Attitude control for part actuator failure of agile small satellite

DOI10.1007/S10409-008-0153-2zbMath1271.70078OpenAlexW1983705547MaRDI QIDQ364167

Mohammad Hasan, M. Dambrine

Publication date: 5 September 2013

Published in: Acta Mechanica Sinica (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1007/s10409-008-0153-2

zbMATH Keywords

singularity analysisagile small satellitegyro failuremicro control moment gyros (MCMG's)

Mathematics Subject Classification ID

Control of mechanical systems (70Q05) Orbital mechanics (70M20) Motion of the gyroscope (70E05)

Related Items (7)

Influence of flexible solar arrays on vibration isolation platform of control moment gyroscopes ⋮ The output torque estimation of MCMG for agile satellites ⋮ An improved constrained steering law for SGCMGs with DPC ⋮ Error analysis and a new steering law design for spacecraft control system using SGCMGs ⋮ Steady-state responses of a belt-drive dynamical system under dual excitations ⋮ Attitude control of a rigid spacecraft with one variable-speed control moment gyro ⋮ Nonlinear dynamics of axially moving viscoelastic Timoshenko beam under parametric and external excitations

Cites Work

• Study on relative orbital configuration in satellite formation flying
• A new design approach of PD controllers

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