Volume 15 (2022)
Volume 14 (2021)
Volume 13 (2020)
Volume 12 (2019)
Volume 11 (2018)
Volume 10 (2017)
Volume 9 (2016)
Volume 8 (2015)
Volume 7 (2014)
Volume 6 (2013)
Volume 5 (2012)
Volume 4 (2011)
Volume 3 (2010)
Volume 2 (2009)
Volume 1 (2008)
Space Science and Technology
Numerical study on the effects of nozzle geometry and creating swirly flow inside the injector nozzle on the performance of an engine

Amirhamzeh Farajollahi; Reza Firuzi; Mohammad Reza Salimi; Mohsen Rostami

Articles in Press, Accepted Manuscript, Available Online from 03 July 2021

https://doi.org/10.30699/jsst.2021.249117.1303

Abstract
  In this study, the effects of geometry and spiral rifling like guides inside the injection nozzle on the performance of an engine are investigated, using AVL Fire software. To do so, firstly injectors with different nozzle geometries and their resultant spray patterns were simulated. Numerical results ...  Read More

Design and Configuration of Ground Sample Components of Low Propulsion Monopropellant Thruster Using Some Engineering Software

sajjad Davari; Hadiseh Karimaei; Mohammad Reza Salimi; Hassan Naseh

Articles in Press, Accepted Manuscript, Available Online from 21 September 2021

https://doi.org/10.30699/jsst.2021.260620.1319

Abstract
  Monopropellant thruster are used to inject a satellite into orbit or control its position on three axes in space missions. One of them is hydrazine thruster which is widely used. In this research, design of the injector, decomposition chamber and nozzle of a 10N hydrazine monopropellant thruster have ...  Read More

Space Science and Technology
Optimized Dimension Design of Catalytic Chamber of a 10 N Thruster

Hadiseh Karimaei; Hadiseh Karimaei; Mohammad Reza Salimi; Hassan Naseh

Articles in Press, Accepted Manuscript, Available Online from 21 September 2021

https://doi.org/10.30699/jsst.2021.271152.1332

Abstract
  In this paper, the catalyst bed of a 10 N hydrazine monopropellant thruster was designed. The catalyst bed is including iridium granules, which is used to decompose the hydrazine in monopropellant thruster. Hydrazine must be decomposed almost completely in the catalytic chamber, because it is a carcinogenic ...  Read More

Infrastructure (labs, sensors, software,…)
Design, Construction and Performance Evaluation of a Cold Gas Thruster Test Stand

َAlireza Alikhani; Mohammad Reza Salimi

Volume 15, Issue 1 , May 2022

https://doi.org/10.30699/jsst.2021.250452.1305

Abstract
  The cold gas thruster is one of the significant components of a satellite and its application possesses a marked impact on the entire system performance. The nonlinear function and order of magnitude, lead to increasing the importance of thruster function. Therefore, pre-mission performance assessment ...  Read More

Space Science and Technology
Effects of geometrical parameters of a two-sided catalyst bed on flow and thermal fields of a monopropellant hydrazine thruster

Mohammad Reza Salimi

Volume 15, Issue 1 , March 2022, , Pages 93-110

https://doi.org/10.22034/jsst.2021.240233.1291

Abstract
  In present study, a hydrazine based monopropellant thruster decomposition chamber is simulated numerically. The catalyst bed separated in two sides, the particles size in upstream side is larger than those in downstream side. Effects of upstream side length and its particles diameter on catalyst bed ...  Read More

Design of Physical Configuration of a 10N Monopropellant Hydrazine Thruster

Hadiseh Karimaei; Mohammad Reza Salimi; Hassan Naseh; Ehsan Jokari

Volume 12, Issue 1 , April 2019, , Pages 13-22

https://doi.org/10.30699/jsst.2019.1115

Abstract
  In this paper, design and physical configuration of various components of a 10N Monopropellant Hydrazine Thruster focusing on design calculations and optimization of catalytic combustion chamber. According to this design, a prototype of the thruster will be manufactured. The mentioned thruster has been ...  Read More

Equilibrium Effects on the Hypersonic Laminar Boundary Layer Flow over Axisymmetric Bodies

Ramin Kamali Moghadam; Mohammad Reza Salimi

Volume 8, Issue 4 , January 2016, , Pages 19-27

Abstract
  An accurate and efficient computational procedure is developed to predict the laminar hypersonic flowfield for both the perfect gas and equilibrium air around the axisymmetric blunt body configurations. To produce this procedure, the boundary layer equations utilize the integral matrix solution algorithm ...  Read More

Assessment of Solution of the Boundary Layer Equations and Approximate Relations for Aeroheating of Axisymmetric Reentry Vehicles

رامین کمالی مقدم; سحر نوری; محمدرضا سلیمی; مجتبی شیدا; سیدامیر حسینی

Volume 6, Issue 3 , October 2013

Abstract
  When a solver is used for analyzing the hypersonic reentry vehicles, high speed and accuracy of the solver results are the basic parameters in the design process. In the present study, the results obtained by solution of laminar boundary layer equations using integral matrix method and approximate method ...  Read More