Space systems design (spacecraft, satellites, space stations and their equipment)
Hamed Alisadeghi; Azade Khadivi; Ehsan Zabihian
Volume 15, Issue 2 , June 2022, , Pages 43-58
Abstract
The interaction of thruster plumes with satellite components can have undesirable effects, such as disturbance force/torque, thermal loading, and species deposition in the surfaces. The purpose of this paper is to use the Direct Simulation Monte Carlo (DSMC) method to analyze the 3D plume impingement ...
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The interaction of thruster plumes with satellite components can have undesirable effects, such as disturbance force/torque, thermal loading, and species deposition in the surfaces. The purpose of this paper is to use the Direct Simulation Monte Carlo (DSMC) method to analyze the 3D plume impingement flows and investigate its effects. Two impingement problems are computed. The impact of a jet of nitrogen on an inclined flat plate is considered. Good agreement is found between surface quantities calculated by DSMC and experimental data. The plume of a hydrazine control thruster firing in a model satellite configuration is simulated. Surface quantities and net impingement effects are calculated. The effects of partial displacement of the thruster locations on the results have also been investigated. The results show that a 20% displacement of the thruster location can change the disturbance force/torque by up to 15% of the initial values.
hamed Alisadesghi; Hamed Ramezani-Najafi; Hossein Reza Abbasi
Volume 9, Issue 2 , September 2016, , Pages 61-76
Abstract
Base on space standards, the thermal design evaluations for satellites are performed using thermal balance tests. Regularly, the thermal model is used for the thermal balance test. This model is completely similar to the flight model of the satellite in terms of thermal characteristics. In this paper, ...
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Base on space standards, the thermal design evaluations for satellites are performed using thermal balance tests. Regularly, the thermal model is used for the thermal balance test. This model is completely similar to the flight model of the satellite in terms of thermal characteristics. In this paper, the definition and implementation of thermal balance tests for Thermal model of AUTSAT Satellite is conducted. the evaluation of the TM and the procedure data Correlation of the numerical model have been focused. In order to increase the accuracy and feasibility of thermal mathematical model correlation, structural and complete models are considered for the balance test separately. In this study, the results of thermal balance test for the structural thermal model has been compared with the numerical analysis and the correlation procedure is illustrated. The results achieved by this procedure shows that all the requirements by the standard are satisfied in this level.
