Electromechanical heat fusion type micro-driving mechanism for space

By designing a space electromechanical and thermal fusion micro-drive mechanism containing a permanent magnet synchronous motor and a magnetic encoder, the problem of insufficient satisfaction in the driving mechanism in the prior art in terms of long life, full-cycle reliability, electromechanical and thermal fusion and lightweight needs is solved, high precision direction and stability are achieved, and on-orbit programming and information processing capabilities are provided, and high reliability is maintained in a strong radiation environment.

CN119705865AActive Publication Date: 2025-03-28SHANGHAI AEROSPACE CONTROL TECH INST
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Patent Information

Application Number
CN202411877378.X
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-19
Publication Date
2025-03-28
Estimated Expiration
2044-12-19

AI Technical Summary

Technical Problem

The drive mechanisms of existing space vehicles and satellites are not met in terms of long life, full-cycle reliability, electromechanical and thermal fusion, and lightweight requirements, and the separation of the controller and mechanism cannot achieve close mechanical and electrical system fusion.

Method used

A space electromechanical and thermal fusion micro-drive mechanism is designed, including an external structure and an integrated drive-control shaft system, using a permanent magnet synchronous motor, a magnetic encoder and a micro-stress detection device to achieve high-precision directed motion and position maintenance, and closed-loop control is realized through the FPGA main control chip.

Benefits of technology

The driving mechanism meets the requirements of high-precision direction, high-precision stability and long-life rotation, has in-orbit programming and information processing capabilities, can maintain high reliability in a strong radiation environment, and achieve a temperature control accuracy of 0.5 degrees Celsius.

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Abstract

The invention discloses an electromechanical heat fusion type micro-drive mechanism for space. The electromechanical heat fusion type micro-drive mechanism comprises an external structure and a drive and control integrated shaft system. The external structure comprises a left outer surface assembly, a right outer surface assembly, a load support, a rear cover plate, an accurate measurement mirror assembly, a locking assembly and a front cover plate. The left outer surface assembly comprises a left shafting bracket, a left connector panel, a left adapter bracket and a left bracket locking nut; the right outer surface assembly comprises a right shafting bracket, a right connector panel, a right adapter bracket and a right bracket locking nut; the drive and control integrated shaft system comprises a mandrel assembly, a control assembly, a bottom cover plate, a connector assembly and a micro stress detection device. The mandrel assembly sequentially comprises a mandrel, a left bearing locking nut, a left bearing seat, a left bearing space ring, a left bearing, a permanent magnet synchronous motor, a right bearing space ring, a right bearing, a right bearing seat and a right bearing locking nut from left to right. The system is long in service life and high in precision, and has programming and information processing capabilities.
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