TY - JOUR
T1 - Uncertain optimal attitude control for space power satellite based on interval Riccati equation with non-probabilistic time-dependent reliability
AU - Yang, Chen
AU - Lu, Wanze
AU - Xia, Yuanqing
N1 - Publisher Copyright:
© 2023 Elsevier Masson SAS
PY - 2023/8
Y1 - 2023/8
N2 - Considering the multi-source uncertainties and disturbances in the attitude dynamics of space power satellite (SPS), an interval dynamic model of SPS is proposed based on the non-probabilistic theory, which is controlled by a novel uncertainty-based linear–quadratic regulator (LQR) method with time-dependent reliability. Based on the interval analysis method, an interval time-varying attitude dynamic model of SPS for sun-pointing is established considering the uncertain inertia and initial states as unknown-but-bounded parameters. Feedforward and feedback controllers are designed to offset the disturbance and control attitude, respectively. An interval Riccati equation-based optimal control method is proposed to develop a novel uncertainty-based LQR method. Non-probabilistic time-dependent reliability is constituted based on the interval process and first passage theory to assess attitude states. An uncertain multi-objective optimization of attitude control with reliability constraints is proposed to realize the uncertain LQR method. Verified by a numerical example of SPS, the proposed method takes only 0.6‰∼0.8‰ time consumption of 10,000 Monte Carlo simulations while maintaining a certain accuracy.
AB - Considering the multi-source uncertainties and disturbances in the attitude dynamics of space power satellite (SPS), an interval dynamic model of SPS is proposed based on the non-probabilistic theory, which is controlled by a novel uncertainty-based linear–quadratic regulator (LQR) method with time-dependent reliability. Based on the interval analysis method, an interval time-varying attitude dynamic model of SPS for sun-pointing is established considering the uncertain inertia and initial states as unknown-but-bounded parameters. Feedforward and feedback controllers are designed to offset the disturbance and control attitude, respectively. An interval Riccati equation-based optimal control method is proposed to develop a novel uncertainty-based LQR method. Non-probabilistic time-dependent reliability is constituted based on the interval process and first passage theory to assess attitude states. An uncertain multi-objective optimization of attitude control with reliability constraints is proposed to realize the uncertain LQR method. Verified by a numerical example of SPS, the proposed method takes only 0.6‰∼0.8‰ time consumption of 10,000 Monte Carlo simulations while maintaining a certain accuracy.
KW - Attitude control
KW - Interval Riccati equation
KW - Interval time-varying attitude dynamics
KW - Multi-objective optimization
KW - Non-probabilistic time-dependent reliability
KW - Space power satellite
UR - http://www.scopus.com/inward/record.url?scp=85160841026&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2023.108406
DO - 10.1016/j.ast.2023.108406
M3 - Article
AN - SCOPUS:85160841026
SN - 1270-9638
VL - 139
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 108406
ER -