ADCS Preliminary Design For GNB

TL;DR

This paper presents a preliminary design and analysis of an Attitude Determination and Control System (ADCS) for a nanosatellite orbiting Earth, utilizing a GNB and control system synthesis based on prior research.

Contribution

It introduces a preliminary ADCS design for a nanosatellite using a GNB, including control system synthesis and analysis based on existing models and methods.

Findings

Control system successfully designed to meet technical requirements

Simulation performed using Matlab and Simulink

Analysis of orbital perturbations and attitude control effectiveness

Abstract

This work deals with an ADCS model for a satellite orbiting around Earth. The object is to achieve a preliminary design and perform some analysis on it. To do so, a GNB was selected and main properties are exploited. Previous works of [9], [13], [14], [15] and [17] were analyzed and a synthesis was obtained; then a suitable control system was designed to satisfy technical requirements. Coding was performed using Matlab and Simulink. Keywords: Attitude Determination, Attitude Control, Nanosatellite, Orbital Perturbations, Quaternion, Two Body Problem, Euler's Equations, Lyapunov Function.