Attitude Stabilization during Retargeting Maneuver of Flexible Spacecraft Subject to Time Delay and Actuators Saturation

Attitude Control of a Flexible Spacecraft via Fuzzy Optimal Variance Technique

“…In this section, we briefly derive the mathematical model of the flexible spacecraft. For a detailed derivation, we refer the reader to [32,33].…”

“…The open-loop simulation shows that the T-S fuzzy model provides a good approximation of the dynamical model with a set of four rules. The absolute errors are summarized in [32], and the comparison results of the position, angular position, and displacement for appendages 1 and 2 are presented in Figures 4-7.…”

“…This paper presents a fuzzy optimal variance control technique to stabilize a spacecraft's attitude and attenuate the vibration in the flexible appendages. It should be noted that the fuzzy controller designed in this paper differs from the controller presented in [32]. In ref.…”

“…With the development of a modelbased approach such as the Takagi-Sugeno fuzzy model, a solid mathematical foundation such as the Lyapunov function approach [23][24][25][26] can be used to investigate the stability and the performance of fuzzy closed-loop complex systems. Valuable work was carried out to derive a dynamic model involving constraints on the control input via the T-S fuzzy model; see, for instance [27][28][29][30][31][32].…”

“…In ref. [32], an unknown independent time delay was present in the system, and the fuzzy controller was designed based on a T-S fuzzy model with time delay in the states and constraints on the amplitude of an actuator. The proposed controller addresses other challenges such as amplitude and rate saturation.…”