Space station solar wing reliable redundancy control system and method based on multi-instruction input

A technology of redundant control and command control, applied in general control systems, control/regulation systems, instruments, etc., can solve problems such as technical solutions for which there is no direct reference, and achieve the effect of ensuring stability

Active Publication Date: 2020-01-17
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
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  • Application Information

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Problems solved by technology

For reliable redundant control of large solar wings, there is no technical solution for direct reference

Method used

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  • Space station solar wing reliable redundancy control system and method based on multi-instruction input
  • Space station solar wing reliable redundancy control system and method based on multi-instruction input
  • Space station solar wing reliable redundancy control system and method based on multi-instruction input

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Embodiment Construction

[0032] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0033] The present invention provides a reliable redundant control system for the solar wing of a space station based on multiple command inputs, such as figure 1 As shown, it includes: a solar wing locking mechanism 3, a solar wing driving mechanism 4, and a controller.

[0034] The solar wing locking mechanism 3 is connected to the solar wing 5 for locking and unlocking the solar wing 5;

[0035] The solar wing driving mechanism 4 is connected to the solar ...

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Abstract

The invention provides a space station solar wing reliable redundancy control system and a space station solar wing reliable redundancy control method based on multi-instruction input. The space station solar wing reliable redundancy control system comprises a solar wing locking mechanism, a solar wing driving mechanism and a controller, wherein the solar wing locking mechanism is used for lockingand unlocking a solar wing; the solar wing driving mechanism is used for driving the solar wing to perform sun-facing directional movement; the controller comprises a solar wing locking mechanism control module and a solar wing driving mechanism control module; the solar wing locking mechanism control module drives the solar wing locking mechanism to lock the solar wing according to a bus instruction locking signal and a hard wire instruction locking signal; the solar wing locking mechanism control module further drives the solar wing locking mechanism to unlock the solar wing according to abus instruction unlocking signal and a hard wire instruction unlocking signal; and the solar wing driving mechanism control module drives the solar wing driving mechanism to realize the sun-facing directional movement of the solar wing according to a bus instruction driving signal, a GNC instruction driving signal and a hard wire instruction driving signal. The invention further provides a space station solar wing reliable redundancy control method based on multi-instruction input.

Description

technical field [0001] The invention relates to the field of solar wing drive control for aerospace systems, in particular to a space station solar wing reliable redundant control system and method based on multiple command inputs. Background technique [0002] In the aerospace system, whether it is a spacecraft or a satellite, the main power to maintain its normal operation in orbit is electric energy. Early satellites had small payload capacity, low precision, and simple control schemes. The outer structure of the satellite is cylindrical, and the solar cells are pasted on the outer surface of the cylinder. Due to the spin of the satellite, the solar cells are only in direct sunlight for a short period of time during the star's revolution. So the satellite has less power available for the payload. [0003] In the prior art, in order to make full use of the electric energy generated by solar cells, solar wings are usually installed on satellites. The solar wing is a two...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B9/03
CPCG05B9/03
Inventor 岑启锋付培华吴鹏飞王有波丁承华
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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