What is it about?
This paper proposes a robust sliding mode control (SMC) method to control the attitude(pitch, roll, yaw) of a small satellite with CEACS operating in LEO in presence of uncertainties and disturbance. The paper provides a thorough literature review of the system and the SMC application in small satellites. The control law development is very detailed and it can be used as a guide for designing sliding mode controllers for satellites.
Featured Image
Why is it important?
It proposes a simple yet effective method to avoid singularity in SMC implementation. It provides a superior control performance for a small satellite featuring CEACS in presence of uncertainties and disturbances It solves the three axes control problem of a small satellite with CEACS
Perspectives
The paper can be used as a step-by-step guide for designing sliding mode controller for satellites. All aspects of the design are explained with details.
Samira Eshghi
UPM
Read the Original
This page is a summary of: Singularity-free integral-augmented sliding mode control for combined energy and attitude control system, Advances in Space Research, January 2017, Elsevier,
DOI: 10.1016/j.asr.2016.10.007.
You can read the full text:
Contributors
The following have contributed to this page
