Closed-loop control method for controlling output energy margin of solar array

Abstract

The invention discloses a closed-loop control method for controlling the output energy margin of a solar array, which relates to the field of autonomous management of on-orbit energy of a satellite power supply subsystem. The method comprises the following steps: 1, a satellite coordinate system OXYZ is established; 2, a solar array on the satellite is set to track rotation of the run at an angular velocity omega0 around the Y axis; 3, the lagging angle of the initial solar array is set to be alpha; 4, the output power psa of the solar array in a solar irradiation area at a previous moment iscalculated; 5, the energy margin Wsp of the solar array in an orbit circle is calculated; 6, the Wsp is judged respectively, and whether the solar array energy margin Wsp is in an energy excessive state or a serious power shortage state or an insufficient output energy state is judged; and 7, the solar array is adjusted to realize closed-loop control on the output energy margin of the solar array.Rotation control of the solar array is incorporated into the allocation process of the satellite energy system, and control on the output energy margin of the solar array is realized.

Description

technical field [0001] The invention relates to the field of on-orbit energy autonomous management of a satellite power supply subsystem, in particular to a closed-loop control method for controlling the output energy surplus of a solar cell array. Background technique [0002] The time it takes for a satellite to circle the Earth is the orbital period T r , usually the orbital period includes the shadow time T sw and light time T sun , the shadow time refers to the time during which the satellite is not exposed to sunlight during the orbital period, and the light time refers to the time during which the satellite is exposed to sunlight during the orbital period. [0003] The power subsystem refers to the satellite subsystem that provides energy during the life of the satellite. The satellite power subsystem is generally a solar array-battery system, which is composed of a solar array, a lithium-ion battery pack, and power control equipment. As the only power generation e...

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Problems solved by technology

When the shunt is in the switch adjustment state, the bus ripple will increase, and the pulsating shunt current will affect the electromotive force of the whole star structure, which will cause interference to the high-precision electromagnetic sensitive detection load

[0007] At present, the rotation control of the solar wing is in the charge of the attitude control subsystem of the satellite. Its control goal is to make the solar wing reach the best l

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