Space systems design (spacecraft, satellites, space stations and their equipment)
Hanieh Eshaghnia; Mehran Nosratollahi; Amirhossain Adami
Volume 14, Issue 4 , December 2021, , Pages 35-49
Abstract
A new approach to the design and development of launchers is the use of advanced technologies to reduce design and development costs as much as possible. In this paper, an approach to reduce costs and increase reliability is proposed, which is based on the use of a non-turbo pump propulsion system (pressure-fed ...
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A new approach to the design and development of launchers is the use of advanced technologies to reduce design and development costs as much as possible. In this paper, an approach to reduce costs and increase reliability is proposed, which is based on the use of a non-turbo pump propulsion system (pressure-fed propulsion system) instead of a turbo pump propulsion system. For this purpose, the multidisciplinary conceptual design optimization of a two-stage launch vehicle with a pressure-fed propulsion system with the aim of sending max payload with a least gross mass to the orbit (500 km) in terms of structure, aerodynamics, propulsion, pressure vessels, simulation, and pitch program disciplines. Then, the sensitivity analysis was performed on the optimum launcher to determine the efficiency of the launcher at different orbital heights and the ability to carry a suitable payload.
Space systems design (spacecraft, satellites, space stations and their equipment)
Hojat Taei; Amirhossain Adami; Mansour Hozuri
Volume 14, Issue 4 , December 2021, , Pages 85-98
Abstract
The need to improve the reliability and safety requirements, has led to increasingly utilization of reliability based design approaches. In this study, reliability based multidisciplinary design optimization for a bipropellant propulsion system has been investigated. The objective function is minimizing ...
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The need to improve the reliability and safety requirements, has led to increasingly utilization of reliability based design approaches. In this study, reliability based multidisciplinary design optimization for a bipropellant propulsion system has been investigated. The objective function is minimizing the total system mass and design constraints are the total impulse and the temperature of the wall of the combustion chamber. Monte Carlo simulation methodology is used to apply uncertainties in the problem and to show the reliability of the system under these uncertainties. The mass, functional and geometric results of the bipropellant propulsion system are differentiated for optimal design, reliability based design and optimal reliability based design. Then, considering the results, the concepts and definitions of design methods are compared and discussed and it is shown that the reliability based multidisciplinary optimization while having the desired mass, has high reliability.
Amirhossain Adami; Hojat Taei; Mansour Hozuri
Volume 12, Issue 1 , April 2019, , Pages 41-53
Abstract
Considering the importance of the presence of uncertainties in the design of complex engineering systems, in this research multidisciplinary design optimization process for a bipropellant propulsion system in the presence of uncertainties, which in addition to minimizing the system mass, has a high robust. ...
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Considering the importance of the presence of uncertainties in the design of complex engineering systems, in this research multidisciplinary design optimization process for a bipropellant propulsion system in the presence of uncertainties, which in addition to minimizing the system mass, has a high robust. Based on this, the multidisciplinary design view of the bipropellant propulsion system is expressed in both optimum design and optimum robust design. The continued with the application of uncertainties, the mass, operational and geometric results of the propulsion system are expressed in terms of optimum design, robust design and optimum robust design. According to the results, it is shown that the lowest mass occurs in optimum design mode. But with uncertainties, it is observed at this point that it has the least robust and reliability. It also attempts to explain the difference between the concepts of robust design and optimum design with the help of results
Hojat Taei; Mansour Hozuri; Amirhossain Adami
Volume 10, Issue 2 , September 2017, , Pages 53-63
Abstract
The hydrazine propulsion system is one of the most widely used monopropellantpropulsion systems. This low-cost and low mass system is used for the attitude control ofsatellites due to its high specificity and rapid response.For this purpose, in the presentstudy, an optimal design of a hydrazine monopropellant ...
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The hydrazine propulsion system is one of the most widely used monopropellantpropulsion systems. This low-cost and low mass system is used for the attitude control ofsatellites due to its high specificity and rapid response.For this purpose, in the presentstudy, an optimal design of a hydrazine monopropellant propulsion system with the aim ofminimization of total mass and maximization of total impulse in the framework ofmultidisciplinary design optimization and sequential design method is considered. Inaddition, the principles of multidisciplinary and sequential design are described in thispaper. It has been tried to examine the impact of different elements on design goals andcompare the optimal value obtained in each of the design structures from differentaspects. It should be noted that the design process is accomplished in two ways, i.e.single-objective and multi-objective, and the optimal multidisciplinary design method iscompared with the sequential design method for the hydrazine monopropellant propulsionsystem.
Hossein Darabi; Jafar Roshanian
Volume 8, Issue 2 , July 2015, , Pages 27-39
Abstract
Collaborative optimization is one of bi-level multidisciplinary optimization methods which consists of system level and discipline level and is applied for complex engineering problems. since this method is rigidly convergent at discipline level because of noisy constraints at system level on one hand ...
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Collaborative optimization is one of bi-level multidisciplinary optimization methods which consists of system level and discipline level and is applied for complex engineering problems. since this method is rigidly convergent at discipline level because of noisy constraints at system level on one hand and minimizing objective function necessity at system level on the other hand, this optimizationmethod is forced to use evolutionary algorithms in order to minimize objective function at system level, also, It has been proved that, applying this algorithms according to their nature is expensive and time consuming. This paper with performed inspections is a new method for applying innovated optimization algorithms through which considerable results are obtained in solving sample problems. It is shown that using this method will decrease function calls number or problem solving time and therefore calculating costs will decrease considerably. Also it is shown that this method sometimes increase accuracy.
S. M. Hashemi Doulabi; H. Darabi; J. Roshnian
Volume 5, Issue 1 , April 2012, , Pages 61-72
Abstract
One of the most important problems that nowadays are common in aerospace societies in Iran and also around the world is how to optimize the designing of the flight objects. Since the flight objects like LVs, which are the subject of this paper, are composed of several subsystems that have influences ...
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One of the most important problems that nowadays are common in aerospace societies in Iran and also around the world is how to optimize the designing of the flight objects. Since the flight objects like LVs, which are the subject of this paper, are composed of several subsystems that have influences to each others, the multidisciplinary design optimization methods(MDO) are commonly used for doing design optimization of them. In usage of the multidisciplinary design optimization methods for different objects, to select the proper optimization algorithm is one of the very important problems. In this research the conceptual design of a lightweight liquid propellant LV is done with the all at once (AAO) method. The object of optimization is to minimize gross launch weight and four disciplines of structure, aerodynamics, trajectory, and propulsion are considered. Performance of gradient based algorithm of SQP and heuristic algorithm of GA and traditional method (statistical method) by solving an example are compared and is shown that if the output of statistical method is used as start point of optimization using gradient based algorithm of SQP, the global answer will be derived.
J. Roshanian; M. Ebrahimi; A. Bataleblu
Volume 4, Issue 2 , January 2012, , Pages 23-34
Abstract
The purpose of this paper is introducing the concept of nondeterministic optimal design or optimal design in the presence of uncertainty based on researches done in the past two decades. Therefore, after an introduction about uncertainty, the uncertainty and uncertainty modeling techniques are described. ...
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The purpose of this paper is introducing the concept of nondeterministic optimal design or optimal design in the presence of uncertainty based on researches done in the past two decades. Therefore, after an introduction about uncertainty, the uncertainty and uncertainty modeling techniques are described. After that, thetraditionalmethodof dealingwith uncertaintyin thedesignis described. The importance of paying attention to the uncertainty and its benefits for different projects and companies is described. The third section is dedicated to introducing the methods of interval analysis, fuzzy logic and probability analysis, which are used in the analysis of uncertainty.The two general categories of nondeterministic design problems, the robust optimal design and reliability-based optimal design are reviewed. The next section introduces the application of nondeterministic design methods in the different disciplines and recent researches in the world on this topic. Finally, future aspects and challenges of the nondeterministic design are addressed.
