Integrated Predictor-Observer Feedback Control for Vibration Mitigation of Large-Scale Spacecraft With Unbounded Input Time Delay

This research investigates an integrated predictor–observer feedback control strategy for the vibration suppression of large-scale spacecraft affected by unbounded input time-delay effect. The vibration model incorporates orbit-attitude coupling effects, with lumped disturbance introduced to address...

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Bibliographic Details
Published inIEEE transactions on aerospace and electronic systems Vol. 61; no. 2; pp. 4561 - 4572
Main Authors Lyu, Bailiang, Liu, Chuang, Yue, Xiaokui
Format Journal Article
LanguageEnglish
Published New York IEEE 01.04.2025
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subjects
Aerodynamics
Asymptotic stability
Closed loops
Control systems
Control theory
Delays
Dynamic response
Feedback control
Integrated predicto-r-observer
Kernel
large-scale spacecraft vibration
Mathematical models
Orbits
Space vehicles
Spacecraft
Stability analysis
state-disturbance estimation
Time lag
unbounded time-delay
Vibration control
Vibrations
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Summary:This research investigates an integrated predictor–observer feedback control strategy for the vibration suppression of large-scale spacecraft affected by unbounded input time-delay effect. The vibration model incorporates orbit-attitude coupling effects, with lumped disturbance introduced to address nonlinearities. Resulted from large-scale characteristics, the unbounded input time-delay is considered during the dynamic response process. Accordingly, for the infinite property of delay effect in time domain, a universal integrated predictor–observer feedback control scheme is developed to achieve asymptotic stabilization of closed-loop system via Lyapunov theory. Notably, the state, disturbance and intermediate observers are analyzed subject to unbounded time-delay respectively to estimate both states and disturbance simultaneously, in contrast to the availability or ignorance assumption directly in existing literature. Then, a predictor is introduced to compensate for the time-delay and prevent adverse performance impacts. Furthermore, numerical simulations of the spacecraft's vibration dynamics are performed to validate the effectiveness of proposed control strategy.
Bibliography:ObjectType-Article-1
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ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2024.3505851