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
Space subsystems design: (navigation, control, structure and…)
Alireza Ahangarani Farahani; Amirhossain Adami; Hamed Arefkhani
Volume 16, Issue 3 , September 2023, , Pages 79-89
Abstract
In this article, a new approach has been presented in the design of a satellite's status controller using reaction wheels. First, a non-linear controller whose gains depend on the state variables at any moment is proposed. In the first step, the process of extracting control coefficients using the GA ...
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In this article, a new approach has been presented in the design of a satellite's status controller using reaction wheels. First, a non-linear controller whose gains depend on the state variables at any moment is proposed. In the first step, the process of extracting control coefficients using the GA optimizer is described. Then, using the results of a number of tests, sufficient data for meta-modeling of the system is extracted and the relevant control gain functions are optimized using the data bank. The input of the mentioned function is the system states and its output is the control coefficients. Finally, a simulator platform was used to determine and control the position of the satellite based on the air bearing to evaluate the proposed approach. Laboratory test results show that the performance of the proposed method is up to 30% better than the classical PID controller with fixed coefficients.
Space systems design (spacecraft, satellites, space stations and their equipment)
Hanieh Eshaghnia; Mehran Nosratollahi; Amirhossain Adami; Hadi Dastoury
Volume 15, Issue 1 , March 2022, , Pages 121-137
Abstract
Turbopump propulsion systems have been used in almost all launch vehicles. With the advancement of manufacturing technologies, especially in the use of composite and lightweight structures, the use of non-turbopump propulsion systems has been considered due to the reduction of operating costs. This study ...
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Turbopump propulsion systems have been used in almost all launch vehicles. With the advancement of manufacturing technologies, especially in the use of composite and lightweight structures, the use of non-turbopump propulsion systems has been considered due to the reduction of operating costs. This study has been investigated the multi-disciplinary optimization design of a two-stage launch vehicle using a pressure-fed propulsion system for both stages. Two main propulsion systems including gas-pressure and self-pressure feeding systems, have been evaluated in different configurations on two launcher stages. To extracting the optimum and possible solution, the launcher mission also has been added as a design variable in the optimization algorithm. The launcher has been extracted and introduced for each specific configuration of the launcher to achieve a certain orbital altitude with the maximum carrying payload and minimum gross mass. For this purpose, the AAO multidisciplinary optimization design framework has been used. The system-level and subsystem optimizer of the GA-SQP algorithm have been chosen.
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.
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)
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.
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
erfan beygi; Amirhossain Adami
Volume 11, Issue 4 , December 2018, , Pages 43-50
Abstract
Basically, it takes alot of time to analyze structures with different parameters, depending on the type of structure and parameters. Also, by changing any parameter, all the analysis process must be repeated. Therefore analyze the effect of different parameters on the behavior of structures, many analyzes ...
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Basically, it takes alot of time to analyze structures with different parameters, depending on the type of structure and parameters. Also, by changing any parameter, all the analysis process must be repeated. Therefore analyze the effect of different parameters on the behavior of structures, many analyzes should be carried out that are time consuming. The results obtained are valid only for the same parameters, and are not valid by changing the parameters. In this research, a Nested dependence method has been developed that can be used to determine the behavior of the structure with proper accuracy with short time. In this method, first an interval is considered for different parameters of the structure. Then, by using the finite element analysis method and applying the loading and boundary conditions, the behavior of the structure. By repeating this process to extract the appropriate number of input data, a Nested dependence method can be used to estimate the structure behavior of different inputs.
atefeh hoseinzadeh; Amirhossain Adami; Asghar Ebrahimi
Volume 11, Issue 1 , June 2018, , Pages 1-12
Abstract
The atmospheric reentry phase is one of the most important mission steps in space missions, therefore, the guidance and control of reentry vehicles in this phase of mission is important. In this article, a reentry vehicle guidance algorithm is proposed which has suitable robustness in the presence of ...
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The atmospheric reentry phase is one of the most important mission steps in space missions, therefore, the guidance and control of reentry vehicles in this phase of mission is important. In this article, a reentry vehicle guidance algorithm is proposed which has suitable robustness in the presence of initial reentry parameters uncertainty. To use any conductive method, first the motion equations must be obtained. In this paper, quadratic nonlinear control method is used to guide the vehicle. In this regard, the equations of motion of reentry vehicles are developed in form of state space and the system and control matrices depending on the state and control variables are extracted. In this article, it is tried to minimize the landing errors at terminal point using Nonlinear Quadratic Tracking (NQT) and chasing a reference trajectory. In order to define a trajectory with different initial states using evolutionary genetic algorithm with changes in weighting matrices Q and R, it is tried to reduce the errors of landing at terminal point. Monte Carlo analysis is used to evaluate the performance of the proposed algorithm. According to the results, the proposed algorithm can reduce the errors more than 90% in the presence of reentry initial parameter uncertainties.
atefeh hoseinzadeh; Amirhossain Adami; Asghar Ebrahimi
Volume 10, Issue 4 , March 2018, , Pages 29-40
Abstract
The atmospheric re-entry phase is one of the most significantmission steps in the space missions;hence, theguidance and control of reentry vehicles in this phase of mission is important. In this article, a reentry vehicle guidance algorithm has been proposed which has suitable robustness in the presence ...
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The atmospheric re-entry phase is one of the most significantmission steps in the space missions;hence, theguidance and control of reentry vehicles in this phase of mission is important. In this article, a reentry vehicle guidance algorithm has been proposed which has suitable robustness in the presence of initial reentry parameters uncertainties. Here,it has been tried to minimize the landing errors at terminal point using Nonlinear Quadratic Tracking (NQT) and chasing a reference trajectory. In order to define several trajectories with different initial states using evolutionary genetic algorithm with changes in weighting matrices Q and R, it hasbeen tried to reduce the errors of landing at terminal point. The reentry position of the reentry vehicles may be different from the desired ones with respect to several events. In this situation, reentry vehicles start to move in a new trajectory which is not suitable. Therefore, the reentry vehicles should be guided to come back into the desired trajectory or a new optimum trajectory needs to be redesignedto have the same target position on the ground. To do this, we need optimum weighting matrices R and Q for every new trajectory. In this article, this problem has been resolved using partial least squares regression; meanwhile, obtaining the optimal matrices by genetic algorithms needed many times. Also,it is shown that using this method, in the presence of reentry uncertainties, weighting matrices for each new initial condition hasbeen quickly derived. Additionaly,through the matrices obtained and the nonlinear quadratic tracking controller, reentry vehicle was directedto the target with a good accuracy. The Monte Carlo analysis has been used to evaluate the performance of the proposed algoritm. According to the results, the proposed algoritm has a suitable accuracy level and it can generate the online optimum trajectory.
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.
MohammadReza Heidari; AmirHoseyn Adami
Volume 5, Issue 3 , October 2012, , Pages 67-80
Abstract
In this paper, specific grains burn back is presented by new geometrical method. The software is developed for Wagon wheel grains and 3D grains. Rapid solid motor ballistic simulation code produces required charts with considered nozzle geometry. Presented method used geometrical introducer point (GIP) ...
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In this paper, specific grains burn back is presented by new geometrical method. The software is developed for Wagon wheel grains and 3D grains. Rapid solid motor ballistic simulation code produces required charts with considered nozzle geometry. Presented method used geometrical introducer point (GIP) to produce the various grains. Limitations and configurations are simply modeled. Thrust, total pressure and temperature are illustrated as web burned changing. The results confirm the performance of the developed algorithm for mentioned grain analysis. Lower time processing and rapid ballistic analysis are the benefits of the presented algorithm. Finally results of the burn back analysis code and the internal ballistic simulation code are evaluated by some other existent codes and real cylindrical grain test.
A. H. Adami; M. Nosratollahi
Volume 4, Issue 2 , January 2012, , Pages 1-10
Abstract
New algorithm is presented in this paper for attitude determination of LEO nanosatellite with 2 accuracy in attitude determination independent of time. The most important limitation in nanosatellites is about subsystems’s masses so, reduction of subsystems’s masses is always considered. ...
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New algorithm is presented in this paper for attitude determination of LEO nanosatellite with 2 accuracy in attitude determination independent of time. The most important limitation in nanosatellites is about subsystems’s masses so, reduction of subsystems’s masses is always considered. ADS plays the important role in the successful orbital maneuver missions. ADS accuracy is connected with increasing of sensors and complex processors which lead to increase the ADS mass. The presented algorithm uses one magnetometer sensor and one horizon sensor and position data receiving by GPS sensor as minimum required sensors. The selected configuration is resulted to minimum ADS mass and mission cost. Finally, error analysis at two most important orbit zones is done and the performance of the presented algorithm is confirmed.
M. Nosratollahi; A. h. Adami-Dehkordi
Volume 3, Issue 2 , January 2011, , Pages 11-22
Abstract
This paper presents the multidisciplinary design optimization of monopropellant propulsion system of the nanosatellite for planner maneuver. Mass, configuration and internal ballistic equations are derived for any part of propulsion system (thruster, tank, pressurized gas, ...). Minimizing total mass ...
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This paper presents the multidisciplinary design optimization of monopropellant propulsion system of the nanosatellite for planner maneuver. Mass, configuration and internal ballistic equations are derived for any part of propulsion system (thruster, tank, pressurized gas, ...). Minimizing total mass of the propulsion system and satisfying all constrains such as Thrust limitation 5 (N) and 10 (N), Minimum specific impulse () and minimum throttle area (). AAO framework is developed and the direct search is selected for optimization method. Finally optimum designs are introduced and compared for 10(N) and 5(N) monopropellant propulsion system.
