TY - JOUR
T1 - Sliding mode control for Mars entry based on extended state observer
AU - Lu, Kunfeng
AU - Xia, Yuanqing
AU - Shen, Ganghui
AU - Yu, Chunmei
AU - Zhou, Liuyu
AU - Zhang, Lijun
N1 - Publisher Copyright:
© 2017
PY - 2017/11/1
Y1 - 2017/11/1
N2 - This paper addresses high-precision Mars entry guidance and control approach via sliding mode control (SMC) and Extended State Observer (ESO). First, differential flatness (DF) approach is applied to the dynamic equations of the entry vehicle to represent the state variables more conveniently. Then, the presented SMC law can guarantee the property of finite-time convergence of tracking error, which requires no information on high uncertainties that are estimated by ESO, and the rigorous proof of tracking error convergence is given. Finally, Monte Carlo simulation results are presented to demonstrate the effectiveness of the suggested approach.
AB - This paper addresses high-precision Mars entry guidance and control approach via sliding mode control (SMC) and Extended State Observer (ESO). First, differential flatness (DF) approach is applied to the dynamic equations of the entry vehicle to represent the state variables more conveniently. Then, the presented SMC law can guarantee the property of finite-time convergence of tracking error, which requires no information on high uncertainties that are estimated by ESO, and the rigorous proof of tracking error convergence is given. Finally, Monte Carlo simulation results are presented to demonstrate the effectiveness of the suggested approach.
KW - Differential flatness
KW - Extended state observer
KW - Mars entry guidance and control
KW - Monte Carlo
KW - Sliding mode control
UR - http://www.scopus.com/inward/record.url?scp=85027515361&partnerID=8YFLogxK
U2 - 10.1016/j.asr.2017.06.014
DO - 10.1016/j.asr.2017.06.014
M3 - Article
AN - SCOPUS:85027515361
SN - 0273-1177
VL - 60
SP - 2009
EP - 2020
JO - Advances in Space Research
JF - Advances in Space Research
IS - 9
ER -