TY - GEN
T1 - Double-loop sliding mode control of reentry hypersonic vehicle with RCS
AU - Song, Jia
AU - Hao, Ce
AU - Zhang, Yanxue
AU - Yu, Nanjia
AU - Liu, Yang
AU - Yang, Erfu
N1 - © 2019 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other uses, in any current or future media, including reprinting /republishing this material for advertising or promotional purposes, creating new collective works, for resale or redistribution to servers or lists, or reuse of any copyrighted component of this work in other works.
PY - 2019/11/14
Y1 - 2019/11/14
N2 - In order to solve the problem of insufficient aerodynamic moment caused by thin air in the re-entry stage of hypersonic vehicle, this paper establishes an attitude angle model of hypersonic vehicle with reaction control system (RCS), and derives its affine linear model to decoupled the internal and external loop. According to the dead zone and saturation characteristics of RCS thruster, a control method to convert continuous moment into discrete switching instruction using pulse width modulation (PWM) is proposed. Since the number of thrusters is usually redundant, the installation matrix of thrusters in the body coordinate is established, and the command moment is coordinately distributed to the individual thrusters. Then a double-loop sliding mode controller (DSMC) is designed to achieve attitude stability and trajectory tracking. Finally, the simulation results show that DSMC has higher maneuverability, fewer thruster switches and stronger robustness to interference.
AB - In order to solve the problem of insufficient aerodynamic moment caused by thin air in the re-entry stage of hypersonic vehicle, this paper establishes an attitude angle model of hypersonic vehicle with reaction control system (RCS), and derives its affine linear model to decoupled the internal and external loop. According to the dead zone and saturation characteristics of RCS thruster, a control method to convert continuous moment into discrete switching instruction using pulse width modulation (PWM) is proposed. Since the number of thrusters is usually redundant, the installation matrix of thrusters in the body coordinate is established, and the command moment is coordinately distributed to the individual thrusters. Then a double-loop sliding mode controller (DSMC) is designed to achieve attitude stability and trajectory tracking. Finally, the simulation results show that DSMC has higher maneuverability, fewer thruster switches and stronger robustness to interference.
KW - aerodynamics
KW - reentry hypersonic vehicle
KW - trajectory control
UR - http://www.scopus.com/inward/record.url?scp=85075783346&partnerID=8YFLogxK
U2 - 10.1109/ICCA.2019.8899548
DO - 10.1109/ICCA.2019.8899548
M3 - Conference contribution book
AN - SCOPUS:85075783346
T3 - IEEE International Conference on Control and Automation, ICCA
SP - 109
EP - 114
BT - 2019 IEEE 15th International Conference on Control and Automation, ICCA 2019
PB - IEEE
CY - Piscataway, N.J.
T2 - 15th IEEE International Conference on Control and Automation, ICCA 2019
Y2 - 16 July 2019 through 19 July 2019
ER -