Space subsystems design: (navigation, control, structure and…)
hamid reza ali mohamadi; Hassan Naseh
Articles in Press, Accepted Manuscript, Available Online from 25 September 2023
Abstract
Achieving to new technologies with high reliability, along with reducing the cost and time of the design cycle, is one of the most important challenges in complex systems. In this paper, reliability based design of a space system is discussed in the conceptual design phase. Normally, there are eight ...
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Achieving to new technologies with high reliability, along with reducing the cost and time of the design cycle, is one of the most important challenges in complex systems. In this paper, reliability based design of a space system is discussed in the conceptual design phase. Normally, there are eight steps in the design for reliability. The first step, planning, and the next seven steps that applied for the liquid propellant engine with electro-pump technology included: determination of failure modes; reliability modeling; reliability allocation; propagation of uncertainty; Implementation of the chosen method in reliability analysis; reliability prediction and reliability evaluation. Therefore, in this research has been performed to achieved method and implementation steps of reliability design in the conceptual design phase of a space system.
Space systems design (spacecraft, satellites, space stations and their equipment)
Amirhossain Adami; zahra pourJabari; Mohammad azhdari; Ali Saadat dar; Hanieh Eshaghnia; Kazem gholipour; seyedmohammad mirmohammadi; Alireza Ahangarani Farahani
Articles in Press, Accepted Manuscript, Available Online from 21 April 2024
Abstract
In this research, the structure of the probes sent to other planets is first investigated and the common structures are introduced. In the following, the system design process of the Armita probe, which was prepared for the first national competition of the probe robot (Iran Space Research Institute), ...
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In this research, the structure of the probes sent to other planets is first investigated and the common structures are introduced. In the following, the system design process of the Armita probe, which was prepared for the first national competition of the probe robot (Iran Space Research Institute), will be discussed. Armita team has won the first place in the first phase of the competition in 1401. The probe design process is based on the ECSS standard and is presented briefly, which includes the compilation and extraction of the requirements document, function-performance tree, product tree and finally the conceptual design of the sub-systems to achieve the intended mission. Based on the extracted results, the Armita probe with a mass of 6.9 kg and geometric dimensions of 48 x 38 x 36 cm with a total energy consumption of 112 amp hours will be able to perform the intended mission and satisfy all technical, dimensional and mass requirements well. shows
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 ...
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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 part of this subsystem has been in focused. In this research, first advantages and disadvantages of existing approaches for the conceptual design of electrical power subsystemwere reviewed, continued with combining of previous methods, improved relationships and using some of the simulation methods plus the using of statistical databases, a complementary method with more ascendency and less disadvantages in comparison with other approaches was presented. Finally, using a data from a specific satellite and the results of the statistical design, the complementary method has been validated.
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 ...
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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 presented pattern, first of all according to the requirements and mission constraints, the main characteristics of the system were determined and then other characteristics were extracted. Finally, for the evaluation of the presented pattern, a low-thrust space propulsion system was designed based on a special mission and the results were compared with a real model. Comparison between the designed space propulsion system and the real one showed an appropriate accuracy of the presented pattern
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 ...
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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 of experts, local constraints such as national launchers limitation also be considered.The main advantage of the proposed code than conventional models, is using accurate simulation methods and newer models in the process of conceptual design of subsystems. view of the practical experience of the past to choose the best design starting point, achieve an operational plan to reduce the risk of costly changes, next steps of design has been achieved.
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 ...
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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 design sequences of a manned spacecraft named Dousti is accomplished systematically.
First of all, in accordance with a target group of manned spacecrafts’ mission, Dousti’s mission profile is defined and system level requirements are recognized. User’s requirements are also considered in the mission profile and subsequently in system level requirements.
General characteristics of Dousti spacecraft as well as its mass and dimensional features are derived in the next step. Statistics and parametric models are systematically applied in design sequence. Then, final characteristics of the spacecraft’s main subsystems designed through engineering methods and applying parametric models are introduced.
Afterwards, resulting characteristics of the spacecraft are traded off to reform and then validated by statistics and parametric models to present the final plan.
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 ...
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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 to the orbit, pitch program trajectory to get to the maximum final velocity, and providing minimum velocity loss due to gravity, and also minimum axial acceleration of various stages of launch vehicle will be optimized as the results of the presented approach. The optimization process is performed subject to the restrictions. Also, the performance index is optimized in a mutual iteration mechanism. Evaluation and verification of the presented method is performed using available data of two and three-stage launch vehicles.
