Designing attitude controller for nano/pico satellites at detumbling mode using magnetic sensor and actuator

Document Type : Original Article

Authors

1 Automatic Control Department, Military Technical College, Cairo, Egypt.

2 Aircraft Electrical Equipment, Military Technical College, Cairo, Egypt.

3 Guidance Department, Military Technical College, Cairo, Egypt.

10.1088/1742-6596/2616/1/012028

Abstract

Recently, satellites have been becoming economically attractive in many applications using the advanced technologies and payloads. Practically, the launching process of any satellite passes through some stages under di erent conditions. For example, the satellite might be uncontrollable in the detumbling mode. Thus, it might be a risk of accident with space
debris and the satellite can not complete the speci ed mission. So it is necessary to design an attitude controller to stabilize the satellite after the separation phase, i.e., in the detumbling mode. In this paper, we design an attitude controller to bring the satellite to the desired condition with a minimum angular momentum. The magnetorquers and magnometers are an e ective solution for the satellite in low-Earth orbits because they are smaller and lighter than
others. Simulation studies are presented to validate the proposed attitude control approaches.

Main Subjects

International Conference on Aerospace Sciences and Aviation Technology
Volume 20, Issue 20
20th International Conference on Aerospace Sciences & Aviation Technology (ASAT-20). May 9 -11, 2023
May 2023
Pages 1-8

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