Journal of Systems Engineering and Electronics ›› 2018, Vol. 29 ›› Issue (5): 1022-1035.doi: 10.21629/JSEE.2018.05.13

• Control Theory and Application • Previous Articles     Next Articles

Active disturbance rejected predictive functional control for space vehicles with RCS

Jiayi TIAN(), Shifeng ZHANG*()   

  • Received:2008-09-04 Online:2018-10-26 Published:2018-11-14
  • Contact: Shifeng ZHANG;
  • About author:TIAN Jiayi was born in 1990. He received his B.S. degree and M.S. degree in aeronautical and astronautical science and technology from Beihang University and National University of Defense Technology in 2013 and 2015 respectively. He is now pursuing his Ph.D. degree in National University of Defense Technology. His research interests include disturbance rejection based control and aircraft dynamics and control. E-mail:|ZHANG Shifeng was born in 1971. He received his Ph.D. degree in control theory and engineering from National University of Defense Technology in 2000. His research interests cover aircraft overall design, flight dynamics, guidance and control, inertial navigation, and measurement and precision analysis. He is currently a Fellow of the Unmanned Aerial Vehicle System Engineering and Flight Test Committee, a Fellow of the Chinese Society of Astronautics Aircraft Overall System Committee, and Topic Principal of the 973, 863 Project Management Office. E-mail:


Reaction control system (RCS) is a powerful and efficient actuator for space vehicles attitude control, which is typically characterized as a pulsed unilateral effector only with two states (off/on). Along with inevitable internal uncertainties and external disturbances in practice, this inherent nonlinear character always hinders space vehicles autopilot from pursuing precise tracking performance. Compared to most of pre-existing methodologies that passively suppress the uncertainties and disturbances, a design based on predictive functional control (PFC) and generalized extended state observer (GESO) is firstly proposed for three-axis RCS control system to actively reject that with no requirement for additional fuel consumption. To obtain a high fidelity predictive model on which the performance of PFC greatly depends, the nonlinear coupling multiple-input multiple-output (MIMO) flight dynamics model is parameterized as a state-dependent coefficient form. And based on that, a MIMO PFC algorithm in state space domain for a plant of arbitrary orders is deduced in this paper. The internal uncertainties and external disturbances are lumped as a total disturbance, which is estimated and cancelled timely to further enhance the robustness. The continuous control command synthesised by above controller-rejector tandem is finally modulated by pulse width pulse frequency modulator (PWPF) to on-off signals to meet RCS requirement. The robustness and feasibility of the proposed design are validated by a series of performance comparison simulations with some prominent methods in the presence of significant perturbations and disturbances, as well as measurement noise.

Key words: reaction control system (RCS), predictive functional control (PFC), generalized extended state observer (GESO), pulse width pulse frequency (PWPF), multiple-input multiple-output (MIMO)