@article{WANG2026, 
author = {Jun WANG and Wei WANG and Zijun ZHANG and Xiaohui WANG and Zhiyi SONG and Xiaoyu HAO},
title = {Fault-tolerant control for near space vehicle with new type dissimilar redundant actuation/flight control system},
year = {2026},
journal = {Journal of Beijing University of Aeronautics and Astronautics},
volume = {52},
number = {8},
pages = {2756-2768},
keywords = {near space vehicle, flight control system, new type dissimilar redundant actuation system, concomitant model, multi-level fault-tolerant control},
url = {https://www.sciopen.com/article/10.13700/j.bh.1001-5965.2025.0835},
doi = {10.13700/j.bh.1001-5965.2025.0835},
abstract = {The paper presents a concomitant model based multi-level fault-tolerant control (FTC) for near space vehicle (NSV) with a new type of dissimilar redundant actuation system (NT-DRAS). The model, with its physical meaning as a virtual system of the actual vehicle, coexists with the real system to perform real-time synchronous simulation and monitoring of the real system's functions and performance status. In order to meet the intelligent decision-making support requirements of the NSV actual system, the concomitant big model consists of a flight control-level main model and actuation-level sub-models that form a hierarchical architecture. In the event that the vehicle's flight attitude-related sensors fail, a hybrid output state can be reconstructed by combining the theoretical output of the flight control-level concomitant main model with the real system usable state. This hybrid output state is then used to solve the state feedback gains using linear quadratic regulator (LQR) technology. Additionally, this study conducts state monitoring and redundancy management for the configured NT-DRAS system at the actuation level, ultimately combining concomitant sub-model based NT-DRAS channel switching measures by flight control-level concomitant main model based LQR control to address complex and progressively deteriorating fault conditions involving actuators and flight control attitude sensors. Finally, numerical simulations are performed on the MATLAB/Simulink platform to verify the effectiveness and progressiveness of the proposed method.}
}