Papers by jalal benmansour
International journal of space science and engineering, 2024
Algerian journal of signals and systems, Dec 30, 2023
Small satellites are becoming more popular because they are cost-effective, easy to assemble, and... more Small satellites are becoming more popular because they are cost-effective, easy to assemble, and use commercially available parts. However, traditional ground stations that communicate with small satellites require a lot of hardware and are expensive to build. This makes it challenging to get the most out of small satellites' information. Software Defined Radios (SDRs) have been developed to reduce the cost of these ground stations by doing many of the tasks in software. Many universities and organizations are developing SDR ground stations to communicate with satellites in different orbits. Communication with satellites is critical to their development and operation. This paper proposes a ground station that uses SDR technology to communicate with one or more small satellites in Low Earth Orbit (LEO). The station is costeffective, portable, and easily scaled, allowing it to acquire data from satellites.
This paper treats the problem of vibration mode and attitude control stabilization of a spacecraf... more This paper treats the problem of vibration mode and attitude control stabilization of a spacecraft with flexible appendage based on state feedback controller (SFC) and vibration suppression using disturbance observer (DO). The spacecraft has a central rigid body and large flexible appendage. The unwanted coupling torques in attitude dynamics that is generated by the vibration of large flexible appendage can affect the performance of attitude stabilization systems. By intergrading DO with SFC, the vibration torques can be reduced and the performance of the desired dynamic can be guaranteed. The Simulation results for flexible spacecraft are given to demonstrate the excellent performance of the composite control approach.
Journal of the Royal Aeronautical Society, Feb 7, 2023
This paper considers the problem of a three-axis flexible satellite attitude stabilisation subjec... more This paper considers the problem of a three-axis flexible satellite attitude stabilisation subject to the vibration of flexible appendages and external environmental disturbances, which affect the rigid body motion. To solve this problem, a disturbance observer is proposed to estimate and thereby reject the flexible appendage vibration. Based on the H∞ and Linear Matrix Inequality (LMI) approach, a controller for spacecraft with flexible appendages is proposed to ensure robustness as well as attitude stability with high precision. Stability analysis of the overall closed-loop system is provided via the Lyapunov method. The simulation results of three-axis flexible spacecraft demonstrate the robustness and effectiveness of the proposed method.
Algerian journal of signals and systems, Sep 30, 2021
In this paper, a robust control method for attitude stabilization flexible satellite and propella... more In this paper, a robust control method for attitude stabilization flexible satellite and propellant slosh torques suppression is proposed based on the combination of a composite disturbance observer (CDO) and feed-forward controller. First, a CDO is constructed to estimate the lumped disturbances, including, the external disturbing forces where the lumped disturbances in the system are equivalent into two parts: a slow varying disturbance and periodic disturbance. Then a PD controller is adopted to stabilize the system and restrain the residue disturbance. Finally, the simulation results for flexible satellite verify that the proposed method can make the satellite asymptotically stable and demonstrate the effectiveness of the proposed scheme.
Lecture notes in electrical engineering, Sep 30, 2020
Algerian Journal of Signals and Systems, 2018
The aim of this paper is to realize high-precision attitude stabilization for roll/yaw axes of fl... more The aim of this paper is to realize high-precision attitude stabilization for roll/yaw axes of flexible communication satellite while attenuate the effects of the elastic vibrations and multiple disturbances such as solar radiation and model uncertainties. a composite control has been designed which is comprise two part an anti-disturbance proportional-derivative (PD) controller is designed to stabilize the attitude while rejecting the effects of flexible vibrations, environmental disturbances, and unmodelled dynamics, whose are assumed as an extended state. This controller comprises two parts, i.e. an extended state observer and a PD controller with feedforward. First, flexible vibrations, environmental disturbances and unmodelled dynamics are regarded as an extended state, which can be estimated by the proposed observer. The estimated extended state can be compensated by feedforward where the attitude can be stabilized by the PD controller. Numerical simulation results are present...
This paper proposes an adaptive sliding-mode controller design for a three-axis stabilized rigid ... more This paper proposes an adaptive sliding-mode controller design for a three-axis stabilized rigid satellite attitude system with uncertain disturbances. The rigid satellite attitude control systems can be described by the dynamic equations and kinematic equations. This method combined sliding mode control and an adaptive algorithm, which is used to estimate the disturbances uncertainties. Tracking performance was guaranteed, as well as the stability of closed-loop attitude control systems which was analysed by using Lyapunov approach stability. The simulations results demonstrated the effectiveness of the proposed control method.
Both vibrations and model uncertainties will pose great challenges for accurate attitude control ... more Both vibrations and model uncertainties will pose great challenges for accurate attitude control of flexible spacecrafts. In this paper, an anti-disturbance proportional-derivative (PD) controller is designed to stabilize the attitude while rejecting the effects of flexible vibrations, environmental disturbances, and unmodeled dynamics, which are assumed as an extended state. This controller comprises two parts, i.e. an extended state observer and a PD controller with feedforward. First, flexible vibrations, environmental disturbances, and unmodeled dynamics are regarded as an extended state which can be estimated by the extended state observer. Then, the estimated extended state can be compensated by feedforward and the attitude can be stabilized by the PD controller. Numerical simulation results are presented to demonstrate the effectiveness of the control scheme.
Automatic Control and Computer Sciences, 2020
The new communication satellites are tricky in a control point of view, since their conceptions h... more The new communication satellites are tricky in a control point of view, since their conceptions have several sources of flexibilities: solar arrays and antennas which can be very large with respect to the main body and may lead to degradation of the performance of spacecraft attitude. This work aims to present a composite disturbance observer based controller (CDOBC) for flexible spacecraft is proposed to enhance the disturbance attenuation performance. The controller contains a composite disturbance observer (CDO) and a state feedback controller (SFC) plus feed-forward. First, the disturbance in the system is equivalent to two parts: slow varying disturbance and periodic disturbance control scheme. Thus, the disturbance can be modelled by a state equation and estimated by CDO according to the attitude rates. Then, the feed-forward is adopted to compensate the estimated disturbance and the state feedback controller is adopted to stabilize the system and restrain the residue disturbance. The simulation results demonstrate the effectiveness of the proposed method.
2022 2nd International Conference on Advanced Electrical Engineering (ICAEE)
Algerian Journal of Signals and Systems
This paper deals with the attitude tracking control problem of rigid satellite with uncertainties... more This paper deals with the attitude tracking control problem of rigid satellite with uncertainties of disturbances. An adaptive proportional derivative controller (PD) is proposed to deal with the influence of external disturbance in the attitude controller. The uncertain disturbances can be estimated through an adaptive algorithm and can be compensated in the proposed controller. The tracking error and the closed-loop system stability are ensured based on the Lyapunov analysis. using the representation of the spacecraft dynamics especially the quaternion properties.Simulation results can clearly illustrate the feasibility, the effectiveness and the performance of the planned control strategies, which have been validated by the Monte Carlo method, the results can be extended to other adaptive attitude control laws.
This paper proposes an adaptive sliding-mode controller design for a three-axis stabilized rigid ... more This paper proposes an adaptive sliding-mode controller design for a three-axis stabilized rigid satellite attitude system with uncertain disturbances. The rigid satellite attitude control systems can be described by the dynamic equations and kinematic equations. This method combined sliding mode control and an adaptive algorithm, which is used to estimate the disturbances uncertainties. Tracking performance was guaranteed, as well as the stability of closed-loop attitude control systems which was analysed by using Lyapunov approach stability. The simulations results demonstrated the effectiveness of the proposed control method.
Algerian Journal of Signals and Systems, 2021
In this paper, a robust control scheme is proposed for flexible satellite attitude stabilization ... more In this paper, a robust control scheme is proposed for flexible satellite attitude stabilization in the presence of multiple disturbances including the disturbances caused by flexible appendages with the sloshing dynamics of the liquid propellant and external disturbances from space environment. A composite control scheme is designed by combining a composite disturbance observer (CDO) with feed-forward controller. First, a CDO is constructed to estimate the lumped disturbances, where the lumped disturbances in the system are equivalent into two parts: a slow varying disturbance and periodic disturbance. Then a PD controller is adopted to stabilize the system and restrain the residue disturbance. Finally, the simulation results for flexible satellite verify that the proposed method can make the satellite asymptotically stable and demonstrate the effectiveness of the proposed scheme.
2015 34th Chinese Control Conference (CCC), 2015
Both vibrations and model uncertainties will pose great challenges for accurate attitude control ... more Both vibrations and model uncertainties will pose great challenges for accurate attitude control of flexible spacecrafts. In this paper, an anti-disturbance proportional-derivative (PD) controller is designed to stabilize the attitude while rejecting the effects of flexible vibrations, environmental disturbances, and unmodeled dynamics, which are assumed as an extended state. This controller comprises two parts, i.e. an extended state observer and a PD controller with feedforward. First, flexible vibrations, environmental disturbances, and unmodeled dynamics are regarded as an extended state which can be estimated by the extended state observer. Then, the estimated extended state can be compensated by feedforward and the attitude can be stabilized by the PD controller. Numerical simulation results are presented to demonstrate the effectiveness of the control scheme.
2018 International Conference on Electrical Sciences and Technologies in Maghreb (CISTEM), 2018
This paper treats the problem of vibration mode and attitude control stabilization of a spacecraf... more This paper treats the problem of vibration mode and attitude control stabilization of a spacecraft with flexible appendage based on state feedback controller (SFC) and vibration suppression using disturbance observer (DO). The spacecraft has a central rigid body and large flexible appendage. The unwanted coupling torques in attitude dynamics that is generated by the vibration of large flexible appendage can affect the performance of attitude stabilization systems. By intergrading DO with SFC, the vibration torques can be reduced and the performance of the desired dynamic can be guaranteed. The Simulation results for flexible spacecraft are given to demonstrate the excellent performance of the composite control approach.
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Papers by jalal benmansour