Yufei Liu
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Research Subjects
Yufei Liu has a total of 12 co-authors. Here are the top co-authors by number of shared publications:
- Gang Zhang
Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150080, China
1 shared publication - Gianmarco Radice
School of Engineering, University of Glasgow, Glasgow G12 8QQ, UK
1 shared publication - Junhui Zhang
North China University of Technology, 100144 Beijing, People’s Republic of China
1 shared publication Meigen Cao
North China University of Technology, 100144 Beijing, People’s Republic of China
1 shared publication- Mingying Huo
Department of Aerospace Engineering, Harbin Institute of Technology, Harbin 150001, China
1 shared publication - Naiming Qi
Harbin Institute of Technology
1 shared publication
Latest Publications
- 1 October 2020
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 58 (10) , 4600-4603
Can Boom-Supported Solar Sails Flutter?
- 1 October 2020
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 58 (10) , 4600-4603
Can Boom-Supported Solar Sails Flutter?
- 27 March 2019
- Published by Institute of Electrical and Electronics Engineers (IEEE) in IEEE Transactions on Aerospace and Electronic Systems
- Vol. 55 (6) , 3674-3683
Initial Trajectory Design of Electric Solar Wind Sail Based on Finite Fourier Series Shape-Based Method
Electric solar wind sail (E-sail) is an innovative propulsion system, which can generate low and continuous thrust without any propellant by reflecting ions from the solar wind. Because the propulsive acceleration of E-sail is low and continuous, its trajectory is usually characterized by long flight time. In order to explore more flight plans, rapid trajectory design is useful for preliminary mission analysis and design. This paper presents a method for rapid generation of minimum-time, three-dimensional trajectories for an E-sail using the finite Fourier series shapebased method. Unlike the more conventional electric thruster, the thrust vector of an E-sail is constrained. In order to consider the characteristics of the E-sail thrust, inequality constraints of thrust acceleration are investigated based on a recent thrust model. The numerical simulation results show that the proposed method is useful to quickly design the flight trajectory of the E-sail by considering the actual characteristics of the thrust vector
- 27 March 2019
- Published by Institute of Electrical and Electronics Engineers (IEEE) in IEEE Transactions on Aerospace and Electronic Systems
- Vol. 55 (6) , 3674-3683
Initial Trajectory Design of Electric Solar Wind Sail Based on Finite Fourier Series Shape-Based Method
Electric solar wind sail (E-sail) is an innovative propulsion system, which can generate low and continuous thrust without any propellant by reflecting ions from the solar wind. Because the propulsive acceleration of E-sail is low and continuous, its trajectory is usually characterized by long flight time. In order to explore more flight plans, rapid trajectory design is useful for preliminary mission analysis and design. This paper presents a method for rapid generation of minimum-time, three-dimensional trajectories for an E-sail using the finite Fourier series shapebased method. Unlike the more conventional electric thruster, the thrust vector of an E-sail is constrained. In order to consider the characteristics of the E-sail thrust, inequality constraints of thrust acceleration are investigated based on a recent thrust model. The numerical simulation results show that the proposed method is useful to quickly design the flight trajectory of the E-sail by considering the actual characteristics of the thrust vector
- Open Access
Autonomous Pointing Control of a Large Satellite Antenna Subject to Parametric Uncertainty
With the development of satellite mobile communications, large antennas are now widely used. The precise pointing of the antenna’s optical axis is essential for many space missions. This paper addresses the challenging problem of high-precision autonomous pointing control of a large satellite antenna. The pointing dynamics are firstly proposed. The proportional–derivative feedback and structural filter to perform pointing maneuvers and suppress antenna vibrations are then presented. An adaptive controller to estimate actual system frequencies in the presence of modal parameters uncertainty is proposed. In order to reduce periodic errors, the modified controllers, which include the proposed adaptive controller and an active disturbance rejection filter, are then developed. The system stability and robustness are analyzed and discussed in the frequency domain. Numerical results are finally provided, and the results have demonstrated that the proposed controllers have good autonomy and robustness.
Open AccessAutonomous Pointing Control of a Large Satellite Antenna Subject to Parametric Uncertainty
With the development of satellite mobile communications, large antennas are now widely used. The precise pointing of the antenna’s optical axis is essential for many space missions. This paper addresses the challenging problem of high-precision autonomous pointing control of a large satellite antenna. The pointing dynamics are firstly proposed. The proportional–derivative feedback and structural filter to perform pointing maneuvers and suppress antenna vibrations are then presented. An adaptive controller to estimate actual system frequencies in the presence of modal parameters uncertainty is proposed. In order to reduce periodic errors, the modified controllers, which include the proposed adaptive controller and an active disturbance rejection filter, are then developed. The system stability and robustness are analyzed and discussed in the frequency domain. Numerical results are finally provided, and the results have demonstrated that the proposed controllers have good autonomy and robustness.