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RS-Satellites propulsion subsystem performance sizing via design plane technique, a generic method
, Article IEEE Aerospace and Electronic Systems Magazine ; Volume 36, Issue 2 , 2021 , Pages 56-70 ; 08858985 (ISSN) ; Kosari, A ; Malaek, S. M. B ; Khoshsima, M ; Sharif University of Technology
Institute of Electrical and Electronics Engineers Inc
2021
Abstract
Remote sensing satellites propulsion subsystem preliminary design based on performance sizing is discussed. The process is a fairly complicated one considering a variety of operational as well as performance requirements. This research aims to reduce the number of iterations required by the current practice to reach a compromise. It is based on a rapid-sizing method that helps lessen lengthy iteration cycles. The proposed technique, similar to such class of preliminary design processes, leads to an acceptable approximation that must be properly conveyed to other disciplines involved for further elaborations. With proper selection of design and performance parameters together with fundamental...
RS-Satellites propulsion subsystem performance sizing via design plane technique, a generic method
, Article IEEE Aerospace and Electronic Systems Magazine ; Volume 36, Issue 2 , 2021 , Pages 56-70 ; 08858985 (ISSN) ; Kosari, A ; Malaek, S. M. B ; Khoshsima, M ; Sharif University of Technology
Institute of Electrical and Electronics Engineers Inc
2021
Abstract
Remote sensing satellites propulsion subsystem preliminary design based on performance sizing is discussed. The process is a fairly complicated one considering a variety of operational as well as performance requirements. This research aims to reduce the number of iterations required by the current practice to reach a compromise. It is based on a rapid-sizing method that helps lessen lengthy iteration cycles. The proposed technique, similar to such class of preliminary design processes, leads to an acceptable approximation that must be properly conveyed to other disciplines involved for further elaborations. With proper selection of design and performance parameters together with fundamental...
Optimal decision making for orbit transfer system of a student micro-satellite, using multi-criteria decision making
, Article 1st IEEE International Symposium on Systems Engineering, ISSE 2015 - Proceedings, 28 September 2015 through 30 September 2015 ; 2015 , Pages 29-33 ; 9781479919208 (ISBN) ; Mahrooz, M. H ; Rahmani, S ; IEEE Systems Council ; Sharif University of Technology
Institute of Electrical and Electronics Engineers Inc
2015
Abstract
One of the most important aspects of a successful space mission is the transition to the correct orbit and maintaining it. As a result, many modern orbit transfer techniques have been developed in space industry in order to accomplish this task in a more reliable and less expensive way. However, when it comes to the design of student satellites, usually there are serious limitations on the financial resources, technical database and satellite industry experts. These limitations may compromise the access to advanced methods and techniques. Therefore, reliability and expenses may no longer be the only criteria to be met in the process of design. As a result, at each step of the design, a...
Investigating optimum procedures needed to maintain a model satellite's CG stable about design point, under subsystem configuration changes
, Article ASME 2010 10th Biennial Conference on Engineering Systems Design and Analysis, ESDA2010, 12 July 2010 through 14 July 2010, Istanbul ; Volume 4 , 2010 , Pages 585-588 ; 9780791849187 (ISBN) ; Abedian, A ; Teimouri, H ; Sharif University of Technology
2010
Abstract
During design, microsatellites are subject to different changes like the changes in weight, location and dimension of parts and elements of subsystems and the payload. These changes should be accumulated by the structure subsystem in a way that some key structural parameters like the center of gravity (CG) and inertia moments remain unchanged. This subject is also important regarding the design of a modular structure of a satellite. In the present study it is tried to accommodate any changes in weight and location of any part(s) and element(s) of a microsatellite by optimum (minimum) rearrangement of other parts on their plane of rest in order to keep the CG and inertia moments unchanged....