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Estimation method of output current of solar cell array at satellite orbit-injection stage

A solar cell array and output current technology, which is applied in the field of spacecraft control, to achieve universal and easy-to-implement effects

Active Publication Date: 2017-03-08
AEROSPACE DONGFANGHONG SATELLITE
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  • Claims
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Problems solved by technology

[0005] The problem solved by the technology of the present invention is: aiming at the deficiencies of the prior art, a method for estimating the output current of the solar cell array in the orbiting section of the satellite is provided. The problem of calculating the output current of the ±Y solar cell array improves the calculation accuracy of the output current of the solar cell array, and provides an important reference for the satellite to choose a reasonable launch window and improve the on-orbit flight control plan

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  • Estimation method of output current of solar cell array at satellite orbit-injection stage

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Embodiment Construction

[0022] The satellite of the present invention adopts a three-axis stable attitude control mode, and the solar battery array is installed in the Y-axis direction of the satellite.

[0023] The coordinate systems involved in the method are given below:

[0024] orbital coordinate system

[0025] Coordinate origin O: satellite centroid;

[0026] +X axis: pointing to the satellite on-orbit velocity direction is the +X axis, perpendicular to the OZ axis;

[0027] +Y axis: The direction perpendicular to the right hand of the +X axis and +Z axis and parallel to the normal of the orbital plane XOZ is the +Y axis;

[0028] +Z axis: The direction of the center of mass of the satellite pointing to the center of the earth is the +Z axis.

[0029] body coordinate system

[0030] Coordinate origin O: satellite centroid;

[0031] +X axis: parallel to the installation direction of the orbital control engine, and +X points to the forward direction of the satellite under normal operating c...

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Abstract

The invention provides an estimation method of an output current of a solar cell array at a satellite orbit-injection stage. The estimation method is used for realizing prediction and estimation of the output current of the solar cell array during the sun positioning process from satellite and rocket separation to satellite attitude after the launching of a satellite. In the process, the estimation method comprises a satellite and rocket separation to solar cell array unfolding mode, a solar cell array unfolding hold mode, a solar searching mode and a solar cell array return-to-zero mode. In each mode, an incident angle and illuminated area of the solar cell array change continuously along with the change of whole-satellite attitude, and the output current of the solar cell array in each mode is estimated. The estimation method introduces a panel coordinate system to solve the difficult that the output current of the + / -Y solar cell array cannot be calculated independently in the solar cell array return-to-zero mode, improves the calculation precision of the output current of the solar cell array, and provides an important reference for selecting a reasonable launching window of the satellite and improving an in-orbit flight control plan.

Description

technical field [0001] The invention belongs to the field of spacecraft control and relates to a method for determining the output current of a solar cell array. Background technique [0002] Generally speaking, from 30 minutes before the launch of the satellite to the normal deployment of the solar array after the launch, the normal work of each stand-alone satellite is supplied by the discharge of the battery pack. In view of the selection of the satellite launch window and the establishment of the ground measurement and control arc, the discharge time of the battery pack is about tens of minutes before the solar array is deployed. Therefore, after the satellite is launched, it must be oriented toward the sun to ensure the output current of the solar array, reduce the discharge power of the battery pack and be able to charge it. [0003] After the satellite is launched, it will fly along with the rocket according to the predetermined orbit. When it reaches the predetermin...

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Application Information

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IPC IPC(8): G01R31/36
CPCG01R19/0092H02S50/10Y02E10/50
Inventor 马文伟刘元默苏蛟鄢婉娟王乐乐
Owner AEROSPACE DONGFANGHONG SATELLITE
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