Year: 2025
Type: article
Abstract: In this paper Two nonlinear control designs are developed for continuous-time spacecraft attitude control system. Firstly, a state transformation is created for the system model to generate a state feedback control strategy. Then, a sliding mode controller is obtained for the system to stabilize the spacecraft model using Lyapunov stability theory. The closed loop control system is simulated to demonstrate the effectiveness of the developed control approaches in regulating the system to the stability.
Authors: E. Aljuwaiser, M. Alfadli
Institution: Kuwait University
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: bronze
OpenAlex ID: W4412501503