Space subsystems design: (navigation, control, structure and…)
Design and Implementation of a Balance System for the CubeSat Attitude Determination and Control Tabletop Simulator

Mahdi Rivandi; Mehran Mirshams; Mohammad Zarourati

Volume 16, Issue 1 , March 2023, , Pages 75-88

Abstract
  To test the Attitude Determination and Control Subsystem of a satellite, it is necessary to have an attitude dynamics simulator, and the simulator must be in a balance condition. Disturbances on the balance system in the simulation include deviations caused by the difference between the center of mass ...  Read More

GPS and navigation GPS)، GLONASS، GALILEO
Inertial navigation position error estimation, using vision system

Mohsen Shamirzaei; Mehran Mir Shams

Volume 14, Issue 3 , September 2021, , Pages 75-90

Abstract
  The main task of the study is to estimate the position error in an inertial navigation system by integrating it with the visual system. The case study is a spacecraft that must accurately measure its position relative to a predetermined landing point. The spacecraft is assumed to be augmented GNSS navigation. ...  Read More

Space subsystems design: (navigation, control, structure and…)
Development of MIL and PIL testbed for Student Microsatellite Attitude Control Subsystem

Niki Sajjad; Mehran Mirshams; Shahrokh Jaliian

Volume 13, Issue 3 , September 2020, , Pages 51-62

Abstract
  This paper presents design, analysis and performance verification test of student microsatellite Attitude Determination and Control Subsystem (ADCS) . ADCS design and implementation procedure contains several various steps. There are four main test levels during simulation called “Model-in-the-Loop”, ...  Read More

Modeling the Solar Array Design of Remote Sensing Satellites Based on Adaptive Neuro-Fuzzy Inference System

mehran mirshams; Mohammad Teshneh lab; Morteza Ramezani

Volume 11, Issue 3 , December 2018, , Pages 1-8

Abstract
  Modeling and analyzing systems, especially in complex systems with high dynamics, noise and uncertainty in understanding the behavior of systems and decision making is very important problem from long time ago. This paper shows that neuro-fuzzy systems can be used effectively to design the solar arrays ...  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

GEO Communication Satellite Engineering Design Code

Zeynab Aghajani; Ehsan Zabihian; Mehran Mirshams

Volume 10, Issue 4 , March 2018, , Pages 41-54

Abstract
  The significance and the wide use of geostationary communication satellites and the long hours of work in the process of their conceptual design was the main motivation to develop a software based on the statistical design to reduce the time spent on the conceptual design phase. This software is based ...  Read More

A Software for Establishing Technical Specifications of GEO Communication Satellites

Mehran Mirshams; Ehsan Zabihian

Volume 10, Issue 3 , December 2017, , Pages 1-14

Abstract
  This study introduces a new computer code termed AZMIN developed by Space Research Laboratory (SRL). This efficient tool which benefits from the Statistical Design Model (SDM) has been developed for the system design of GEO communication satellites. The main advantage of the AZMIN is to determine technical ...  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

Optimal Control of a Tri-axial Spacecraft Simulator Test bed Actuated by Reaction Wheels

Hojat Taei; M. Mirshams; M. Ghobadi; M. A. Vahid D.; H. Haghi

Volume 8, Issue 4 , January 2016, , Pages 35-44

Abstract
  This article describes the details of a Tri-axial Spacecraft Simulator Testbed (TSST) that has been developed as part of a research program on spacecraft multi-body rotational dynamics and control in Space Research Laboratory (SRL) at K. N. Toosi University of Technology. This dumbbell style simulator ...  Read More

Complementary Method the Conceptual Design of Space Craft Electrical Power  Subsystem

Mehrn Mirshams; Asad Saghari; Ehsan Zabihian

Volume 8, Issue 3 , October 2015, , Pages 55-63

Abstract
  This paper proposes a supplementary method for conceptual design of satellite electrical power subsystem(EPS). Each of represented methods for satellite electricalpower subsystemconceptual design in different references have some advantages and also disadvantages, besides in each of the methods a determined ...  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, , Pages 9-21

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

Comprehensive Code of Remote Sensing Satellite Conceptual Design

A. Saghari; M. Mirshams; A. Jafarsalehi

Volume 7, Issue 2 , July 2014, , Pages 35-47

Abstract
  In this article the results of research to achieve a comprehensive code of remote sensing satellite conceptual design is presented. In compiling the code with considering the design philosophy of "better, faster, cheaper" has been attempted in caddition to the use of new technologies and the experiences ...  Read More

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

M. Mirshams; S. Irani; A. M. Akhlaghi; H. Naseh

Volume 5, Issue 2 , July 2012, , Pages 49-57

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

Conceptual Design Algorithm of Dousti Manned Spacecraft

M. Mirshams; L. Khalaj-Zade

Volume 4, Issue 2 , January 2012, , Pages 11-22

Abstract
  To design a manned spacecraft carrying one to two crews to the low Earth orbits, design phases should be completed in various levels. It also needs to gather manned spacecrafts technical data which is developed in the same category. In the system design algorithm presented in this paper, the conceptual ...  Read More

Drivation of System Level Characteristics of a Manned Spacecraft by Applying Statistics Models

M. Mirshams; L. Khaladjzadeh

Volume 3, Issue 1 , July 2010, , Pages 25-36

Abstract
  Designing a manned spacecraft carrying one or two persons to low Earth orbits needs to recognize system level requirements and acquire technical data developed in this eria. Revising manned spacecrafts’ characteristics leads to recognize system level requirements and achieve applicable results ...  Read More

Constrained Optimization of Launch Vehicle Trajectory Using Spline and Bezier Curves

A. Tavakoli; M. Nikusokhan; J. Roshanian; M. Mirshams

Volume 2, Issue 2 , July 2009, , Pages 51-60

Abstract
  Design of launch vehicle (LV) trajectory is among the problems in which the use of optimization is of high significance. Implementing optimization using optimal control problem leads to a two point boundary value problem (TPBVS) that can be solved only numerically. On the other hand, development of optimal ...  Read More

Design and Manufacturing Steps of a Satellite Reaction Wheel

S.H. Miri Roknabadi; M. Mirshams; A. A. Nikkhah

Volume 2, Issue 2 , July 2009, , Pages 61-68

Abstract
  This paper presents a technical note of mathematic model, design and manufacturing steps of a Reaction Wheel, one of the most important active actuators of satellite. After that Reaction Wheels are tested for the satellite simulator of K.N.Toosi University of Technology, Iran. There were some requirements ...  Read More

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

M. Mirshams; H. Karimi; H. Naseh

Volume 1, Issue 2 , December 2008, , Pages 17-25

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

Multi-Stage Liquid Propellant Launch Vehicle Conceptual Design, Based on Combinatorial Optimization of Major Design Parameters

M. Mirshams; H. Karimi; H. Naseh

Volume 1, Issue 1 , September 2008, , Pages 21-36

Abstract
  The principle goal of this paper is developing of Launch Vehicle Conceptual Design (LVCD) method based on combinational optimization of major design parameters. To this end, ten sub-algorithms will be presented in this design approach. Mass distribution of different stages to launch maximum payload mass ...  Read More