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PID design for nonlinear spacecraft model with reaction wheels

Seda Nur Çakıcı,NUR SENA KOCAKILIÇ,AMİNE EL ARUK,MUHAMMET ÖZTÜRK

  • Seda Nur Çakıcı: Necmettin Erbakan UNİVERSİTESİ
  • NUR SENA KOCAKILIÇ: NECMETTİN ERBAKAN ÜNİVERSİTESİ
  • AMİNE EL ARUK: NECMETTİN ERBAKAN ÜNİVERSİTESİ
  • MUHAMMET ÖZTÜRK: NECMETTİN ERBAKAN ÜNİVERSİTESİ
  •  Year : 2025
  •  Vol : 4
  •  Issue : 1
  •  Page : 116-130
The attitude control of a spacecraft is one of the most critical factors to ensure mission success. Satellites must maintain a constant orientation in space due to their operational objectives, such as communication satellites with directional antennas or those that depend on precise solar panel alignment to maximise energy efficiency. It is very important to keep the satellite stable at a predetermined position in space. To maintain this constant orientation and correct any disturbances, attitude control systems are used. The dynamics of such systems can be described using Newton's Second Law, which results in a set of non-linear equations for motion about the x, y and z axes. Due to their nonlinearity, these equations cannot be analysed directly using classical control methods based on transfer functions. PID (Proportional - Integral - Derivative) controllers are widely used in control systems, but their coefficients need to be determined appropriately. To obtain a suitable set of PID coefficients for satellite control via reaction wheels, the nonlinear system must first be linearised around a point close to the reference values. This ensures that the linear approximation accurately represents the system dynamics near the desired direction. This study aims to determine PID coefficients with respect to our desired control performance criteria. For this, the PID coefficients are calculated from the linearised system and applied to the original nonlinear model. For this calculation, the previously obtained linear model and actuator models are used. The PID coefficients are calculated by considering the desired settling time and overshoot. The PID coefficients are tested for linear and nonlinear models in simulation to show the effectiveness of the proposed approach.
Cite this Article As : Çakıcı, S. N., Kocakılıç, N. S., El Aruk, A. & Öztürk, M. (2025). PID design for nonlinear spacecraft model with reaction wheels. Aerospace Research Letters (ASREL), 4(1), 116-130. https://doi.org/10.56753/ASREL.2025.1.8

Conflict of interest : Hayir

This article is published under the CC BY-NC 4.0 license.
Asrel Aerospace Research Letters
2025, Vol4, Issue1
E-ISSN: 2980-0064
Received : , Accepted : , Published Online :

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