Robust finite time control algorithm for satellite attitude control

Li, You; Ye, Dong; Sun, Zhiyong

doi:10.1016/j.ast.2017.05.014

Cited by 25 publications

(21 citation statements)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The dynamic model of satellite with flexible appendages could be modeled as follows [5][6][7][8] ( )…”

Section: Dynamic and Kinematic Modelmentioning

confidence: 99%

“…Standard sliding mode controllers are modified to have better convergence rate. In Li and Ye's work [5][6][7][8], standard sliding mode is implemented to design attitude tracking controllers. The fixed sliding mode parameter is modified to be dynamic; the update law of control parameter is constructed hence the desired controller is derived.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Finite-Time Control Algorithm Based on Modal State Observer for Flexible Satellite Attitude Tracking

2020

IEEE Access

View full text Add to dashboard Cite

An attitude controller with finite time convergence rate for satellite attitude tracking issue considering the flexible dynamic based on a finite time modal state observer is proposed in this paper. The deformation of flexible appendages is taken into consideration and a finite-time state observer with auxiliary state to offset the initial error is proposed to get the flexible vibration estimation. The modal state and its derivative could be estimated by a full dimensional feedback observer. A finite time sliding mode based on the fraction order feedback of MRP is constructed and the finite time controller is proposed. The modal estimation is implied in controller design hence the counteraction of flexible system could be offset. System global finite-time stability is proved by Lyapunov method and the superiority is demonstrated by simulation results.

show abstract

“…The dynamic model of satellite with flexible appendages could be modeled as follows [5][6][7][8] ( )…”

Section: Dynamic and Kinematic Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Finite-Time Control Algorithm Based on Modal State Observer for Flexible Satellite Attitude Tracking

2020

IEEE Access

View full text Add to dashboard Cite

show abstract

“…Therefore, 1 , → 0 as → ∞. Finally, from the transformation in (10), it can be easily shown that → d as → ∞. Thus, the proposed controller achieves asymptotic tracking.…”

Section: Proposition 4 E Nonlinear Dynamics Of the Uncertain Scs Givmentioning

confidence: 75%

“…Nonlinear sliding mode control for attitude tracking of a magnetically actuated satellite is introduced in [9]. More recently, a three-stage sliding mode control for attitude tracking of a satellite system with uncertain inertia matrix and torque disturbance has been proposed [10]. Attitude control of a rigid body with uncertain inertia matrix using sliding mode control along with a state observer has also been addressed [11].…”

Section: Introductionmentioning

confidence: 99%

Design of Robust Observer-Based Backstepping Control for a Satellite Control System

Alshamali

Aljuwaiser

2019

Mathematical Problems in Engineering

View full text Add to dashboard Cite

This paper presents the attitude tracking of a class of satellite control systems under external disturbances. Once the error dynamics of the satellite are obtained, a nonlinear transformation expresses them in a suitable representation for the design of a high-gain observer and backstepping control. The observer-based backstepping controller is then designed to drive the angles of the satellite dynamics to their desired values in the presence of exogenous disturbances. Closed-loop stability of the proposed controller is demonstrated via Lyapunov theory, and its effectiveness is confirmed through numerical simulations.

show abstract

“…Having the estimate of the current attitude, the controller issues torque commands for desired orientation [9], [21], [22]. The closed loop feedback ensures the maintenance of desired attitude control by repeating the torque command until the desired orientation is achieved [23], [24], [25], [26].…”

Section: Fig 2 a Multilayered Panel With Printed Magnetorquermentioning

confidence: 99%

Optimized Design and Thermal Analysis of Printed Magnetorquer for Attitude Control of Reconfigurable Nanosatellites

Mughal

Ali

et al. 2020

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

Attitude Control System (ACS) is one of the critical subsystems of any spacecraft andtypically is in charge of de-tumbling, controlling and orienting the satellite after initial deployment and during the satellite operations. The magnetorquer is a core magnetic attitude control actuator and, therefore, a good choice for nanosatellite attitude stabilization. There are various methods to achieve control torque using the magnetorquer. An innovative design of printed magnetorquer has been proposed for the nanosatellites which is modular, scalable, cost effective, less prone to failure, with reduced harness and power consumption since the traces are printed either on top layer or inner layers of the printed circuit board. The analysis in terms of generated torque with a range of input applied voltages, trace widths, outer and inner-most trace lengths is presented to achieve the optimized design.The optimum operating voltage is selected to generate the desired torque while optimizing the torque to the power ratio. The results of analysis in terms of selection of optimized parameters including torque to power ratio, generated magnetic dipole moment and power consumption have been validated practically on a cubesat panel. The printed magnetorquer configuration is modular which is useful to achieve mission level stabilization requirements. For spin stabilized satellites, the rotation time analysis has been performed using the printed magnetorquer.

show abstract

Robust finite time control algorithm for satellite attitude control

Cited by 25 publications

References 24 publications

Finite-Time Control Algorithm Based on Modal State Observer for Flexible Satellite Attitude Tracking

Finite-Time Control Algorithm Based on Modal State Observer for Flexible Satellite Attitude Tracking

Design of Robust Observer-Based Backstepping Control for a Satellite Control System

Optimized Design and Thermal Analysis of Printed Magnetorquer for Attitude Control of Reconfigurable Nanosatellites

Contact Info

Product

Resources

About