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 New Technologies
System Design and Simulation of Air-spacecraft Aerospike Nozzle by Utilizing the Computational Fluid Dynamics (CFD) Method

Hassan Naseh; Ali Alipoor

Articles in Press, Accepted Manuscript, Available Online from 29 June 2021

https://doi.org/10.30699/jsst.2021.276758.1338

Abstract
  The main purpose is to introduce the performance system design and optimization method of aerospike nozzle for different aero-space conditions. For this purpose, some of the important parameters of the aerospike nozzle structure and cold flow condition tests in the nozzle optimization are studied. The ...  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

Space New Technologies
Cost Estimation for Space Propulsion Systems and Human Resource Cost and The Project Implementation Time optimization

Hassan Naseh; mostafa jafarpanah

Articles in Press, Accepted Manuscript, Available Online from 25 January 2022

https://doi.org/10.30699/jsst.2022.248628.1302

Abstract
  The purpose of this paper is to present the cost estimation and optimization of space propulsion systems. Thus, choosing optimal propulsion system (from fuel and oxidizer aspect) is done in order to increase the efficiency and decrease the cost. Also, human resource cost and technology development time ...  Read More

Space systems design (spacecraft, satellites, space stations and their equipment)
Cost Estimation Model Presentation for Cryogenic/Semi-Crogenic Space Propulsion Systems

Mostafa Jafarpanah; Hassan Naseh

Volume 14, Issue 4 , January 2022, , Pages 25-33

https://doi.org/10.22034/jsst.2021.1268

Abstract
  The purpose of this paper is to present the cost estimation model for Cryogenic/Semi-Crogenic space propulsion systems. Therefore, the space propulsion system selection from fuel and oxidizer type aspect and achieving the maximum performance and minimum cost has been performed. Then, the fuel and oxidizer ...  Read More

Space systems design (spacecraft, satellites, space stations and their equipment)
Sensitivity analysis based on Progressive LHS Applied to Hydrazine Catalyst Bed Design

Mohammad Naddafi Pour Meibody; Hassan Naseh; Fathollah Ommi

Volume 12, Issue 4 , February 2020, , Pages 35-46

https://doi.org/10.30699/jsst.2020.1143

Abstract
  Now, the required samples to achieve the specific precision of sensitivity analysis in design are performed based on trial and error methods. The purpose of this paper is to develop an approach for determining the number of the required sample to achieve the specific precision of sensitivity analysis. ...  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

Optimal Mission Design for Moon Exploration Expedition

Hassan Naseh; Mehran Mirshams; Elyas Fadakar; Mehdi Jafari Nadoushan

Volume 11, Issue 2 , September 2018, , Pages 47-53

Abstract
  The main goal of this paper is to introduce the Moon exploration mission design based on existing technology.The Moon exploration mission design entailsoptimal maneuvering orbit, payload and launch vehicle design. Optimal maneuvering orbit is designed with respect to Circular Restricted Three Body Problem ...  Read More

Launch Vehicle Classical Design Software with Training Approach in Higher Education

Hasan Naseh; Mehran Mirshams; Javad Naderifar

Volume 9, Issue 3 , December 2016, , Pages 73-79

Abstract
  The main goal of this paper is development of multi-stage Launch Vehicle (LV) system design software based on advanced classical method. This software has been named Launch Vehicle Conceptual Classical Design (LVCCD). This software covers the complete syllabuses of LV System Design (LVSD) course. The ...  Read More

Comprehensive Pattern in Designing Low-Thrust Space Propulsion Systems

H. Fazeli; H. Naseh; M. Mirshams; A.B. Novinzadeh

Volume 7, Issue 3 , October 2014

Abstract
  Designing space propulsion systems as one of the important subsystems of the spacecrafts and upper stage space launch systems needs to bypass different and complicated steps. In this article the comprehensive process of designing liquid fuel low-thrust space propulsion systems was illustrated. In the ...  Read More

Reliability Allocation to Launch Vehicle Subsystems by Using AHP Method in Conceptual Design Phase

مهران میرشمس; سعید ایرانی; امیرمهدی اخلاقی; حسن ناصح

Volume 5, Issue 2 , July 2012

Abstract
  The goal of this paper is presenting a methodology for reliability allocation to launch vehicle subsystems using Analytical Hierarchy Process (AHP) method in conceptual design phase. In this methodology, the goal function is reliability and the main considered criterions are technology, complexity, operational ...  Read More

Multi-Stage Liquid Propellant Launch Vehicle Conceptual Design (LVCD) Software, Based on Multi-Parameter Optimization Idea

مهران میرشمس; حسن کریمی; حسن ناصح

Volume 1, Issue 2 , July 2008

Abstract
  The principle goal of this paper is to introduce Launch Vehicle Conceptual Design (LVCD) software based on multi-parameter optimization idea. The main objectives of this software arereduction of the cost and time of conceptual design phase. This software is user friendly such that an operator familiar ...  Read More