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Energy budget method of cubesat sun-synchronous orbit solar battery array

A sun-synchronous orbit and solar cell array technology, applied in computing, electrical digital data processing, instruments, etc., can solve the problems of complex modeling, easy to produce deviations, and large amount of calculations, and achieve the realization of small difficulty, small amount of calculation, The effect of sufficient energy supply

Inactive Publication Date: 2017-12-19
NANJING UNIV OF SCI & TECH
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Problems solved by technology

The modeling of this method is complex, the amount of calculation is large, and it is easy to produce deviations

Method used

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  • Energy budget method of cubesat sun-synchronous orbit solar battery array
  • Energy budget method of cubesat sun-synchronous orbit solar battery array
  • Energy budget method of cubesat sun-synchronous orbit solar battery array

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Embodiment Construction

[0034] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0035] combine figure 1 , the method for estimating the energy of the cubic star sun-synchronous orbit solar cell array of the present invention, comprises the steps:

[0036] Step 1: Build a cube star model containing solar arrays in STK (such as figure 2 ):

[0037] Step 1.1: Use text files to create the cube star body model and active plane model, in which the cube star body model is used as the body-mounted battery array; the active plane model is used as the unfolded battery array.

[0038] Step 1.2: Create a new scene in STK, import the text file created in step 1.1, and generate a cube star model including the body-mounted battery array and the deployed battery array.

[0039] Step 1.3: Establish the reference plane of the body-mounted battery array on the surface of the body-mounted battery array, and establish the reference plane of the unfolded ...

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Abstract

The invention discloses an energy budget method of a cubesat sun-synchronous orbit solar battery array. The method comprises the following steps of firstly building a cubesat model including the solar battery array in an STK; secondly building an obit model in the STK according to six sun-synchronous orbital elements of a cubesat, and conducting simulation to obtain beta angle change conditions and single-circle illumination duration change conditions in one year when the cubesat is in orbit; then selecting the orbit with the shortest illumination duration when the beta angle is the smallest, and simulating the orbit to obtain a solar incident angle of the orbit illumination period; finally substituting the solar incident angle into a computing formula of the in-obit output power of the solar battery array, and conducting accumulation to obtain total energy generated by the solar battery array in the orbit illumination period. The energy budget method has the advantages of being simple in operation, strong in intuition, small in implementation difficulty and high in accuracy, and can serve as a reliable input condition for energy balance analysis of the cubesat.

Description

technical field [0001] The invention relates to a cube star energy budget, in particular to an energy estimation method for a cube star sun synchronous orbit solar battery array. Background technique [0002] CubeSats mostly operate in sun-synchronous orbits with better lighting conditions, and use the combination of body-mounted solar cell arrays and unfolded solar cell arrays to obtain energy, which is currently the most important energy source for cubesats in orbit. CubeSat energy balance analysis is an important part of power system reliability design, and has guiding significance for power system design and mission planning of the whole star. Among them, the estimation of the on-orbit energy of the CubeSat solar cell array is the first and most critical step in the analysis of the CubeSat energy balance in combination with the orbital conditions of the CubeSat. [0003] The existing energy estimation method of the cube star solar synchronous orbit solar cell array is t...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20Y02E60/00
Inventor 马海宁张翔
Owner NANJING UNIV OF SCI & TECH
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