ResearchPaper
Space systems design (spacecraft, satellites, space stations and their equipment)
Hossein Mahdavy-Moghaddam; Vahid Rahimi Goradel
Articles in Press, Corrected Proof, Available Online from 21 March 2023
Abstract
Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the ...
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Each missile has a payload section and an engine section. In the path of the missile, there is a time when the mission of the engine section is over and after that the engine will not play an effective role and will be as extra weight and consequently reduced range or factor for easy detection of the warhead by enemy agents. In such a situation, after completing the engine mission, the mechanism of separating the steps and separating the head from the body is used. One of the separation methods is to use the thrust termination system method. In this paper, with the studies performed on the thrust termination system and the presentation of mathematical relations, the pressure drop and inverse thrust created in the chamber after opening the reverse thrust valves are predicted. Also, cold type separation and thrust termination system were used and the combustion chamber pressure drop is simulated. Then, the effect of important and influential factors on the thrust termination system has been investigated.
ResearchPaper
Space subsystems design: (navigation, control, structure and…)
Milad َAzimi; Samad Moradi
Articles in Press, Corrected Proof, Available Online from 21 March 2023
Abstract
This paper deals with form-finding and free vibration analysis of a pre-stressed class-one triplex tensegrity structure. The form-finding is performed via a two-step procedure, the nodal coordinates connectivity matrix, and structural element force density determination. Accordingly, the possible states ...
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This paper deals with form-finding and free vibration analysis of a pre-stressed class-one triplex tensegrity structure. The form-finding is performed via a two-step procedure, the nodal coordinates connectivity matrix, and structural element force density determination. Accordingly, the possible states for the nodal coordinates and the structural force density of the triplex prism have been determined by trial and error (based on topology and member type knowledge) to satisfy the force density, and equilibrium matrices rank requirements. Based on different structural topologies, the equation of the motion in the frequency domain for free vibration analysis of the system is derived using the spectral element approach and dynamic shape functions. Simulations are provided for different system heights and the top-bottom aria ratios and compared with the FEM. The numerical simulations in the form of a comparative study of the natural frequencies of triplex tensegrity prism with different heights and cross-sections represent the system’s robustness with different topologies for single or multi-stage applications.
Technical Note
Space Science and Technology
Hadiseh Karimaei; Hadiseh Karimaei; Mohammad Reza Salimi; Hassan Naseh
Articles in Press, Accepted Manuscript, Available Online from 21 September 2021
Abstract
In this paper, the catalyst bed of a 10 N hydrazine monopropellant thruster was designed. The catalyst bed is including iridium granules, which is used to decompose the hydrazine in monopropellant thruster. Hydrazine must be decomposed almost completely in the catalytic chamber, because it is a carcinogenic ...
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In this paper, the catalyst bed of a 10 N hydrazine monopropellant thruster was designed. The catalyst bed is including iridium granules, which is used to decompose the hydrazine in monopropellant thruster. Hydrazine must be decomposed almost completely in the catalytic chamber, because it is a carcinogenic chemical fuel and on the other hand, achieving the maximum power from the thruster is also an important goal. As a result, the effect of change in catalytic chamber length on the mass fraction of chemical species including hydrazine, ammonia, nitrogen, and oxygen was studied. Also, after determining the length of the catalytic chamber, the diameter of the nozzle throat corresponding to the same length was determined.
ResearchPaper
Space subsystems design: (navigation, control, structure and…)
Ali Kasiri; Farhad Fanisaberi; Vahid Joudakian
Articles in Press, Accepted Manuscript, Available Online from 25 January 2022
Abstract
Many studies have investigated the problem of external disturbance rejection and also increasing the attitude control system's robustness against the parametric uncertainties. Due to stochastic properties, noise effect minimization becomes an interesting and challenging problem in the field of spacecraft ...
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Many studies have investigated the problem of external disturbance rejection and also increasing the attitude control system's robustness against the parametric uncertainties. Due to stochastic properties, noise effect minimization becomes an interesting and challenging problem in the field of spacecraft attitude control that has been underestimated, while control actuators and attitude sensors themselves are important sources of noise generation., the main purpose of this paper is to (i)control the satellite’s attitude and (ii)minimize the variance of output, simultaneously. The Minimum Variance controller, which is considered the simplest type of model predictive controller, has a powerful capability for minimizing the effects of output noise. This feature makes it a suitable control scheme for space-based high-resolution photography missions. so,, we described the conventional Minimum Variance regulator method at first, then an Incremental version of the regulator has been presented to solve the tracking problem. Finally, the generalized minimum variance controller which can control both minimum-phase and non-minimum-phase systems is derived for a high pointing accuracy spacecraft. The simulation results show the efficiency of the proposed controller to restrain the noise effects in a high-resolution tri-stereo imaging mission.
ResearchPaper
Space subsystems design: (navigation, control, structure and…)
Valiollah Shahbahrami; Milad َAzimi; َAlireza Alikhani
Articles in Press, Accepted Manuscript, Available Online from 06 March 2022
Abstract
In this paper, a robust adaptive hybrid control approach based on a combination of super-twisting and non-singular terminal sliding mode control (STNSMC) approaches for vibration and attitude control of a flexible spacecraft with fully coupled dynamic is developed. The proposed adaptation law eliminates ...
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In this paper, a robust adaptive hybrid control approach based on a combination of super-twisting and non-singular terminal sliding mode control (STNSMC) approaches for vibration and attitude control of a flexible spacecraft with fully coupled dynamic is developed. The proposed adaptation law eliminates the need for bounds knowledge of external disturbances and uncertainties. Then an ST-based NSMC generates a continuous control signal to reject the Chattering phenomenon, the non-singular terminal switching control law with the ability to generate continuous control commands to eliminate the chattering phenomenon. Moreover, finite-time convergence is achieved, and the singularity problem has been avoided. The overall stability of the system has been demonstrated using the Lyapunov theory. One of the essential features of the proposed control algorithm is to prevent overestimation of control gains and faster convergence rates comparing to conventional ST and non-singular terminal SMC approaches. The simulations in the form of a comparative study for large-angle maneuver reveal the advantage of the proposed approach.
ResearchPaper
Space subsystems design: (navigation, control, structure and…)
Abbas Dideban; Alireza Ahangarani Farahani
Articles in Press, Accepted Manuscript, Available Online from 29 August 2022
Abstract
This paper presents a new control methodology based on Continuous Time Delay Petri Nets (CTDPN) tool for the attitude control of satellite simulator. The graphical and mathematical features of this tool help the expert designer to design an appropriate controller using graphical model easily, and then ...
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This paper presents a new control methodology based on Continuous Time Delay Petri Nets (CTDPN) tool for the attitude control of satellite simulator. The graphical and mathematical features of this tool help the expert designer to design an appropriate controller using graphical model easily, and then apply the necessary changes to the mathematical model. In this approach, the controller gains are derived from the states and some other variables. Thus, the system states and variables must be available. The new gain tuning algorithm consists of three stages. First, A simulation environment is made for mathematical modeling based on the CTDPN tool and controller design. Secondly, using optimal methods, the controller gains are calculated at any given time and the data are collected. Finally, using the database, a relationship between the set of variables and the gains are derived. Experimental results indicate the promising performance of the controller in comparison to the conventional controller applied to the satellite simulator platform. The results indicate that the designed controller is robust against variation of parameters, as the controller gains are tuned based on the system state and variables.
ResearchPaper
safety in space
Mohammad Nadjafi; Hassan Naseh; Mehrdad Sedigh Koochaki
Articles in Press, Accepted Manuscript, Available Online from 05 February 2023
Abstract
The Monopropellant Hydrazine Propulsion system is one of the most widely used types of single-agent propulsion systems to control the position or correction of satellites in orbits. This system consists of combustion chamber subsystems (catalyst bed, catalyst, nozzle, and cap), fuel and fuel tank, high-pressure ...
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The Monopropellant Hydrazine Propulsion system is one of the most widely used types of single-agent propulsion systems to control the position or correction of satellites in orbits. This system consists of combustion chamber subsystems (catalyst bed, catalyst, nozzle, and cap), fuel and fuel tank, high-pressure tank, control valves, and interface pipes. In this paper, the MPHP system (as a case study) is described in detail, and then critical risks are identified by creating FMECA tables on the case study in the design phase. Based on the proposed FMCEA flowchart, potential failure modes are identified. In the next step, decisions and corrective actions are formulated regarding the inherent failures of the system. Finally, the necessary measures to reduce the risks will be taken according to the system's failure modes, and the reduction of the identified risks to an acceptable level is presented. The attained results show that the catalyst decomposition chamber, catalyst bed, inlet flow control valve, and propellant management facilities units have the highest risk index values (RPN), respectively. For this purpose, corrective measures have been suggested for each of these.
ReviewPaper
Space New Technologies
Pedram Hajipour; Roghieh Karimzadeh Baee; Houman Zarrabi; Roghayeh Doost; Leila Mohammadi
Articles in Press, Accepted Manuscript, Available Online from 05 February 2023
Abstract
According to the technical specifications of the future generations of telecommunication (the fifth generation and later), which should provide new services with very high data rates in the minimum time and a wide coverage, as well as the exponential increase in traffic, the use of combined space-air ...
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According to the technical specifications of the future generations of telecommunication (the fifth generation and later), which should provide new services with very high data rates in the minimum time and a wide coverage, as well as the exponential increase in traffic, the use of combined space-air networks Land is essential. It should be noted that the management of this type of combined networks has major challenges in providing such services. Meanwhile, the intelligent management of resources in satellite-based hybrid networks will lead to increased capacity and improved service quality. For this purpose, in this article, a comprehensive review of the use of artificial intelligence in the field of satellite communications will be discussed. In the field of intelligent increase of capacity, various factors such as how to configure the network, how to allocate resources such as spectrum, energy and power will be investigated with consideration of intelligent interference management. Finally, in the field of service quality improvement, factors such as how to model and intelligently predict traffic, as well as how to deal with harmful environmental conditions, will be presented.
ResearchPaper
Space Ground Segment: receiving, transmitting, controlling and data processing
Roghayeh Doost; Saber Shahidzadseh; Roghieh Karimzadeh Baee; Pedram Hajipour
Articles in Press, Accepted Manuscript, Available Online from 05 February 2023
Abstract
Aeronautical-ESIM (A-ESIM) provides a satellite broadband service for aircraft occupants. Due to the frequency sharing of this service with previous services, there is a possibility of its frequency interference on previous services. According to the resolution WRC 2019, the A-ESIM frequency interference ...
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Aeronautical-ESIM (A-ESIM) provides a satellite broadband service for aircraft occupants. Due to the frequency sharing of this service with previous services, there is a possibility of its frequency interference on previous services. According to the resolution WRC 2019, the A-ESIM frequency interference on co-frequency ground stations must be prevented by observing the power flux density (PFD) mask . However, the approval of the PFD condition fulfillment method has been postponed to the WRC 2023. In this regard, some countries have simulated and determined the minimum allowable height of A-ESIM from the ground, so that the PFD reached the ground does not exceed the specified mask. In many cases, only limited positions of unauthorized heights will cause the PFD to override the mask. Therefore, in this paper, with a new solution, the authorized and unauthorized positions of A-ESIM are determined at any height less than the minimum allowable height, relative to a fixed ground station. In addition, the unauthorized positions of the A-ESIM in both take-off and landing positions are simulated and determined depending on the slope of the A-ESIM.
ResearchPaper
Space subsystems design: (navigation, control, structure and…)
Arash Abarghooei; Hassan Salarieh; Pedram Hosseiniakram
Articles in Press, Accepted Manuscript, Available Online from 05 February 2023
Abstract
Linear algorithms are the most widely used method for satellite attitude control using reaction wheels because of their simplicity and low computational cost. The first part of the paper introduces different attitude determination and control algorithms, and reviews resources that utilized optimal linear ...
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Linear algorithms are the most widely used method for satellite attitude control using reaction wheels because of their simplicity and low computational cost. The first part of the paper introduces different attitude determination and control algorithms, and reviews resources that utilized optimal linear and nonlinear control methods (such as LQR and SDRE). Next, dynamic equations for the control of the satellite using reaction wheels have been extracted, then the satellite controller has been designed by using optimal linear and nonlinear methods, which are robust against noise and disturbance, as an alternative for the PD controller. Finally, the designed control algorithms have been implemented for different satellite pointing scenarios, and by simulating these methods in MATLAB software, their performance has been studied and compared.
ResearchPaper
investigating space radiation
Sara Shoorian; S. Amir Hosein Feghhi; Hamid Jafari; Reza Amjadifard
Articles in Press, Accepted Manuscript, Available Online from 15 February 2023
Abstract
Protection of astronauts and electronic components in satellites and spacecraft against space rays is one of the most important primary requirements in space missions. In this work, the effect of three materials, aluminum, as the most common material, polyethylene and a graded-z structure, in the protection ...
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Protection of astronauts and electronic components in satellites and spacecraft against space rays is one of the most important primary requirements in space missions. In this work, the effect of three materials, aluminum, as the most common material, polyethylene and a graded-z structure, in the protection of space radiations has been evaluated. The calculations of the dose caused by these radiations on the human body and a silicon piece have been carried out by MCNPX Monte Carlo code,. The dose caused by cosmic rays has been calculated after applying shields of aluminum, graded-z structure and polyethylene. The results showed that by using polyethylene and about 4.4% increase in weight compared to the aluminum shield, it is possible to reduce the dose caused by photons by more than 50% in the human body and 30% in silicon parts, and the dose caused by protons by about 30%. It cut both for astronauts and electronic components. Graded-z shielding performed very well in the dose attenuation caused by photons, but appeared ineffective in the dose attenuation caused by protons.
ResearchPaper
physiology and space medicine (astrobiology)
Articles in Press, Accepted Manuscript, Available Online from 05 March 2023
Abstract
Light is a vital factor for plant cultivation. LED lamps in different spectra have some advantages such as low heat production and energy requirement, and long lifespan, which was used for the first time to design plant growth chambers in closed culture systems and space research. In this research, impact ...
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Light is a vital factor for plant cultivation. LED lamps in different spectra have some advantages such as low heat production and energy requirement, and long lifespan, which was used for the first time to design plant growth chambers in closed culture systems and space research. In this research, impact of light spectrums was studied on the growth mechanisms through chlorophyll pigments, enzyme defense system, and antioxidant metabolite analyses. Seeds were cultivated in Murashige and Skoog medium and exposed to different light spectrums of white, red, blue, and red-blue. Then the seedlings were harvested for growth and biochemical analyses after 4 weeks. Results showed that red-blue and blue lights induced the fresh weight, dry weight, root length, adventitious roots, chlorophyll content, protein, flavonoids and antioxidant enzymes of superoxide dismutase and catalase. Blue spectrum significantly decreased stem length and increased the relative water content. Moreover, the highest amount of hydrogen peroxide was observed in seedlings treated with red light. It seems that light spectra by changing the hydrogen peroxide level can regulate antioxidant enzyme activity and enhance antioxidant metabolites, and red-blue light may use as a suitable lighting spectrum for the design of M. chamomilla cultivation chamber in space research.
ResearchPaper
investigating space radiation
gholamreza raisali; masume soleimaninia; Amir Moslehi
Articles in Press, Accepted Manuscript, Available Online from 05 March 2023
Abstract
In this paper, the sensitive volume and critical charge of a 65-nm CMOS SRAM as two important quantities in Single Event Upset (SEU) calculations have been determined. SEU is the most common event in space investigations. To this purpose, a memory cell which is consisted of NMOS and PMOS was simulated ...
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In this paper, the sensitive volume and critical charge of a 65-nm CMOS SRAM as two important quantities in Single Event Upset (SEU) calculations have been determined. SEU is the most common event in space investigations. To this purpose, a memory cell which is consisted of NMOS and PMOS was simulated using Silvaco TCAD tool. Then, the variations in output voltages were studied after striking incident particles with different values of Linear Energy Transfer (LET) at different regions of the transistors. The Qcritical was obtained by integrating the output current when the output voltages were inverted. To determine the sensitive volume, the minimum amount of LET in which the output logic state of the memory cell flips, was considered as a criteria of sensitivity. The results showed the value of 0.054 µm3 and 1.48 fC for sensitive volume and critical charge, respectively which are in good agreement with the references.
ResearchPaper
investigating space radiation
Pedram Hajipour; Leila mohammadi; Azam Eidi; Sara Shoorian; Nahid Eidi esfiani; Seyed Amir Hossein Feghhi
Articles in Press, Accepted Manuscript, Available Online from 12 March 2023
Abstract
One of the damaging factors for the proper functioning of telecommunication payloads are high energy ionizing particles in space, which the use of proper shield is a way to deal with it. In the design of protection, several factors, such as the type of part and the amount of weight acceptable for the ...
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One of the damaging factors for the proper functioning of telecommunication payloads are high energy ionizing particles in space, which the use of proper shield is a way to deal with it. In the design of protection, several factors, such as the type of part and the amount of weight acceptable for the payload.etc.must be taken into consideration. In recent years, in order to reduce the costs of construction and launch, the use of non-space components has been favored.Therefore, the use of shields with the suitable material in with radiation resistance, with respect to the weight budget considerations, will be one of the important challenges .In this paper, the aim is to investigate the methods of reducing the weight budget considering with respect to the radiation damage of ionizing dose. In this regard, a five-year technology development mission in the GEO orbit has been predicted, and the results of simulations and testing of aluminum and polyethylene shielding to check ionizing dose damage, according to the initial and reference weight budget, have been presented and compared. The analysis and evaluation of the test results using polyethylene protection shows a 17.21 percentage reduction between the two external and internal radiation meters.
ResearchPaper
Infrastructure (labs, sensors, software,…)
Mojtaba Salehi; Mohammad Navabi
Articles in Press, Accepted Manuscript, Available Online from 20 April 2023
Abstract
In a flying system, attitude control is one of the essential subsystems. In this subsystem, estimating the current state is very important to control the state, which is achieved by considering the attitude sensors. Comprehensive research is being done today to reduce the cost of Attitude sensors in ...
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In a flying system, attitude control is one of the essential subsystems. In this subsystem, estimating the current state is very important to control the state, which is achieved by considering the attitude sensors. Comprehensive research is being done today to reduce the cost of Attitude sensors in applications such as drones, satellite simulation platforms, etc. For this purpose, sensors based on Micro-electromechanical Systems have received much attention due to their small size and low energy consumption. This model of sensors, despite its many advantages, has various noises and disturbances that require the application of fusion and estimation algorithms to obtain an acceptable output. In this research, to determine the attitude of the test platform, data fusion algorithms including complementary filter, Kalman filter, and Extended Kalman filter are implemented on a low-cost sensor. The mentioned estimation methods were implemented on the test platform and by determining the effective parameters in the estimation algorithms, the desired accuracy was obtained. The module obtained in these experiments is comparable to more expensive sensors.
ResearchPaper
GPS and navigation
reza ghasrizadeh; Amir Ali Nikkhah
Articles in Press, Accepted Manuscript, Available Online from 12 May 2023
Abstract
This paper presents a solution for detecting and recovery for the spoof error of GPS receiver signals, in order to increase the accuracy of the navigation system integrating inertial systems with GPS signals. integrated inertial navigation and GPS data has many advantages. However, due to the weakness ...
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This paper presents a solution for detecting and recovery for the spoof error of GPS receiver signals, in order to increase the accuracy of the navigation system integrating inertial systems with GPS signals. integrated inertial navigation and GPS data has many advantages. However, due to the weakness of satellite signals against jamming and spoof attacks of providing analytical solutions, they have a special place in improving Kalman filter estimation compared to hardware solutions. In this paper, a new method for loosely coupled of INS/GPS is presented, in which the steady state of Kalman gain parameters is used during deception detection and recovery. With the gain parameters of the Kalman filter tending to constant values, with the aim of correcting and predicting the error of state variables, it can be used to detection GPS spoofed data. It can be detected by spoof in the GPS receiver signal when couple with inertial waves through the amount of Kalman gain fluctuations. In the case of closed loop, the Kalman gain matrix denominators tend to a constant value, and in case of deception, this function is associated with many fluctuations. By using dynamic weighting, the effect of errors caused by these attacks is recovered.
Technical Note
Space subsystems design: (navigation, control, structure and…)
حامد کاشانی
Articles in Press, Accepted Manuscript, Available Online from 14 May 2023
Abstract
Aerospace systems and subsystems are subjected to impulsive loads due to several reasons like engine start and burnout, separation and so on. These loads may make temporary or permanent failures in some sensitive components or subsystems. To avoid these failures some constraints should be consider in ...
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Aerospace systems and subsystems are subjected to impulsive loads due to several reasons like engine start and burnout, separation and so on. These loads may make temporary or permanent failures in some sensitive components or subsystems. To avoid these failures some constraints should be consider in design mechanical process. Another approach can be reducing the load level in transmission path without any change in the source of load and without adding any new component and only with design optimization of available components i.e. structural joints destructive effects of impulsive loads. This paper uses analytical results of joints behavior to present practical solution for minimizing load transmission through the joint.
ResearchPaper
Space subsystems design: (navigation, control, structure and…)
Mahdi Rivandi; Mehran Mirshams; Mohammad Zarourati
Articles in Press, Accepted Manuscript, Available Online from 21 May 2023
Abstract
To test the attitude determination and control subsystem of a satellite, an attitude dynamics simulator is needed, and the simulator must also be placed in a weight balance condition. The disturbances considered for simulation resulting from the deviations caused by the difference between the center ...
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To test the attitude determination and control subsystem of a satellite, an attitude dynamics simulator is needed, and the simulator must also be placed in a weight balance condition. The disturbances considered for simulation resulting from the deviations caused by the difference between the center of mass and rotation, as well as the movement of two horizontal Actuators, which is a factor for the rotational and vortex movement of the simulator, are presented as disturbances entering the balance system. Experimental models and proportional-integral-derivative control coefficients for three axis control are used in simulation. Mass Sliders and reaction wheels are used in the horizontal and vertical axes, respectively, which are the actuators of the balance system. Finally, we reach the accuracy of 0.2 deg and 0.5 deg for the Euler angles, roll and pitch, respectively, in a period of 25s, indicating a suitable accuracy for balancing the CubeSat attitude simulator system.
Technical Note
space sciences and exploration
Fateme Mousavi
Articles in Press, Accepted Manuscript, Available Online from 21 May 2023
Abstract
Seed aging is a process that can lead to a complete loss of seed viability. This process occurs when seeds are exposed to long-term storage or controlled deterioration treatments such as excessive dryness, lack of oxygen, and temperature fluctuations on Earth or in outer space. Proteomic changes can ...
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Seed aging is a process that can lead to a complete loss of seed viability. This process occurs when seeds are exposed to long-term storage or controlled deterioration treatments such as excessive dryness, lack of oxygen, and temperature fluctuations on Earth or in outer space. Proteomic changes can occur in the dry state of seeds. Extreme temperature fluctuations in outer space, especially on the moon and Mars, are one of the most important challenges for space scientists to transfer plant seeds and grow them in outer space outside the atmosphere. The present study studied the effects of simulated space temperature fluctuations on the quantitative and qualitative content of dry tomato seed proteins. The results showed 13 protein bands in the molecular weight range of 8.89 to 91.82 kilodaltons. A double or more significant decrease in the intensity of protein bands with high molecular weight was also observed in the treated group compared to the control. Finally, the two-dimensional electrophoresis technique followed by mass spectrometry is suggested for better resolution of tomato seed proteins and their better separation, as well as identification of unknown protein bands in future studies.
