Space systems design (spacecraft, satellites, space stations and their equipment)
Hojat Taei; Mahmood Haghighat Esfahani; Sajjad Yadegari Dehkordi
Volume 14, Issue 3 , September 2021, , Pages 39-50
Abstract
In this paper, a novel Comprehensive Preference-based Design (CPD) approach is presented which attempts to achieve subjective attributes that are defined in the concept of maximization of designer/customer's satisfaction in addition to objective goals which are formulated in the form of minimization ...
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In this paper, a novel Comprehensive Preference-based Design (CPD) approach is presented which attempts to achieve subjective attributes that are defined in the concept of maximization of designer/customer's satisfaction in addition to objective goals which are formulated in the form of minimization of a performance criterion in a two-phase structure using two nested optimizers.In the first phase of CPD,using the concept of satisfaction,the subjective preferences of the designer/customer are defined in terms of fuzzy relationships and operators.Whereas the results of this phase are inaccurate,in the second phase,it is attempted to define a performance criterion and in order to achieve an optimal operational plan,attitude parameters and the compromises needed to meet the designer/customer's preferences are implemented.The methodology is utilized to design of a space launch vehicle for delivering 1200 kg payload to a 750 km orbit.Comparison of the results shows that despite the higher mass of launch vehicle designed by CPD,overall design satisfaction is higher and designer/customer's preferences have been satisfied.
Space systems design (spacecraft, satellites, space stations and their equipment)
Abbas Saeidi; Nasser Rahbar; Mohammad Ali Alirezapouri
Volume 14, Issue 3 , September 2021, , Pages 65-73
Abstract
In recent years, according to progress of aerospace industries particularly satellites it has been paying much attention to attitude determination of satellite. Attitude determination of satellite in various ways, such as: radio, radar, optical methods and using GPS, q and kalman filter is done, that ...
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In recent years, according to progress of aerospace industries particularly satellites it has been paying much attention to attitude determination of satellite. Attitude determination of satellite in various ways, such as: radio, radar, optical methods and using GPS, q and kalman filter is done, that each of these methods has advantages and disadvantages. Due to disturbance in space, high accuracy in attitude determination, various algorithms to obtain properly accurately attitude, desirable access to position, velocity and time of satellite to achieve desired attitude determination satellite are considered a top priority. However in this Paper, first we review the various methods for attitude determination satellite and then examine of operation and relations of algorithms discussed. This Paper focus on the advantages and disadvantages of qEKF algorithm in compare to other methods are available.
Space systems design (spacecraft, satellites, space stations and their equipment)
Mohammad Razmjooei; Mohammad Shahbazi; Fathollah Ommi
Volume 14, Issue 2 , June 2021, , Pages 1-26
Abstract
In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating ...
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In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating conditions and compare the performance of these insulators. The heat and mass transfer equations are considered in two dimensions in a solid body. We used the equations, finite volume method with implicit formulation for time dependency to solve equations. The reaction equation which written in the form of Arrhenius, is solved using Runge-Kutta method, and the density and the flux of the gas produced at each step are obtained. Also we represent a model for the rate of recession.
Space systems design (spacecraft, satellites, space stations and their equipment)
Masoud EidiAttarZade; Atiyeh SarAbadani; Ghazal Davarnia; Hamed Khosrobeygi; Mohammad Farshchi; Alireza Ramezani
Volume 14, Issue 2 , June 2021, , Pages 47-37
Abstract
Numerical modeling of space engines aside the experimental test is routine. In the design step of such engines, low-cost softwares are vital. In this paper, small-scale space engine thrust chamber analysis code will be developed. In this code, propellant injection and evaporation distribution will be ...
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Numerical modeling of space engines aside the experimental test is routine. In the design step of such engines, low-cost softwares are vital. In this paper, small-scale space engine thrust chamber analysis code will be developed. In this code, propellant injection and evaporation distribution will be modelled. 1D Combustion solver calculates the reactions of distributed fuel and oxidizer through the thrust chamber axis by chemical mechanisms. Then the cooling solver computes the heat transfer from hot gases to the film cooling layer and the outer surroundings. Validation shows acceptable errors in the modelling of processes. By this developed code, the performance of the Astrium bi-propellant thruster with MonoMethylHydrazine and NitrogenTetrOxide and distributed chemical reaction has been investigated. Results show that hot gas temperature inside the combustor is not uniform and has a peak. Furthermore, the evaporation of the propellant droplets is continued to the nozzle throat.
Space systems design (spacecraft, satellites, space stations and their equipment)
Mahmoud Talafi Noghani; Peiman Aliparast
Volume 14, Issue 1 , March 2021, , Pages 35-41
Abstract
In this paper, a shielding box is designed for a Ku-band VSAT transmitter power amplifier based on an electromagnetic band gap structure. The proposed structure, is a bed of nails on the inner surface of the top wall of the box. It suppresses cavity resonances in the Ku-band uplink frequency range of ...
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In this paper, a shielding box is designed for a Ku-band VSAT transmitter power amplifier based on an electromagnetic band gap structure. The proposed structure, is a bed of nails on the inner surface of the top wall of the box. It suppresses cavity resonances in the Ku-band uplink frequency range of 14-14.5 GHz. The amplifier which is composed of two cascaded modules (a pre-amplifier and a 50 W power amplifier) is first imported to a full wave simulation software. Full wave simulation of the printed circuit board (PCB) which includes the small signal scattering parameters of the power amplifier modules, proves the optimum performance of the proposed design.
Space systems design (spacecraft, satellites, space stations and their equipment)
Mostafa Zakeri; Mehran Nosratollahi; MohammadReza Sabeti; Hamid Reza Moghadas Najaf Abad; Hamid Maleki
Volume 14, Issue 1 , March 2021, , Pages 43-54
Abstract
This research presents a new and effective approach to managing change control in the design process of complex engineering products. This approach involves using design constraints to combine two DSM matrix structures and a systematic process for controlling changes. The system process involves using ...
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This research presents a new and effective approach to managing change control in the design process of complex engineering products. This approach involves using design constraints to combine two DSM matrix structures and a systematic process for controlling changes. The system process involves using a systemic code to evaluate changes, how to create a transfer model, and a management change assessment request. The process presented in this article, in addition to using similar activities in this field, has provided a systematic approach to using the knowledge of designers of a project to guide the control of changes to major engineering projects, including decision-making on controlling changes and how to identify the best The path to the change control process
Space systems design (spacecraft, satellites, space stations and their equipment)
Mona Habibi; Mahdi Fakoor; Hadi Parviz Nowruzani
Volume 14, Issue 1 , March 2021, , Pages 65-75
Abstract
In this research, to investigate the effects of uncertainties on the natural frequency of satellite system attributed to the variation of layout components, the optimal layout of the satellite is performed utilizing particle swarm optimization (PSO) algorithm, considering stability and geometrical constraints. ...
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In this research, to investigate the effects of uncertainties on the natural frequency of satellite system attributed to the variation of layout components, the optimal layout of the satellite is performed utilizing particle swarm optimization (PSO) algorithm, considering stability and geometrical constraints. In order to produce random samples, enough number of results will be extracted, which are mass center of components, and based on the outputs, the finite element modeling of different samples by considering mass point is carried out. After modal analysis, mass and stiffness matrices are extracted, the simulation of Monte - Carlo runs based on Wishart random matrix theory and the eigenvalues of the matrix, i.e. natural frequencies, are obtained. Probabilistic distribution of natural frequencies is shown that in the proposed layout, the distribution of samples is very low and the variation of natural frequency is robust to the proposed optimal location.
Space systems design (spacecraft, satellites, space stations and their equipment)
Alireza Mohammadi; Fathollah Ommi
Volume 13, Issue 4 , December 2020, , Pages 15-23
Abstract
This paper presents numerical study on spray characteristics and droplet distribution by using Lagrangian method in the discrete phase model of CFD. A two-fluid Eulerian method and Lagrangian approach is selected for modeling two phases turbulence flow in mixing chamber and atomization at outlet of nozzle ...
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This paper presents numerical study on spray characteristics and droplet distribution by using Lagrangian method in the discrete phase model of CFD. A two-fluid Eulerian method and Lagrangian approach is selected for modeling two phases turbulence flow in mixing chamber and atomization at outlet of nozzle while turbulence has been modeled by K-ɛ. In this study, water has been used instead of fuel and Nitrogen instead of atomization gas or oxidizer, while their ratio has been considered 0.32 to provide 26 degrees cone angle and this way, droplet‘s characteristic has been studied and compared with maximum entropy methods. Then droplet‘s diameter has been investigated by changing liquid and gas phase flow rateand based on that, we can optimize atomizer ‘s working condition with maximum efficiency with respect to its cone angle, droplet ‘s diameter and velocity and level of penetration by minimum need of experimental tests.
Space systems design (spacecraft, satellites, space stations and their equipment)
Hamidreza Soleimani; Milad َAzimi
Volume 13, Issue 4 , December 2020, , Pages 37-48
Abstract
This paper analyses the dynamic behavior of the rigid solar panels deploying mechanism of a spacecraft with flexible hinges. The proposed mechanism, maintaining a proper speed, guarantees the deployment synchronization of solar panels and minimizes the effects of impact and vibration applied during the ...
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This paper analyses the dynamic behavior of the rigid solar panels deploying mechanism of a spacecraft with flexible hinges. The proposed mechanism, maintaining a proper speed, guarantees the deployment synchronization of solar panels and minimizes the effects of impact and vibration applied during the final stage and after the panels lock-up using torsional springs in the hinges and yoke driven assembly. The equations of the motion of the system are derived using Lagrangian approach and the behavior of the mechanism for constant and variable torque excitation modes is investigated. The simulation results presented along with the dynamic simulations performed by Adams software and conventional mechanisms show the efficiency of the proposed method.
Space systems design (spacecraft, satellites, space stations and their equipment)
Mehran Nosratollahi; Mohammad Fatehi Fatehi; Amirhossain Adami
Volume 13, Issue 3 , September 2020, , Pages 1-16
Abstract
Orbital transfer blocks has the task of transferring satellites to objective orbits from parking orbit. In this paper, Attention will be given to multidisciplinary optimal design of the propulsion system of two liquid component which is one of the most important subsystems of Orbital transfer blocks. ...
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Orbital transfer blocks has the task of transferring satellites to objective orbits from parking orbit. In this paper, Attention will be given to multidisciplinary optimal design of the propulsion system of two liquid component which is one of the most important subsystems of Orbital transfer blocks. Designing with multi objective bipropellant system, based on minimum total mass and maximum Isp, and at the end mentioned to costs and compared. For combinations of NTO as Oxidizer and fuels which are: UDMH, MMH, Hydrazine and RP-1 then for usual structures that utilized in this systems, design and optimization occurred by multi objective hybrid Particle Swarm Optimization (PSO) algorithms.
Space systems design (spacecraft, satellites, space stations and their equipment)
Peyman Aliparast
Volume 13, Issue 3 , September 2020, , Pages 17-24
Abstract
in this paper, design, implementation and test of 24 bit acoustic DAQ subsystem for bio-capsule of Pajohesh explorer is presented. the proposed structure has been used B&K 4942 microphone as input sensing element. the proposed DAQ, has 48Ksps speed, 24 bit resolution, 113dB dynamic range and 23 KHz ...
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in this paper, design, implementation and test of 24 bit acoustic DAQ subsystem for bio-capsule of Pajohesh explorer is presented. the proposed structure has been used B&K 4942 microphone as input sensing element. the proposed DAQ, has 48Ksps speed, 24 bit resolution, 113dB dynamic range and 23 KHz BW. we used a ARM Cortex M3 for signal handling and processing. the acquiescing data have been sending to Bio- capsule FC and also recorded in a Micro-SD card. power consumption of the proposed DAQ is obtained 2.8W. the proposed DAQ take a place with dimentions of 40*40*100 mm3 inside of bio-capsule stand.
Space systems design (spacecraft, satellites, space stations and their equipment)
Ghasem Heydari; Maryam Kiani; S. Hossein Pourtakdost; Mohammad Sayanjali
Volume 13, Issue 3 , September 2020, , Pages 25-38
Abstract
Halo orbits are of importance for observation and study of the space due to their specific characteristics including the orbital position and the periodic motion. In this regards, present paper has focused on optimal trajectory planning to transfer to halo orbits. To this aim, homotopy approach has been ...
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Halo orbits are of importance for observation and study of the space due to their specific characteristics including the orbital position and the periodic motion. In this regards, present paper has focused on optimal trajectory planning to transfer to halo orbits. To this aim, homotopy approach has been adopted for optimal trajectory design. This approach has improved the convergence rate and insensitivity of the problem to initial guess. The designed trajectory transfers a spacecraft orbiting the Earth to a Halo orbit around Lagrangian point L1 of the Earth-moon restricted three-body system. The propulsion system has been assumed to be low thrust with constant specific impulse. Homotopy approach has a broad domain of applicability and methods in which continuation method has been employed here among them. The optimal designed trajectory minimizes the fuel consumption via transforming solution of the minimum energy problem utilizing the homotopy approach. This approach simplifies solution of the complex problem of minimum fuel indeed.
Space systems design (spacecraft, satellites, space stations and their equipment)
mohammad razmjooei; mohammad shahbazi; Fathollah Ommi
Volume 13, Issue 2 , June 2020, , Pages 13-35
Abstract
In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating ...
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In this paper, the heat transfer and ablation thermal insulators in solid rocket motor are investigated. Therefore, by collecting and solving the thermal ablation equations, a computer program, using MATLAB software, is developed which can predict the thermal response of insulators in different operating conditions and compare the performance of these insulators. The heat and mass transfer equations are considered in two dimensions in a solid body. We used the equations, finite volume method with implicit formulation for time dependency to solve equations. The reaction equation which written in the form of Arrhenius, is solved using Runge-Kutta method, and the density and the flux of the gas produced at each step are obtained. Also we represent a model for the rate of recession.
Space systems design (spacecraft, satellites, space stations and their equipment)
Amirhossain Adami; Mehran Nosratollahi; Hanieh Eshagh nia; Sajjad Kheirkhah; Shiva Emami; Ali Saadat dar; Narges Afsari; Khashayar Mashhadi; Mansour Hozuri
Volume 13, Issue 2 , June 2020, , Pages 63-77
Abstract
The CANSAT design, a simple and small scale of a satellite, is an experience for preparing for the design of a Life cycle of the space project. In this paper, the process of design and construction of ARTA CanSat, which is participated in the scientific-exploratory class of international competition ...
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The CANSAT design, a simple and small scale of a satellite, is an experience for preparing for the design of a Life cycle of the space project. In this paper, the process of design and construction of ARTA CanSat, which is participated in the scientific-exploratory class of international competition in CANSAT Iran, has been written. The operation scenario is that an automatic scanner system, lands after releasing from 300 meters above ground level with using a recovery subsystem (parachute), which is controlled its downfall and landing position by the parachute controller system. During the descent, the data is transmitted by the sensors and sent to the ground station. After touchdown, the Hotwire system's operates and separates the parachute from the Rover section; Then CanSat with the moving on the ground by using the simpler section embedded underneath the structure, performing excavation while moving to the target point. Throughout the mission, the health of the biological payload is preserved.
Space systems design (spacecraft, satellites, space stations and their equipment)
Hojat Taei; Pourya Shokrolahi
Volume 13, Issue 2 , June 2020, , Pages 87-96
Abstract
The final phase of orbital rendezvous and docking has been studied in this article. The main objective is to control the position of a chaser that can reach the target in the minimum time, or in other words, bypassing the optimal path. Another important objective of this paper is the minimum energy consumption. ...
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The final phase of orbital rendezvous and docking has been studied in this article. The main objective is to control the position of a chaser that can reach the target in the minimum time, or in other words, bypassing the optimal path. Another important objective of this paper is the minimum energy consumption. In the dynamic simulation, the equations of the linear form of Clohessy-Wiltshire (CWH) equations have been utilized. In linear CWH equations, the change in either direction of X or Y will result in the change in another direction and will affect the orbital docking operation. In order to achieve the objectives of this paper, the design variables should be optimized; To optimize the design variables, two methods, i.e. genetic algorithm (GA) and particle swarm optimization (PSO), have been used. Finally, to evaluate the real conditions, the results will be investigated by applying uncertainty in the outputs of thrusters.
Space systems design (spacecraft, satellites, space stations and their equipment)
Alireza HeshmatiMoez; S. Hassan Sedighi; Mohamad Soleimani; Mohamad Khalaj AmirHoseini
Volume 13, Issue 2 , June 2020, , Pages 99-104
Abstract
This paper presents a new unit to design dual linearly polarized reflectarray antenna at ku for satellite telecommunication. Two orthogonal sets of parallel dipoles are used for each polarization to achieve more degree of freedom in the design and wider phase variation in the unit cells, consequently. ...
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This paper presents a new unit to design dual linearly polarized reflectarray antenna at ku for satellite telecommunication. Two orthogonal sets of parallel dipoles are used for each polarization to achieve more degree of freedom in the design and wider phase variation in the unit cells, consequently. A 0.3m Reflectarray Antenna with two distinct beams is fabricated and measured in an anechoic chamber. The measurements have been carried out for both polarizations (X and Y ) in the azimuth and elevation planes. This antenna has x-polarized beam at (θ0=30º, ϕ0=90º) with 23.7 dBi gain and y-polarized beam at (θ0=30º, ϕ0=0º) with 24.2 dBi gain at Ku-band. The proposed design has one layer and simple structure compared to the references as well as dual band and dual polarization capabilities.
Space systems design (spacecraft, satellites, space stations and their equipment)
Meghdad Payan; Hanif Kazerooni
Volume 13, Issue 1 , March 2020, , Pages 83-98
Abstract
The need to stay in space and use its advantage in different perspectives, has led our country to take steps to use satellite technology. In this regard, constructing an advanced satellite launch site with all the modern facilities is one of the key issues. Imam Khomeini Space Center is the first permanent ...
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The need to stay in space and use its advantage in different perspectives, has led our country to take steps to use satellite technology. In this regard, constructing an advanced satellite launch site with all the modern facilities is one of the key issues. Imam Khomeini Space Center is the first permanent launch platform of the Islamic Republic of Iran. In 1389, it was announced that due to existing geographic constraints, research was conducted to build the second space center in Chabahar. In this paper, using several performed studies on the infrastructure of the advanced space centers around the world as well as various simulation methods, a conceptual design for the Chabahar launch site is presented. Full descriptions of the launch platforms, processing complex, assembling of satellites, etc. are illustrated. The design and construction of the Chabahar launch site will be a major step forward in the development of the space industry of Islamic Republic of Iran.
Space systems design (spacecraft, satellites, space stations and their equipment)
Hamed Hashemi Mehneh; amirreza Ghedamini Harouni
Volume 12, Issue 4 , December 2019, , Pages 1-17
Abstract
The robust multi-disciplinary, multi-objective shape optimization of re-entry capsule with aero-thermodynamic, trajectory, stability and the geometry considerations are presented in this paper. In this research, the results of maximizing the volumetric efficiency of the capsules while minimizing the ...
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The robust multi-disciplinary, multi-objective shape optimization of re-entry capsule with aero-thermodynamic, trajectory, stability and the geometry considerations are presented in this paper. In this research, the results of maximizing the volumetric efficiency of the capsules while minimizing the ballistic coefficient and the longitudinal stability derivative with considering uncertainties are discussed in presence of some constraints on geometry, heating load, and load factor. To reduce the time and cost of robust optimization, the Adaptive Monte Carlo Simulation technique is used which decreases the number of required evaluations within the robust optimization process. Utilizing the constrained multi-objective genetic algorithm will result in a collection of robust optimal solutions. The results show that the performance of obtained robust optimal configurations is in a way that the considered constraints aren’t violated with 99.8% of confidence level even in the presence of uncertainties.
Space systems design (spacecraft, satellites, space stations and their equipment)
Vahid Bohlouri; Hossein Haghighi; Soheil Seyedzamani
Volume 12, Issue 4 , December 2019, , Pages 57-67
Abstract
In this paper, damping mode of a satellite attitude control is designed and implemented using magnetic actuators in software /hardware-in-the-loop testbed. To this end, the equivalent of Earth’s magnetic field is designed using Helmholtz coil, frictionless is made by air-bearing, and algorithms ...
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In this paper, damping mode of a satellite attitude control is designed and implemented using magnetic actuators in software /hardware-in-the-loop testbed. To this end, the equivalent of Earth’s magnetic field is designed using Helmholtz coil, frictionless is made by air-bearing, and algorithms are developed on designed control board. By measuring the Earth’s magnetic field, actuator commands are generated by the damping algorithm then braking torque is produced. Some applied restrictions and special requirements such as non-simultaneous operation between magnetic sensor and magnetic actuators, air-bearing friction, initial angular velocity are considered. By identifying the air-bearing frictional model, the results are compared in software/hardware-in-the-loop. The compared results show that the ability of the designed system to perform damping mode.
