array, an energy storage battery pack and a power supply control device. The output power of the power supply system topology selects from two independent buses: a semi-regulated BUS1 bus and a non-regulated BUS2 bus. The BUS1 bus mainly supplies a platform with electric power. The BUS2 bus mainly supplies an electric propulsion load with electric power. The solar battery array supplies the semi-regulated bus and the non-regulated bus with power sequentially. The system has high current charging capability. The double bus form optimizes the system topology. The power supply system design has high current charging capability. The power utilization of the solar array in the power supply system is raised.

Description

technical field [0001] The invention belongs to the technical field of space power supply control, in particular to a power supply system suitable for deep space exploration aircraft. Background technique [0002] The power system of deep space exploration aircraft needs to be designed by integrating the characteristics of high-orbit (GEO) satellites and low-orbit (LEO) satellites. Usually, the power system topology (such as "three Neither the "three-domain" S3R system nor the "two-domain" S4R system can well meet the mission of deep space exploration aircraft. The limitation of the traditional "three-domain" S3R system is that it cannot well complete the task of high-current charging in a short period of time. , while the "two-domain" S4R system has the problem of low effective power utilization of the solar array. [0003] The patent document with the patent number 2016107977030 discloses a high-power and high-efficiency satellite power supply system based on high-voltage...

AI Technical Summary

Problems solved by technology

[0002] The power system of deep space exploration aircraft needs to be designed by integrating the characteristics of high-orbit (GEO) satellites and low-orbit (LEO) satellites. Usually, the power system topology (such as "three The traditional "three-domain" S3R system and the "two-domain" S4R system, etc.) cannot well meet the mission of deep space exploration aircraft. , while the "two-domain" S4R system has the problem of low effective power utilization of the solar cell array

[0003] The patent document with the patent number 2016107977030 discloses a high-power and high-efficiency satellite power supply system based on high-voltage and low-voltage double buses. The first solar battery array to the sixth solar battery array in this patent document supply power for 28V electrical loads and nickel-cadmium battery packs , the seventh solar battery array to the eighth solar battery array supply power for 42V electrical loads and lithium-ion battery packs, and the high and low voltage bus system is used to reduce the current density of the system, but the solar battery arrays and electrical loads are grouped in this application document The power supply is fixed and cannot automatically adjust the power supply relationship between the solar cell array and the electric load, so a power system topology needs to be redesigned

Images