Attitude Control of a Flexible Spacecraft via Fuzzy Optimal Variance Technique

Abstract

This paper investigates the performance of a fuzzy optimal variance control technique for attitude stability and vibration attenuation with regard to a spacecraft made of a rigid platform and multiple flexible appendages that can be retargeted to the line of sight. The proposed technique addresses the problem of actuators’ amplitude and rate constraints. The fuzzy model of the spacecraft is developed based on the Takagi-Sugeno(T-S) fuzzy model with disturbances, and the control input is designed using the Parallel Distributed Compensation technique (PDC). The problem is presented as an optimization problem in the form of Linear Matrix Inequalities (LMIs). The performance and the stability of the proposed controller are investigated through numerical simulation.

Neural Adaptive Fixed-Time Attitude Stabilization and Vibration Suppression of Flexible Spacecraft

“…where V 1 , V 2 , and V 3 are defined as ( 15), (19), and (28), respectively. Combining ( 19), (27), and (37) and by the aid of Lemma 3, the time differentiation of (41) can be evaluated as…”

“…In [17], an intelligent PD control scheme was proposed based on the NN identification. In [18,19], Takagi-Sugeno (T-S) fuzzy model-based optimal controllers were constructed. There have also been some related results focused on the attitude control of flexible spacecraft equipped with piezoelectric devices for active vibration suppression [20][21][22][23][24].…”

Attitude Stabilization of a Satellite with Large Flexible Elements Using On-Board Actuators Only

“…Fixed-time attitude control and stabilization using a neural network is considered in [15]. Fuzzy-logic optimal control was investigated in [16]. Thus, there are a huge variety of control approaches for flexible spacecraft attitude stabilization.…”