scholarly journals An implementation of optimal control methods (LQI, LQG, LTR) for geostationary satellite attitude control

2019 ◽  
Vol 9 (6) ◽  
pp. 4728
Author(s):  
Farid Djaballah ◽  
M. A. Si Mohammed ◽  
Nabil Boughanmi
Keyword(s):  
Numerical Simulation ◽  
Dynamic Model ◽  
Attitude Control ◽  
Geostationary Satellite ◽  
Attitude Motion ◽  
Linear Quadratic ◽  
Integer Order ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Attitude Controller

<p>This paper investigates a new strategy for geostationary satellite attitude control using<strong> </strong>Linear Quadratic Gaussian (LQG), Loop Transfer Recovery (LTR), and Linear Quadratic Integral (LQI) control techniques. The sub-system satellite attitude determination and control of a geostationary satellite in the presence of external disturbances, the dynamic model of sub-satellite motion is firstly established by Euler equations. During the flight mission at 35000 Km attitude, the stability characteristics of attitude motion are analyzed with a large margin error of pointing, then a height performance-order LQI, LQG and LTR attitude controller are proposed to achieve stable control of the sub-satellite attitude, which dynamic model is linearized by using feedback linearization method.<strong> </strong>Finally, validity of the LTR order controller and the advantages over an integer order controller are examined by numerical simulation. Comparing with the corresponding integer order controller (LQI, LQG), numerical simulation results indicate that the proposed sub-satellite attitude controller based on LTR order can not only stabilize the sub-satellite attitude, but also respond faster with smaller overshoot.</p><p> </p>

scholarly journals Satellite Attitude Control System Design considering the Fuel Slosh Dynamics

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Luiz Carlos Gadelha de Souza ◽  
Alain G. de Souza
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Rigid Motion ◽  
Linear Quadratic Regulator ◽  
Solar Panels ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Fuel Slosh

The design of the satellite attitude control system (ACS) becomes more complex when the satellite structure has different type of components like, flexible solar panels, antennas, mechanical manipulators, and tanks with fuel. A crucial interaction can occur between the fuel slosh motion and the satellite rigid motion during translational and/or rotational manoeuvre since these interactions can change the satellite centre of mass position damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances thus affecting the satellite attitude acquisition. As a result, the design of the satellite controller needs to explore the limits between the conflicting requirements of performance and robustness. This paper investigates the effects of the interaction between the liquid motion (slosh) and the satellite dynamics in order to predict what the damage to the controller performance and robustness is. The fuel slosh dynamics is modelled by a pendulum which parameters are identified using the Kalman filter technique. This information is used to design the satellite controller by the linear quadratic regulator (LQR) and linear quadratic Gaussian (LQG) methods to perform a planar manoeuvre assuming thrusters are actuators.

Optimal robust control approaches for a geostationary satellite attitude control

2020 ◽  
Vol 14 (3) ◽  
pp. 333
Author(s):  
Naeimeh Najafizadeh Sari ◽  
Hadi Jahanshahi ◽  
Mahdi Fakoor ◽  
Christos Volos ◽  
Peyman Nikpey
Keyword(s):  
Robust Control ◽  
Attitude Control ◽  
Geostationary Satellite ◽  
Satellite Attitude ◽  
Satellite Attitude Control

Design of Satellite Attitude Control System Considering the Interaction between Fuel Slosh and Flexible Dynamics during the System Parameters Estimation

2014 ◽  
Vol 706 ◽  
pp. 14-24 ◽  
Author(s):  
Alain G. de Souza ◽  
Luiz C.G. de Souza
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Rigid Motion ◽  
Parameters Estimation ◽  
System Stability ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Fuel Slosh

The design of the satellite Attitude Control System (ACS) becomes more complex when the satellite structure has different type of components like, flexible solar panels, antennas, mechanical manipulators and tanks with fuel, since the ACS performance and robustness will depend if the dynamics interaction effects between these components are considered in the satellite controller design. A crucial interaction can occur between the fuel slosh motion and the satellite rigid motion during translational and/or rotational maneuver since these interactions can change the satellite center of mass position damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances affecting thus the satellite attitude acquisition. It is known that one way to minimize such problems is to design controllers with a bandwidth below the lowest slosh and/orvibration mode which can result in slow maneuvers inconsistent with the space mission requirements. As a result, the design of the satellite controller needs to explore the limits between the conflicting requirements of performance and robustness. This paper investigates the effects of the interaction between the liquid motion (slosh) and the flexible satellite dynamics in order to predict what the damage to the controller performance and robustness is. The fuel slosh dynamics is modeled using its pendulum analogs mechanical system which parameters are identified using the Kalman filter technique. This information is used to designs and to compare the satellite attitude control system by the Linear Quadratic Regulator (LQR) and the Linear Quadratic Gaussian (LQG methods. Besides, one investigates the effects of the rod length estimation in the plant of the system stability. This investigation has shown that the poles of the plant to walk to and from the imaginary axis, leaving in the end the plant more stable.

Optimal robust control approaches for a geostationary satellite attitude control

2020 ◽  
Vol 14 (3) ◽  
pp. 333
Author(s):  
Mahdi Fakoor ◽  
Christos Volos ◽  
Peyman Nikpey ◽  
Hadi Jahanshahi ◽  
Naeimeh Najafizadeh Sari
Keyword(s):  
Robust Control ◽  
Attitude Control ◽  
Geostationary Satellite ◽  
Satellite Attitude ◽  
Satellite Attitude Control

scholarly journals Satellite Attitude Control Using Control Moment Gyroscopes

2020 ◽  
pp. 94-105
Author(s):  
Kenedy Matiasso Portella ◽  
Wilcker Neuwald Schinestzki ◽  
Róger Mateus Sehnem ◽  
Leonardo Barros da Luz ◽  
Lorenzzo Quevedo Mantovani ◽  
...  
Keyword(s):  
Attitude Control ◽  
Angular Momentum Vector ◽  
Attitude Control System ◽  
Linear Quadratic ◽  
Control Laws ◽  
Final Choice ◽  
Satellite Attitude ◽  
Control Moment ◽  
Satellite Attitude Control ◽  
Control Moment Gyroscopes

In space missions, there is often a need for an attitude control system capable of maintaining the desired attitude. In situations that require agile and accurate responses, which also require large torques, control moment gyroscopes (CMGs) may be used. Control moment gyroscopes are high angular moment gyros mounted on gimbals and are responsible for changing the direction of the angular momentum vector, consequently generating the control torques. There are several linear and nonlinear techniques that can be employed in the design of control laws with the final choice being a compromise between simplicity, effectiveness, efficiency and robustness. The main objective of this study is to evaluate the performance of control systems techniques with 4 CMGs in a pyramidal arrangement, either by using Linear Quadratic Tracker (LQT) with integral compensator or Exponential Mapping Control (EMC). A reference attitude will be defined to be traced in the presence of disturbance torques caused by the gravitational gradient.

scholarly journals Satellite attitude control using environmental forces based on variable structure control

2021 ◽  
Author(s):  
Tarunkumar Patel
Keyword(s):  
Numerical Simulation ◽  
Control Strategy ◽  
Attitude Control ◽  
Variable Structure Control ◽  
Variable Structure ◽  
Parameter Uncertainties ◽  
Space Applications ◽  
Structure Control ◽  
Satellite Attitude ◽  
Satellite Attitude Control

The present thesis examines the use of environmental forces for satellite attitude control using variable structure control. The system comprises of a satellite with control flaps to utilize environmental forces such as solar radiation pressure and aerodynamic forces. A variable structure control approach has been adopted to develop control law for suitably rotating the control flaps to achieve desired satellite attitude performance. The detailed numerical simulation of the governing nonlinear system equation of motion including the effects of various system parameters on the controller performance establishes the effectiveness of the proposed control strategy. The numerical simulation matches with the analytical results. Furthermore from analysis, the proposed controller is found to be robust against parameter uncertainties and external disturbances and its performance is superior in comparison to other strategies proposed in the literature. Thus, the robustness of the proposed control strategy and utilizing natural environmental forces for attitude control makes the proposed concept attractive for future space applications.

scholarly journals Satellite attitude control using environmental forces based on variable structure control

2021 ◽  
Author(s):  
Tarunkumar Patel
Keyword(s):  
Numerical Simulation ◽  
Control Strategy ◽  
Attitude Control ◽  
Variable Structure Control ◽  
Variable Structure ◽  
Parameter Uncertainties ◽  
Space Applications ◽  
Structure Control ◽  
Satellite Attitude ◽  
Satellite Attitude Control

The present thesis examines the use of environmental forces for satellite attitude control using variable structure control. The system comprises of a satellite with control flaps to utilize environmental forces such as solar radiation pressure and aerodynamic forces. A variable structure control approach has been adopted to develop control law for suitably rotating the control flaps to achieve desired satellite attitude performance. The detailed numerical simulation of the governing nonlinear system equation of motion including the effects of various system parameters on the controller performance establishes the effectiveness of the proposed control strategy. The numerical simulation matches with the analytical results. Furthermore from analysis, the proposed controller is found to be robust against parameter uncertainties and external disturbances and its performance is superior in comparison to other strategies proposed in the literature. Thus, the robustness of the proposed control strategy and utilizing natural environmental forces for attitude control makes the proposed concept attractive for future space applications.

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