Hui Qi
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Research Subjects
Research Interests
Hui Qi has a total of 5 co-authors. Here are the top co-authors by number of shared publications:
- Bangsheng Fu
Department of Aerospace Engineering, Harbin Engineering University, Harbin, 150001, China
1 shared publication - Jiangtao Xu
College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China
1 shared publication - Quanxi Gao
Master, Dept. of Aerospace Engineering, Harbin Engineering Univ., Harbin 150001, Heilongjiang, China. ORCID:
1 shared publication - Shaobo Wang
College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, Heilongjiang, China
1 shared publication - Ya Yang
Shanghai Electro-Mechanical Engineering Institute, Shanghai 201109, China
1 shared publication
Latest Publications
- Open Access
- 26 November 2019
- Published by MDPI AG in Applied Sciences
- Vol. 9 (23) , 5113
Attitude Control in Ascent Phase of Missile Considering Actuator Non-Linearity and Wind Disturbance
During the ascent phase of a missile, a challenging problem occurs that blocks the construction of a high-precision attitude control scheme, which directly affects accurate modeling including disturbances: non-linearities of an actuator, rapidly time-varying parameters, un-modeled dynamics, etc. In order to improve the control performance, an active disturbance rejection control (ADRC) scheme, considering non-linear dynamics of the actuator and wind disturbance during the ascent phase, is proposed in this paper. An expand state observer (ESO) is planned to estimate and compensate the actuator’s non-linear dynamics, flight model uncertainties, and wind disturbance. Therefore, the complex non-linear time-varying control problem is simplified into a linear time-invariant control problem. The pitch attitude control system is controlled by the cascade method and ADRC controllers are designed for actuator close loop and attitude control loop, respectively. The simulation results show that ADRC has strong robustness under different dead-zones and external disturbances of the actuator. On the other hand, ADRC can effectively suppress the external atmospheric disturbance. Compared with the traditional gain-scheduling control scheme, the ADRC scheme can significantly reduce the overloading of the system and shows remarkable performance for tracking as well as wind resistance.
- 26 November 2019
- Published by MDPI AG in Applied Sciences
- Vol. 9 (23) , 5113
Open AccessAttitude Control in Ascent Phase of Missile Considering Actuator Non-Linearity and Wind Disturbance
During the ascent phase of a missile, a challenging problem occurs that blocks the construction of a high-precision attitude control scheme, which directly affects accurate modeling including disturbances: non-linearities of an actuator, rapidly time-varying parameters, un-modeled dynamics, etc. In order to improve the control performance, an active disturbance rejection control (ADRC) scheme, considering non-linear dynamics of the actuator and wind disturbance during the ascent phase, is proposed in this paper. An expand state observer (ESO) is planned to estimate and compensate the actuator’s non-linear dynamics, flight model uncertainties, and wind disturbance. Therefore, the complex non-linear time-varying control problem is simplified into a linear time-invariant control problem. The pitch attitude control system is controlled by the cascade method and ADRC controllers are designed for actuator close loop and attitude control loop, respectively. The simulation results show that ADRC has strong robustness under different dead-zones and external disturbances of the actuator. On the other hand, ADRC can effectively suppress the external atmospheric disturbance. Compared with the traditional gain-scheduling control scheme, the ADRC scheme can significantly reduce the overloading of the system and shows remarkable performance for tracking as well as wind resistance.