Sizing/Optimization of a Small Satellite Energy Storage and Attitude Control System

2006 ◽  
Author(s):  
David J. Richie ◽  
Vaios J. Lappas ◽  
Phil L. Palmer
Keyword(s):  
Control System ◽  
Energy Storage ◽  
Attitude Control ◽  
Small Satellite ◽  
Attitude Control System ◽  
Sizing Optimization

Design of Semi-Physical Simulation for Small Satellite by Virtual Display

2011 ◽  
Vol 130-134 ◽  
pp. 2684-2687 ◽  
Author(s):  
Kai Xu ◽  
Yan Lv ◽  
Guang Jin
Keyword(s):  
Control System ◽  
Real Time ◽  
Attitude Control ◽  
Physical Simulation ◽  
Simulation System ◽  
Space Environment ◽  
Small Satellite ◽  
Attitude Control System ◽  
Actual Environment ◽  
Virtual Display

Semi-physical simulation of attitude control system is the more synthetically test and verify for designing of small satellite control system. It is an important means of small satellite development. However, the results of current semi-physical simulation system have a lot of non-intuitive. Compare with the actual environment, the simulation environment still has striking disparity. So the shortcomings affect precision of simulation. Based on the virtual display technology, the group semi-physical simulation system has been constructed for attitude control of small satellite due to the combination with xPC real-time environment, the simulation computer, high-precision single-axis air-bearing turntable, reaction wheel, air thrust device, fiber gyroscopes, sensors synchronizer, power subsystem and wireless devices virtual display computer etc. Semi-physical simulation achieved the visual simulation in orbit and tracked new information of virtual environment of space into real-time simulation computer. Simulation results show that the simulation system for real-time attitude and orbit position of small satellite semi-physical simulation has an excellent display effect. At the same time, Real-time transfuse of orbit information provides a more accurate space environment simulation. The simulation system of small satellite attitude control to design and evaluate the more direct and convenient.

Design and Verification of Attitude Control System for A Small Satellite

2021 ◽  
Author(s):  
Shuyan Ni ◽  
Shimiao Chen ◽  
Yurong Liao ◽  
Naiping Cheng
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Small Satellite ◽  
Attitude Control System

scholarly journals Optimal Control for Combined Energy Storage and Attitude Control System (CEACS) in Small Satellites

2011 ◽  
Vol 110-116 ◽  
pp. 3587-3592 ◽  
Author(s):  
Ban Ying Siang ◽  
Renuganth Varatharajoo
Keyword(s):  
Control System ◽  
Energy Storage ◽  
Attitude Control ◽  
Control Methods ◽  
Attitude Control System ◽  
H Infinity ◽  
Small Satellites ◽  
Satellite Attitude Control ◽  
H Infinity Control ◽  
Control Modules

The combined energy storage and attitude control system (CEACS) combines both energy storage and attitude control modules via the flywheel technology. Previously only the conventional control methods were tested for CEACS. In this paper, H2 and H-infinity control methods are implemented in CEACS. The satellite attitude control performances show that both control options can be employed for a good attitude pointing accuracy. (Abstract)

scholarly journals Sliding Mode Control Techniques for Combined Energy and Attitude Control System

2014 ◽  
Vol 629 ◽  
pp. 310-317 ◽  
Author(s):  
Samira Eshghi ◽  
Renuganth Varatharajoo
Keyword(s):  
Control System ◽  
Energy Storage ◽  
Attitude Control ◽  
Sliding Mode ◽  
Storage System ◽  
Energy Storage System ◽  
Storage Device ◽  
Optimization Approach ◽  
Attitude Control System ◽  
The Mathematical Model

Combined Energy and Attitude Control System (CEACS) is an optimization approach that combines the energy storage system and the attitude control system. With a double counter rotating flywheel simultaneously serving as energy storage device and as attitude control actuator, CEACS requires an accurate control strategy to obtain the mission requirements. In addition, it is important to design the control law to be invariant to uncertainties and disturbances, and guarantee robustness as CEACS inherits these in-orbit uncertainties. This paper presents a nonlinear control employing sliding mode to enhance the CEACS attitude control capability. The mathematical model for the conventional and boundary layer sliding mode controls are developed herein for CEACS. The controller provides enhancement in pointing accuracies, reasonable transient responses and a robustness against uncertainties and in-orbit disturbances.

An active force controlled of small CMG-based satellite

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Mohd Badrul Salleh ◽  
Nurulasikin Mohd Suhadis ◽  
Renuganth Varatharajoo
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Pd Controller ◽  
Active Force ◽  
Small Satellite ◽  
Attitude Control System ◽  
Content Type ◽  
Satellite Attitude ◽  
Attitude Maneuver ◽  
Significant Difference

Purpose This paper aims to investigate the attitude control pointing improvement for a small satellite with control moment gyroscopes (CMGs) using the active force control (AFC) method. Design/methodology/approach The AFC method is developed with its governing equations and integrated into the conventional proportional-derivative (PD) controller of a closed-loop satellite attitude control system. Two numerical simulations of an identical attitude control mission namely the PD controller and the PD+AFC controller were carried out using the MATLAB®-SimulinkTM software and their attitude control performances were demonstrated accordingly. Findings Having the PD+AFC controller, the attitude maneuver can be completed within the desired slew rate, which is about 2.14 degree/s and the attitude pointing accuracies for the roll, pitch and yaw angles have improved significantly by more than 85% in comparison with the PD controller alone. Moreover, the implementation of the AFC into the conventional PD controller does not cause significant difference on the physical structure of the four single gimbal CMGs (4-SGCMGs). Practical implications To achieve a precise attitude pointing mission, the AFC method can be applied directly to the existing conventional PD attitude control system of a CMG-based satellite. In this case, the AFC is indeed the backbone for the satellite attitude performance improvement. Originality/value The present study demonstrates that the attitude pointing of a small satellite with CMGs is improved through the implementation of the AFC scheme into the PD controller.

FDD of the Attitude Control System of Satellite with Actuator Fault and Time Delay via Two-Stage Kalman Filter

2013 ◽  
Vol 441 ◽  
pp. 859-863 ◽  
Author(s):  
Cheng Liang Li ◽  
Xue Qin Chen ◽  
Qing Xian Jia ◽  
Yun Hai Geng
Keyword(s):  
Kalman Filter ◽  
Control System ◽  
Time Delay ◽  
Attitude Control ◽  
Actuator Fault ◽  
Small Satellite ◽  
Coordination Control ◽  
Attitude Control System ◽  
Altitude Control ◽  
Input Time

The recent decades have witnessed active studies in fault detection and isolation (FDD) of the small satellites subject to actuator failures and attitude coordination control of spacecraft formation flying (SFF) which plays a significant role in missions such as synthetic-aperture radar imaging. However, because of the time delay in communication links, the performance of coordination control is not always satisfactory. In this paper we propose a method to estimate the actuator fault as well as the input time delay at the same time. First of all, the model of the altitude control system of the small satellite with actuator fault and the model of the altitude control system with actuator fault and the input time delay are presented respectively. Based on the Two-Stage Kalman Filter algorithm, the fault and input time delay of the altitude control system of the small satellite can be estimated. At last, the simulation of the algorithm in a satellite attitude control system with actuator fault and input time delay will illustrate the effectiveness of the proposed approach.

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