Paper Information

Journal:   JOURNAL OF SPACE SCIENCE AND TECHNOLOGY (JSST)   SPRING 2009 , Volume 2 , Number 3; Page(s) 43 To 50.
 
Paper: 

FLEXIBLE SPACECRAFT THREE AXIS ATTITUDE MANEUVER BY ACTIVE VIBRATION CONTROL

 
Author(s):  SAYANJALI M.*, ROSHANIAN J., GHAFARI A.
 
* IRANIAN SPACE AGENCY, K.N. TOOSI UNIV. OF TECH. AMCA AVE., SAYEH AVE., TEHRAN, IRAN
 
Abstract: 
In this paper, equation of motion of three axis attitude dynamic of flexible spacecraft is derived using combination of finite element method and Euler equation. Flexible appendages are modeled by beam elements. Goal of control is target attitude of spacecraft from initial state to desired attitude and suppression of vibration that induced inflexible appendages. So a combination of back stepping and sliding mode control method used for three-axis attitude maneuver of flexible spacecraft and for suppressing vibration of flexible appendage used from active vibration control method by PZT actuator. Control law for vibration control is based on LQG method.
 
Keyword(s): FLEXIBLE SPACECRAFT, THREE AXIS ATTITUDE MANEUVER, SLIDING MODE CONTROL, ACTIVE VIBRATION CONTROL
 
References: 
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