Zobrazeno 1 - 10
of 218
pro vyhledávání: '"M. Mirshams"'
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 8, Iss 4, Pp 35-44 (2016)
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 Uni
Externí odkaz:
https://doaj.org/article/0f3b431be2204750bdb0fa50128a2b8e
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 7, Iss 3, Pp 9-21 (2014)
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-thru
Externí odkaz:
https://doaj.org/article/b292edb0623748d59522f7df02cef3a1
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 7, Iss 2, Pp 35-47 (2014)
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 caddit
Externí odkaz:
https://doaj.org/article/daa6bd85c94f43d59e94466fde85374d
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 7, Iss 1, Pp 1-12 (2014)
This paper focuses upon the development of an efficient method for conceptual design optimization of a satellite. There are many option for a satellite subsystems that could be choice, as acceptable solution to implement of a space system mission. Ev
Externí odkaz:
https://doaj.org/article/576c0e4d76494b5d9dd32566aaf36116
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 5, Iss 2, Pp 49-57 (2012)
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
Externí odkaz:
https://doaj.org/article/4074f0d680c64fb09c5f8babc1b1d935
Autor:
M. Mirshams, L.. Khalaj-Zade
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 4, Iss 2, Pp 11-22 (2012)
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 des
Externí odkaz:
https://doaj.org/article/55eacda8af5a4a5096c6a1d680a957e2
Autor:
M. Mirshams, L. Khaladjzadeh
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 3, Iss 1, Pp 25-36 (2010)
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 lev
Externí odkaz:
https://doaj.org/article/9b2769f4da144243b81dcb1ed1c9f57f
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 2, Iss 2, Pp 51-60 (2010)
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 on
Externí odkaz:
https://doaj.org/article/be1d62ce95d84b65a24cd384dc80265d
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 2, Iss 2, Pp 61-68 (2010)
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 Univ
Externí odkaz:
https://doaj.org/article/3ec1af67cb254ae1a171bd57dc52c1f2
Publikováno v:
فصلنامه علوم و فناوری فضایی, Vol 2, Iss 3, Pp 35-42 (2010)
This paper presents an optimal attitude maneuver by means of Reaction Wheels to achieve desired attitude for a Satellite. At first, Dynamic Equations of motion for a satellite with three Reaction Wheels as its active actuators has been educed, and th
Externí odkaz:
https://doaj.org/article/ac500aa690e44e54ae0e31ada6f38cac