低軌質量矩航天器姿態(tài)動力學與氣動補償控制

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中圖分類號： TN974 文獻標志碼：A DOI：10.12305/j.issn.1001-506X.2025.06.25

Abstract：Aiming at the serious interference aerodynamic eccentric moment on the atitude control performance ultra-low Earth orbit satelites，an adaptive dynamic compensation control method for micronano satelltes based on mass moment technology is proposed.For the mass moment drive method based on ball screw pairs，considering the mechanism transmision friction，a complete dynamic model mass moment sateliterotation，translation， actuator translation is established to clarify theinfluence various parameters on disturbance moment. To address the uncertainties in the aerodynamic environment the unknown center mass the satelite，an adaptive dynamic compensation scheme is designed，which includes aradial basis function （RBF）-based disturbance observer，a sliding mode controllr， an integral separated proportional-integral-derivation（PID）controler. Simulation results show that the proposed compensation control method can accurately estimate compensate for aerodynamic moment disturbances effectively eliminate the influencefriction in the mass moment mechanism， validate the effectiveness the proposed aerodynamic compensation control method.

Keywords：ultra-low Earth orbit satellite；atitude control；aerodynamic moment；friction characteristics; sliding mode control

0 引言

成像分辨率高、實時覆蓋性強等優(yōu)勢，在災害預警、軍事偵察、互聯網通信等領域具有極高的潛在應用價值。（剩余14644字）