TY - JOUR
T1 - Reentry Attitude Fault Tolerant Control for RLV Based on Adaptive Second-Order Nonsingular Fast Terminal Sliding Mode
AU - Liu, Dakai
AU - Esche, Sven K.
AU - Wang, Mingang
AU - Chang, Xiaofei
N1 - Publisher Copyright:
© 2022, The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences.
PY - 2022/11
Y1 - 2022/11
N2 - In this paper, a novel adaptive continuous nonsingular fast terminal sliding mode fault tolerant control scheme for reusable launch vehicles (RLVs) is proposed. This scheme was designed to counteract the modeling uncertainties, external disturbances and actuator faults during the reentry phase. First, an attitude dynamics model for the reentry of RLVs is built. Then, with feedback linearization, a second-order attitude tracking error model is derived. Subsequently, based on the traditional discontinuous nonsingular fast terminal sliding manifold (NFTSM), a second-order continuous NFTSM-based control strategy is developed to achieve a fast and accurate attitude tracking in the presence of uncertainties, disturbances and actuator faults. Compared with the existing NFTSM-based control strategies, the proposed control law guarantees higher robustness and chattering reduction without introducing state or disturbance observers. Thus, the proposed control law has a more concise and simpler structure. Furthermore, it does not require prior knowledge of the upper bounds of the disturbances. While most of the existing control strategies based on the NFTSM tend to suffer large oscillations at the initial phase of the control process, the proposed control law eliminates these oscillations. Finally, simulations are carried out that demonstrate that the proposed control law has better robustness to disturbances and faults while creating less chattering than the exiting control laws.
AB - In this paper, a novel adaptive continuous nonsingular fast terminal sliding mode fault tolerant control scheme for reusable launch vehicles (RLVs) is proposed. This scheme was designed to counteract the modeling uncertainties, external disturbances and actuator faults during the reentry phase. First, an attitude dynamics model for the reentry of RLVs is built. Then, with feedback linearization, a second-order attitude tracking error model is derived. Subsequently, based on the traditional discontinuous nonsingular fast terminal sliding manifold (NFTSM), a second-order continuous NFTSM-based control strategy is developed to achieve a fast and accurate attitude tracking in the presence of uncertainties, disturbances and actuator faults. Compared with the existing NFTSM-based control strategies, the proposed control law guarantees higher robustness and chattering reduction without introducing state or disturbance observers. Thus, the proposed control law has a more concise and simpler structure. Furthermore, it does not require prior knowledge of the upper bounds of the disturbances. While most of the existing control strategies based on the NFTSM tend to suffer large oscillations at the initial phase of the control process, the proposed control law eliminates these oscillations. Finally, simulations are carried out that demonstrate that the proposed control law has better robustness to disturbances and faults while creating less chattering than the exiting control laws.
KW - Adaptive gain
KW - Finite-time fault tolerant control
KW - Higher order sliding mode control
KW - Nonsingular fixed-time terminal sliding mode
KW - RLV
UR - http://www.scopus.com/inward/record.url?scp=85132366482&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85132366482&partnerID=8YFLogxK
U2 - 10.1007/s42405-022-00480-5
DO - 10.1007/s42405-022-00480-5
M3 - Article
AN - SCOPUS:85132366482
SN - 2093-274X
VL - 23
SP - 980
EP - 991
JO - International Journal of Aeronautical and Space Sciences
JF - International Journal of Aeronautical and Space Sciences
IS - 5
ER -