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A method for evaluating the on-orbit output power of a solar wing

A technology of output power and sun, which is applied in the field of on-orbit output power evaluation of solar wings, can solve the problems of inability to adapt to the PCU power topology and the inability to accurately determine the shunt series, and achieve high accuracy, high precision, and high calculation accuracy.

Active Publication Date: 2020-05-08
CHINA ACADEMY OF SPACE TECHNOLOGY
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AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: aiming at the inability of the solar wing on-orbit power evaluation method in the prior art to adapt to the power topology of the new generation of PCU, to fill in the fact that the solar wing power evaluation based on the new generation of PCU topology cannot accurately determine the number of shunts, and to overcome the disadvantages of the prior art Insufficient, provide a new generation of PCU power topology solar array power evaluation method on orbit

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  • A method for evaluating the on-orbit output power of a solar wing
  • A method for evaluating the on-orbit output power of a solar wing
  • A method for evaluating the on-orbit output power of a solar wing

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Embodiment Construction

[0054] The task of the satellite power supply and distribution subsystem is to provide and distribute power to the payload and service module subsystems of the satellite during each flight phase of the satellite, including the active segment, transfer orbit and synchronous orbit.

[0055]The satellite power supply and distribution subsystem uses the solar battery array as the main power source, and the battery pack as the energy storage device. The power supply busbar and power are regulated and controlled by the power controller; During the light period, the busbar charges the battery pack through the battery charging regulator, the busbar first inputs the current to the battery charging regulator, and the battery charging regulator reduces the voltage of the busbar input current to the battery voltage and then outputs it to the battery; when the solar cell array When the output power is greater than the sum of the load power of the whole star, the charging power of the batter...

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Abstract

The invention provides a solar wing on-orbit output power assessment method under novel power topology. The method realizes on-orbit power evaluation of a solar cell array under the new generation PCUpower topology by measuring and calculating parameters of each part of the solar cell array, and is used for solving the problem that a solar wing on-orbit power assessment method in the prior art cannot be suitable for the new generation PCU. By utilizing on-obit telemetry parameters of whole-satellite load current, subarray shunt regulation state, solar cell array current, orbit position and date and the like, the method can determine in-orbit power output capacity of the solar cell array in real time, and carry out effective verification on the ground design result; and the method is highin reliability and high in precision.

Description

technical field [0001] The invention relates to a method for evaluating the on-orbit output power of a solar wing, which belongs to the field of synchronous orbit long-life communication satellites. Background technique [0002] The solar array is the energy source of the satellite's power supply and distribution subsystem. It provides power for the entire satellite load during the satellite's light period, and at the same time charges the battery pack to meet the discharge requirements of the battery during the shadow period. The stable and reliable power output of the solar cell array is the most basic guarantee for the normal operation of the whole star, so it is necessary to accurately and reliably determine the power output capability of the solar cell array. [0003] When the satellite is in orbit, the dynamic changes of the orbital environmental conditions and the load make the power output of the solar cell array constantly changing, and the solar incidence angle cha...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02S50/00H02J7/35
CPCH02J7/35H02S50/00Y02E10/50
Inventor 李大正李雅琳李峰邢杰张文芳
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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