Designing attitude controller for nano/pico satellites at detumbling mode using magnetic sensor and actuator | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Volume 20, Issue 20, May 2023, Page 1-8 PDF (1.89 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.1088/1742-6596/2616/1/012028 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
K Mohsen  1; M Ibrahim2; A M Kamel3; M Ashry1
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| 1Automatic Control Department, Military Technical College, Cairo, Egypt. | ||||
| 2Aircraft Electrical Equipment, Military Technical College, Cairo, Egypt. | ||||
| 3Guidance Department, Military Technical College, Cairo, Egypt. | ||||
| 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. | ||||
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