Energy system suitable for LEO satellite and control method of energy system

A technology of energy system and control method, which is applied in the direction of control/regulation system, regulation of electric variables, photovoltaic power generation, etc., which can solve the problems of large volume and weight, low reliability, and large system overhead of solar cell arrays, and achieve the elimination of single point Effects of failure, improved reliability, and reduced voltage and current stress

Active Publication Date: 2018-01-12
SHANGHAI INST OF SPACE POWER SOURCES
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Problems solved by technology

Because this method requires a redundant solar cell array, and the solar cell array has a large volume and weight, high cost, and high system overhead, and the reliability of this method is K*(N-1) / N (K is the single-channel reliability) , the reliability is not high

Method used

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  • Energy system suitable for LEO satellite and control method of energy system
  • Energy system suitable for LEO satellite and control method of energy system
  • Energy system suitable for LEO satellite and control method of energy system

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Embodiment Construction

[0035] based on the following Figure 4 ~ Figure 7 Preferred embodiments of the present invention will be described in detail.

[0036] Such as Figure 4 As shown, the present invention provides an energy system suitable for LEO satellites, including: a solar cell array 1 , an MPPT circuit unit 2 , a capacitor array 3 , a battery pack 4 , a satellite platform load 5 and a remote control unit 6 .

[0037] In this embodiment, the capacitor array 3 can use tantalum capacitors to filter the output signal of the MPPT circuit unit; the battery pack 4 can use a lithium-ion battery pack to supplement the insufficient energy of the solar cell array.

[0038] The telemetry / remote control unit collects the voltage and current signals of the solar battery array, MPPT circuit unit, battery pack and load to obtain telemetry values, and outputs relevant remote control signals.

[0039] The solar cell array 1 includes N solar cell array modules (1-1, 1-2, ..., 1-N), and the solar cell array...

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Abstract

The invention relates to an energy system suitable for an LEO satellite and a control method of the energy system. The energy system comprises a solar cell array, an MPPT circuit unit, a storage battery, a capacitor array, a satellite platform load and a remote measuring and controlling unit, wherein the MPPT circuit unit carries out peak power tracking on the solar cell array by three DC-DC conversion modules which are connected in parallel according to a triple redundancecy hot backup mode, the MPPT circuit unit carries out closed-loop control by a majority voting control circuit, and each control circuit generates a driving signal to carry out closed-loop control on the corresponding MPPT circuit according to output voltage signals and output current signals of the solar cell array module and voltage signals and current signals of the storage battery to implement maximum power tracking on the solar cell array module and charging management on the storage battery. The solar cell array is high in utilization rate, high in reliability and low in system cost.

Description

technical field [0001] The invention relates to the field of spacecraft power supply system design, in particular to an energy system suitable for LEO satellites and a control method thereof. Background technique [0002] Low-orbit (LEO) satellites have strong rapid response capabilities, and are increasingly valued by countries. With the rapid development of LEO satellites, the restrictive relationship between the increasing power requirements of LEO satellites and the urgent need to reduce the area of ​​solar arrays to facilitate attitude control has emerged and will become more prominent. The energy system design has the following two Aspects of the problem: [0003] 1. In the solar cell array-battery pack power system, the output power of solar cells is affected by factors such as ambient temperature and radiation, and the peak power point of the output often drifts. LEO satellite loads have high instantaneous power, short orbit period, and many light / earth shadow cycl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J7/35H02J7/00G05F1/67
CPCY02E10/56
Inventor 刘绘莹何小斌刘世超靳洋李阳董宝磊
Owner SHANGHAI INST OF SPACE POWER SOURCES
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