Space systems design (spacecraft, satellites, space stations and their equipment)
Mohammad Razmjooei; Mohammad Shahbazi; Fathollah Ommi
Volume 14, Issue 2 , June 2021, , Pages 1-26
Abstract
In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating ...
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In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating conditions and compare the performance of these insulators. The heat and mass transfer equations are considered in two dimensions in a solid body. We used the equations, finite volume method with implicit formulation for time dependency to solve equations. The reaction equation which written in the form of Arrhenius, is solved using Runge-Kutta method, and the density and the flux of the gas produced at each step are obtained. Also we represent a model for the rate of recession.
Space systems design (spacecraft, satellites, space stations and their equipment)
mohammad razmjooei; mohammad shahbazi; Fathollah Ommi
Volume 13, Issue 2 , June 2020, , Pages 13-35
Abstract
In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating ...
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In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating conditions and compare the performance of these insulators. The heat and mass transfer equations are considered in two dimensions in a solid body. We used the equations, finite volume method with implicit formulation for time dependency to solve equations. The reaction equation which written in the form of Arrhenius, is solved using Runge-Kutta method, and the density and the flux of the gas produced at each step are obtained. Also we represent a model for the rate of recession.
Amirhossein Edalatpour; Fatholah Ommi; Zoheir Saboohi
Volume 12, Issue 1 , April 2019, , Pages 23-40
Abstract
Micro-propulsion Systems are low thrust engines that be used in space missions like keeping satellite in orbit and changing orbit. These engines have several kinds and liquid propellant micro-propulsion is used in this project. In two propellant micro-propulsion systems, various fuels and oxidizers can ...
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Micro-propulsion Systems are low thrust engines that be used in space missions like keeping satellite in orbit and changing orbit. These engines have several kinds and liquid propellant micro-propulsion is used in this project. In two propellant micro-propulsion systems, various fuels and oxidizers can be used. Kerosene is used as fuel and liquid oxygen is used as oxidizer in this project. First of all, a micro-propulsion is designed and analysis of combustion, heat transfer, nozzle exit flow and amount of performance’s parameters is done with RPA software. Similar to big engines, micro-propulsion systems have injectors, injection plate, combustion chamber and nozzle. Design of all of this parts will be explained. With manufacturing of designed model and perform hot fire test, accurate performance of engine is observed. Finally, performance’s parameters in hot fire test are compared with performance’s parameters in RPA.
Mohmmad Goharkhah; Mostafa Esmaeili; Mehdi Ashjaee
Volume 11, Issue 2 , September 2018, , Pages 11-19
Abstract
In this paper, the effect of an external non-uniform magnetic field on forced convective heat transfer of magnetite nanofluid (ferrofluid) in a heated channel is studied numerically. The main goal is to emphasize the importance of magnetic field location and investigate the possibility of heat transfer ...
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In this paper, the effect of an external non-uniform magnetic field on forced convective heat transfer of magnetite nanofluid (ferrofluid) in a heated channel is studied numerically. The main goal is to emphasize the importance of magnetic field location and investigate the possibility of heat transfer enhancement by finding the optimum location of magnetic field source.It is observed that the magnetic field results in creation of recirculation zones which affect the thermal boundary layer thickness and Nusselt number. Results show that the effect of magnetic field location on the heat transfer is completely dependent on the thermal boundary condition. It is also shown that the flow and temperature fields can be manipulated by application of multiple magnetic field sources. Using genetic algorithm (GA), an optimum arrangement for locations of eight magnetic field sources is obtainedresulting in a27% heat transfer enhancement compared to the case of no magnetic field.
