Hadi Hosseini Onari; ehsan maani; Vahid Bohlouri; Soheil Seyedzamani
Volume 10, Issue 4 , March 2018, , Pages 19-28
Abstract
In this study, hardware in the loop (HIL) simulation consisting of solar array simulator, programmable electric load, charger board, distribution board and attitude and position simulator is designed and developed for the mentioned purpose. Because of satellite high angular velocity ...
Read More
In this study, hardware in the loop (HIL) simulation consisting of solar array simulator, programmable electric load, charger board, distribution board and attitude and position simulator is designed and developed for the mentioned purpose. Because of satellite high angular velocity in de-tumbling mode, it is not possible to perform the experimental tests for power consumption analysis. Electricalpower HIL can be used for modifying, redesigning, and verification of the electricalpower subsystem design. The power consumption of communications satellite components is simulated in a de-tumbling mode. De-tumbling mode of operation is implemented in HIL test bed and the experimental results are extracted. The results consisting of battery voltage, battery capacity, current, depth of discharge and voltage stability are investigated. The results of this paper can be useful in the design, implementation and verification of electrical power subsystem for a wide range of satellites from LEO to GEO.
Vahid Bohlouri; S.H Jalali-Naini
Volume 10, Issue 4 , March 2018, , Pages 55-66
Abstract
his paper suggests arobust optimization algorithm for the design of the satellite attitude control system in order to increase the robustness of the performance under uncertainties. A single-axis on-off attitude control with rigid dynamics is considered using Schmitt-Trigger and PID controller. The model ...
Read More
his paper suggests arobust optimization algorithm for the design of the satellite attitude control system in order to increase the robustness of the performance under uncertainties. A single-axis on-off attitude control with rigid dynamics is considered using Schmitt-Trigger and PID controller. The model uncertainties include the moment of inertia, thrust level, thruster delay and theexternal disturbance amplitude.A weighted combination of expected value and standard deviation of pointing error is considered as an objective function for the robust optimization. The numerical solutions show that the robust optimization reduces the variations of the objective function, i.e. it increases the robustness of the system performance compared to the deterministic optimization.
