Parviz Behrouzi
Volume 1, Issue 1 , October 2004, , Pages 1-8
Abstract
During its near-ground hovering phase a Short Take-Off and Vertical Landing (STOVL) aircraft creates a complex three-dimensional flow field between jet streams, the airframe surface and the ground. A proper understanding and numerical prediction of this flow is important in the design of such aircraft. ...
Read More
During its near-ground hovering phase a Short Take-Off and Vertical Landing (STOVL) aircraft creates a complex three-dimensional flow field between jet streams, the airframe surface and the ground. A proper understanding and numerical prediction of this flow is important in the design of such aircraft. In this paper an experimental facility, used to gather validation data suitable for testing Computational Fluid Dynamics (CFD) model predictions of multi-jet ground impingement flows, is described. Water is used as the working medium and Laser Doppler Anemometry (LDA) measurements of three-poster impinging jet flow fields are reported. Emphasis is placed on the presentation of the mean and rms velocity contours in the fountain formation region between the jets. The effect of jet imbalance and splay-angle were studied. An overview were provided to guide users through the data and highlight several important flow features which have already emerged from the data and which are considered of importance to CFD model validation.
Volume 2, Issue 1 , March 2005, , Pages 1-5
M. Taeibi- Rahni; M. Ramezanizadeh
Volume 2, Issue 2 , June 2005, , Pages 1-9
Volume 2, Issue 3 , September 2005, , Pages 1-8
Volume 2, Issue 4 , December 2005, , Pages 1-8
Mehdi Nazarinia; Mohammad Reza Dr. Soltani; Kaveh Ghorbanian
Volume 3, Issue 1 , March 2006, , Pages 1-20
Abstract
An extensive experimental study is conducted to examine effects of different winglet-shapes and orientations on the vortex behind a wing, static surface pressure over the wing, and wing wake of a swept wing at various angles of attack. Four types of winglets, spiroid (forward and aft), blended, and winggrid ...
Read More
An extensive experimental study is conducted to examine effects of different winglet-shapes and orientations on the vortex behind a wing, static surface pressure over the wing, and wing wake of a swept wing at various angles of attack. Four types of winglets, spiroid (forward and aft), blended, and winggrid are used in this investigation. Wing static surface pressure measurements are obtained for both chordwise and spanwise, as well as the wake profiles at various angles of attack using the aforementioned winglets. The data are compared with those of the wing without winglet, bare wing. The results show that addition of winglets change the flowfield over and around the wing significantly. Furthermore, it is found that certain winglet configurations improve both the wake and the wing pressure distribution. The total pressure in the wake of the model varies drastically when the wing is equipped with winglets. Keywords: Winglets, Pressure Distribution, Induced Drag, Spiroid Winglet, Turbulator.
Mohammad Ali Kouchakzadeh
Volume 4, Issue 1 , March 2007, , Pages 1-8
Abstract
The buckling analysis of rectangular laminated composite plates with an edge delamination under in-plane compressive loading is performed using the finite element method. Such a plate may be considered as a simplified model of stiffener plates of a stiffened panel. The buckling load and buckling mode ...
Read More
The buckling analysis of rectangular laminated composite plates with an edge delamination under in-plane compressive loading is performed using the finite element method. Such a plate may be considered as a simplified model of stiffener plates of a stiffened panel. The buckling load and buckling mode are obtained by solving an eigenproblem. In an unconstrained analysis, physically inadmissible modes appear because of the overlap between separated sublaminates in the delaminated region. To eliminate overlap, constraints are added iteratively on the entire overlapped area using penalty function method. The validity and superiority of the analysis method in predicting buckling load and buckling mode is shown in comparison with the experimental and analytical results available in the literature. Numerical results show the effect of delamination width and depth and boundary conditions on the buckling load.
A.L. Mehrabian; Jafar Dr. Roshanian
Volume 4, Issue 2 , June 2007, , Pages 1-12
F. Saghafi; farid Shahmiri
Volume 4, Issue 3 , September 2007, , Pages 1-11
Abstract
The purpose of this paper is concerned with the mathematical model development issues, necessary for a better prediction of dynamic responses of articulated rotor helicopters. The methodology is laid out based on mathematical model development for an articulated rotor helicopters, using the theories ...
Read More
The purpose of this paper is concerned with the mathematical model development issues, necessary for a better prediction of dynamic responses of articulated rotor helicopters. The methodology is laid out based on mathematical model development for an articulated rotor helicopters, using the theories of aeroelastisity, finite element and the time domain compressible unsteady aerodynamics. The helicopter is represented by a set of coupled nonlinear partial differential equations for the main rotor within nonlinear first order ordinary differential equations representation, describing the dynamics of the rest of the helicopter. The complexity of the formulation imposes the use of numerical solution techniques for dynamic response calculations. The validation is performed by comparing simulated responses oppose to flight test data for a known configuration. The results show improvement in dynamic response prediction of both on-axis and cross-coupled responses of helicopter to pilot inputs.
M. Sohrabian
Volume 4, Issue 4 , December 2007, , Pages 1-6
Abstract
This paper investigates the dynamical behavior of an assembled beam like structure with tip masses modeling a two stage space rocket structure. The beam like structure is composed of two beams connected together carrying two masses at the free ends to model the payload, and the stabilizing fins mass ...
Read More
This paper investigates the dynamical behavior of an assembled beam like structure with tip masses modeling a two stage space rocket structure. The beam like structure is composed of two beams connected together carrying two masses at the free ends to model the payload, and the stabilizing fins mass properties. The effect of non-homogeneity of the structure due to different cross section properties at each stages of the rocket and the tip masses, heavily affects the dynamical behavior and stability regions of the structure if excited using a follower force. The rocket thrust is considered in this study as follower force as in flexible space structures the thrust direction is affected by the lateral vibrations of the structure. As demonstrated in this study the primarily mode of instability in such a structure, i.e. divergence or flutter, depends on the stiffness and mass distributions of the structure. This would enable the designer to alter the mode of instability by modifying these distributions. In inspecting the instability regions of the structure under follower force, and establishing an analytical solution, the Galerkin method is employed and the stability regions of the structure are determined.
Reza Kamali
Volume 5, Issue 1 , March 2008, , Pages 1-11
Abstract
Today, Flapping Micro Aerial Vehicles (MAV) are used in many different applications. Reynolds Number for this kind of aerial vehicle is about 104 ~ 105 which shows dominancy of inertial effects in comparison of viscous effects in flow field except adjacent of the solid boundaries. Due to periodic flapping ...
Read More
Today, Flapping Micro Aerial Vehicles (MAV) are used in many different applications. Reynolds Number for this kind of aerial vehicle is about 104 ~ 105 which shows dominancy of inertial effects in comparison of viscous effects in flow field except adjacent of the solid boundaries. Due to periodic flapping stroke, fluid flow is unsteady. In addition, these creatures have some complexities in kinematic modeling. Although numerical methods are widely used for unsteady aerodynamic problems, it is highly difficult to solve the full 3D Navier–Stokes equations for complex flows like the ones of the flapping insect wings. Actually, the numerical simulation of flapping wings for different conditions of flapping frequencies and wing shapes has not been done yet. This is done in the present study. In present study, a computer code based on the unsteady Panel Method has been developed for flow analysis. The prepared algorithm and the computer code are capable of modeling MAVs flapping wings in different unsteady conditions. The results of aerodynamic design coefficients have been drew. At the end the optimum wing shape and flapping frequency are chosen as another result of this study.
H. Mehrjou; Mohammad Farshchi
Volume 6, Issue 1 , March 2009, , Pages 1-12
Abstract
An efficient finite volume approach has been used to develop a three dimensional Helmholtz acoustic solver for complex geometries. This acoustic solver was utilized to obtain characteristic mode shapes and frequencies of a baffled combustion chamber. An experimental setup, including stationary and moving ...
Read More
An efficient finite volume approach has been used to develop a three dimensional Helmholtz acoustic solver for complex geometries. This acoustic solver was utilized to obtain characteristic mode shapes and frequencies of a baffled combustion chamber. An experimental setup, including stationary and moving sensors, has also been used to measure these quantities for the same model combustion chamber. Although each of these methods has certain limitations, combination of the numerical results and the experimental data provide a capability to identify complicated acoustical fields created by the combustor complex geometry. Using this approach the effects of the nozzle convergent section and the number of radial baffles on the chamber’s dominant acoustic modes were investigated. It has been shown that acoustic solver is capable of capturing major effects caused by the presence of radial baffles and combustor nozzle geometry; however radial baffles may produce nonlinear effects that cannot be captured by a Helmholtz acoustic solver.
Ali Moosavi; Masoud Mirzaei; Jafar Dr. Roshanian
Volume 7, Issue 1 , March 2010, , Pages 1-8
Abstract
The purpose of this paper is to examine the multidisciplinary design optimization (MDO) of a reentry vehicle. In this paper, optimization of a RV based on, minimization of heat flux integral and minimization of axial force coefficient integral and maximization of static margin integral along reentry ...
Read More
The purpose of this paper is to examine the multidisciplinary design optimization (MDO) of a reentry vehicle. In this paper, optimization of a RV based on, minimization of heat flux integral and minimization of axial force coefficient integral and maximization of static margin integral along reentry trajectory is carried out. The classic optimization methods are not applicable here due to the complexity of the equations, therefore in this research, the genetic algorithm technique is utilized for optimization of the RV. In addition, the results of the genetic algorithm, are validated with those of two other methods, Pareto genetic algorithm and response surface method. In the present paper, in order to decrease the computational time, parallel processing strategy is employed
hasan sajjadi; S. F. Hosseinizadeh; Y. Vazifehshenas
Volume 8, Issue 1 , March 2011, , Pages 1-10
Abstract
Numerical investigation was performed on NACA 0015 which is a symmetric airfoil. Pressure distribution and then lift and drag forces are verified. Changing of ground clearance was a considerable point. Also the angle of attack was changed from 0° to 10°. Pressure coefficient reaches its higher amounts ...
Read More
Numerical investigation was performed on NACA 0015 which is a symmetric airfoil. Pressure distribution and then lift and drag forces are verified. Changing of ground clearance was a considerable point. Also the angle of attack was changed from 0° to 10°. Pressure coefficient reaches its higher amounts on the wing lower surface when the ground clearance diminishes. Increment of the angle of attack leads to outspread of the high pressure domain over the lower surface and so leads to greater lift force. For higher angles of attack the ground clearance had no effect on the pressure distribution. Mostly for high angles of attack, the suction effect on the upper surface makes an adverse pressure gradient which can cause turbulent behavior and finally enhance drag force. To solve the problem SIMPLE algorithm is utilized. Moreover, QUICK algorithm and second-order upwind are used for momentum verification and turbulent viscosity, respectively. After all, the efficiency of the utilized model is checked. It is observed that k-e model cannot give acceptable results admitting experimental achievements in comparison with Spalart-Allmaras. This is depicted for drag and lift coefficient and also the pressure distribution on both surfaces of the airfoil.
A. Ebadi; Ehsan Selahi
Volume 11, Issue 2 , October 2017, , Pages 1-11
Abstract
The purpose of this paper is to estimate the fatigue life of an airplane wing with laminated composite skin, subjected to variable mechanical and thermal loads. To achieve this aim,at first, the three-dimensional model of airplane wing was drawn in CATIA software. Then, by transferring the model to the ...
Read More
The purpose of this paper is to estimate the fatigue life of an airplane wing with laminated composite skin, subjected to variable mechanical and thermal loads. To achieve this aim,at first, the three-dimensional model of airplane wing was drawn in CATIA software. Then, by transferring the model to the ABAQUS software, the finite element model of the wing wascreated. Here, the spars and ribs weremade ofaluminum T7075 and skin waslaminated composite with uni-directional and woven roving carbon epoxy layers. The convergence behavior of the structure wasexamined for selecting an appreciate element numbers. Finally, transient dynamic analysis followed by fatigue analysis of the wing structure was carried out. By performing fatigue simulation, the number of loading cycles resulted in failure of the structural components and wing skin panel was predicted. By comparing the simulation results with experimental research carried out by other researchers, the validity of the presented simulation method was demonstrated. The results of this research indicated that the replacement of traditional metallic wing skin with laminated composite skin causes a significant increase in fatigue life of the wing,besides a considerable weight reduction.
Hassan Isvand; Ahmad Sharafi; Ali Salmaninejad
Volume 12, Issue 1 , March 2019, , Pages 1-14
Abstract
In this study, the behavior of a subject consisting of a cylinder with 4 plates perpendicular to it with a rotational degree of freedom under airflow both through the numerical approach, known as improved discrete vortex and experimental approach were investigated. The experimental and numerical results ...
Read More
In this study, the behavior of a subject consisting of a cylinder with 4 plates perpendicular to it with a rotational degree of freedom under airflow both through the numerical approach, known as improved discrete vortex and experimental approach were investigated. The experimental and numerical results have shown that oscillating regime occurs in low velocity and length. This movement is vibrations with irregular range around an equilibrium angle of 45 degree. In oscillating motion regime, it is seen that after releasing the object in free flow, a high torque force, due to the flow’s acceleration from the model, is induced to the plates and makes a big angular change, but after a while, the range of oscillation around the equilibrium angle of 45 degree decreases. The probability of rotational motion regime in length ratio of one and velocity of 13 m/sec in initial angle of attack is low. However, the experimental and numerical results have indicated that still in high initial angle of attack around 45 degree, owing to the induced decreased torque to plates, there exists an oscillating movement. Rotational regime in length ratio of 3 and free flow velocity 13 m/sec in all initial angle of attack is observed. In addition, rotational regime appears in all initial angle of attack with the length ratio of 4 and different free flow velocities because of increase in the area of plates.
Aerospace Science and Technology
Milad Noorabadi; Rahnama Malihe; Ghasemi Mohammad Amin; Jafar Eskandari Jam
Volume 12, Issue 2 , October 2019, , Pages 1-9
Abstract
In this paper the energy absorption capacity of stiffened circular composite tube is considered. The governing equations and dynamic equilibrium are first derived and then solved. Additionally, a finite element model of reinforced circular composite tube structure is modeled. At the following, the effects ...
Read More
In this paper the energy absorption capacity of stiffened circular composite tube is considered. The governing equations and dynamic equilibrium are first derived and then solved. Additionally, a finite element model of reinforced circular composite tube structure is modeled. At the following, the effects of various parameters such as structural geometry, number of rings and stingers on mechanical behavior of such tubes are considered. The Stiffened cylinder is under axial loading and internal pressure, and boundary conditions for both sides of the cylinder are considered as simple supports. Results show increasing in the amount of energy in the stingers while the number of stingers increases, and decreasing in the amount of total energy while the number of rings and stringers are increase. Total strain energy and the strain energy created in structural elements increase by increasing the ratio of radius to thickness. The analytical solution results are in good compatibility with the results achieved from the finite element method.
Reza Soltani Nezhad; Abolqasem Naghash
Abstract
This article examines the fault tolerance control (FTC) system for the Boeing 747. to reach this goal, firstly 6 degrees of freedom equations are simulated and linearized by using dynamic inversion method. Then, the system is controlled by a linear proportional-integral-derivative controller. To control ...
Read More
This article examines the fault tolerance control (FTC) system for the Boeing 747. to reach this goal, firstly 6 degrees of freedom equations are simulated and linearized by using dynamic inversion method. Then, the system is controlled by a linear proportional-integral-derivative controller. To control this system, the angular velocity loop (r, q, p) must be closed and use cascade control to achieve this goal. Faults such as actuator and sensor failure are injected into the system, and by adding an integrated gain to the controller, the system resists these faults. Also, a redundancy system has been used in sensors to prevent sensor faults. Moreover, a linear Kalman filter has been used to eliminate noise in the system. If an actuator is locked in the Boeing 747, the faulty actuator is removed from the control system. Then, a healthy actuator or other remaining actuators will eliminate the effects of this fault.
Aerospace Science and Technology
ali Vahedi; Mohammad Homayoun Sadr; Saied Shakhesi
Abstract
Epoxy is among the most important polymers, which is extensively employed in various technologies and applications. Nevertheless, epoxy polymers present low thermal conductivities and thus the enhancement of their thermal conductivity is an important research topic. Carbon nanotubes (CNTs) owing to their ...
Read More
Epoxy is among the most important polymers, which is extensively employed in various technologies and applications. Nevertheless, epoxy polymers present low thermal conductivities and thus the enhancement of their thermal conductivity is an important research topic. Carbon nanotubes (CNTs) owing to their excellent thermal conductivities have been widely considered for the enhancement of the thermal conduction of epoxy polymers. In this work, we developed a combined molecular dynamics finite element multiscale modelling to investigate the heat transfer along CNT/epoxy nanocomposites. To this aim, the heat transfer between the CNT and epoxy atoms at the nanoscale was explored using the atomistic classical molecular dynamics simulations. In this case, we particularly evaluated the interfacial thermal conductance between the polymer and fillers. We finally constructed the continuum models of polymer nanocomposites representative volume elements using the finite element method in order to evaluate the effective thermal conductivity. The developed multiscale modelling enabled us to systematically analyze the effects of CNT fillers geometry (aspect ratio), diameter and volume fraction on the effective thermal conductivity of nanocomposites. Our results suggest that the interfacial thermal conductance between the CNT additives and epoxy polymer dominate the heat transfer mechanism at the nanoscale.The obtained findings in this study provide good vision regarding the enhancement of thermal conductivityof polymeric materials using highly conductive nanofillers.
Aerospace Science and Technology
Mahdi Azizi; Alireza Jahangirian
Abstract
To keep pace with current trends in the wind industry, this paper aims at the improvement of the annual energy production of a horizontal axis wind turbine by aerodynamic optimization of blades at the wind conditions of the Manjil site. To achieve this goal, the Riso wind turbine, whose characteristics ...
Read More
To keep pace with current trends in the wind industry, this paper aims at the improvement of the annual energy production of a horizontal axis wind turbine by aerodynamic optimization of blades at the wind conditions of the Manjil site. To achieve this goal, the Riso wind turbine, whose characteristics are publicly available, is selected, and its twist angle and chord length distributions along the blades are optimized. The blade element momentum theory with appropriate corrections is used to predict the turbine output power. The genetic algorithm optimization tool, and Weibull probability density function, for wind regime representation, are also utilized in this work. Optimization results show a 9.4% and 11.6% increase in annual energy production, respectively, for the blade with optimal twist angle and the blade with optimal chord length and twist angle distributions. Finally, the superiority of selecting annual energy production as the objective function is assessed in comparison with other objective functions.
Aerospace Science and Technology
Sahar Noori; Mohamad Saleh Afshar; Nima Karimi
Abstract
Airships usually have low cruising speed due to their large volume and high drag level. This makes the aerodynamic design of the vehicle, including the surfaces shape, the length-to-diameter ratio and the position of the fins, all very important. Furthermore, an important parameter in the vehicle aerodynamic ...
Read More
Airships usually have low cruising speed due to their large volume and high drag level. This makes the aerodynamic design of the vehicle, including the surfaces shape, the length-to-diameter ratio and the position of the fins, all very important. Furthermore, an important parameter in the vehicle aerodynamic drag is determining the flow separation area at the rear of the air vehicle. The flow separation plays an essential role in the amount of drag and lift force, so the location of the fins and the design of the rear of the airship will be very important. By using both analytical and numerical methods, this study examines the aerodynamic efficiency of an airship in three different configurations, focusing on the location, type, and angle of attack of the fin, and compares analytical and numerical results. According to studies conducted among the types of fins, the cross-type will have the best performance among the fins in terms of lift-drag ratio. Also, moving the fins forward and distancing them from the rear of the vehicle disrupts the flow pattern at the rear of the vehicle and delays separation. This will improve aerodynamic efficiency and improve the lift-drag ratio of the vehicle.
Aerospace Science and Technology
Seyed mohammad navid ghoreishi; Nabi Mehri-Khansari; Houman rezaei
Abstract
Regardless of the initiation or propagation procedure of crack in a gas turbine blade, the precise expectation of the fracture behavior, such as mixed-mode Stress Intensity Factors (SIF), plays a significant role in acquiring its operational life. Therefore, multilateral three-dimensional fracture solutions ...
Read More
Regardless of the initiation or propagation procedure of crack in a gas turbine blade, the precise expectation of the fracture behavior, such as mixed-mode Stress Intensity Factors (SIF), plays a significant role in acquiring its operational life. Therefore, multilateral three-dimensional fracture solutions are required, including real-based mixed-mode loading (I/II/III) conditions and geometrical considerations. In this study, three-dimensional semi-elliptical crack in a gas turbine blade with various geometrical parameters and inclination angles under mixed-mode loading (I/II/III) conditions were investigated based on the employing finite element techniques and analytical procedure. In this context, the semi-elliptical crack has been considered in the critical zone of the rotating blade to achieve the effect of crack aspect ratio, rotational velocity, crack location, and mechanical properties. Fluid Solid Interaction (FSI) analysis was also performed in addition to solid functional enriched elements. Structural simulation is done at the speed of 83.776 m/s based on CFD simulation. The results indicated that Al Alloys blade shows a profitable resistance in crack propagation. Moreover, as the crack domain is near the location of x/c= 0.25 and 1.9 of crack front, the mode II SIF will be independent of rotational velocity and the blades' mechanical properties. Similarly, for the location of x/c= 1.1 in crack front, the mode III SIF is independent of rotational velocity and blades' mechanical properties.
Aerospace Science and Technology
Hassan Naseh; Mehran MirShams; Hamid Reza Fazeley
Abstract
Recently, engineering systems are quite large and complicated. Conceptual design process of Space Transportation Systems (STSs) is a multidisciplinary task which must take into account interactions of various disciplines and analysis codes. Current approach for the conceptual design of STSs requires ...
Read More
Recently, engineering systems are quite large and complicated. Conceptual design process of Space Transportation Systems (STSs) is a multidisciplinary task which must take into account interactions of various disciplines and analysis codes. Current approach for the conceptual design of STSs requires the evaluation of a large number of different configurations and concepts. With existing legacy codes, estimating the performance of all design combinations becomes very time consuming and computationally expensive. A possible solution to this problem could be employing of surrogates during design tasks. This paper describes an effort to optimize the design of an entire STS to achieve a low Earth orbit, consisting of multiple stages using an efficient surrogate-based Multidisciplinary Design Optimization (MDO) framework with the goal of minimizing vehicle weight and ultimately vehicle cost. Furthermore, a combination of Response Surface Methodology (RSM) and Kriging surrogates has been used for building surrogate models. The disciplines of aerodynamics, propulsion, trajectory simulation, geometry, and mass properties, have been integrated to produce an engineering system model of the entire vehicle. In addition, the system model has been validated using the existing design data of STS’s trajectory and their subsystems. For the design optimization, in order to ensure that the payload achieves the desired orbit, a hybrid algorithm has been used to minimize the deference between the actual and desired orbital parameters. The objective function of the optimization problem is to minimize the overall system mass, thus minimizing the system cost per launch. The proposed design and optimization methodology provides designers with an efficient and powerful approach in computation during designing space transportation systems and can also be developed for more complex industrial design problems with comparable characteristics.
Aerospace Science and Technology
Mahsa Azadmanesh; Jafar Roshanian; Mostafa Hassanalian
Abstract
This paper employs the fast terminal sliding mode control with the sign and the saturation function to track the landing trajectory of a probe on an asteroid and to further improve the dynamic tracking performance. Then the controller is enhanced by adding the fuzzy control to both fast terminals. To ...
Read More
This paper employs the fast terminal sliding mode control with the sign and the saturation function to track the landing trajectory of a probe on an asteroid and to further improve the dynamic tracking performance. Then the controller is enhanced by adding the fuzzy control to both fast terminals. To make fair judgments on the performance of the suggested method, the proportional derivative sliding mode control with both the sign function and the saturation function is simulated as well. The two-point barycentric gravitational model is used to describe the weak gravity around the asteroid. The proposed fuzzy fast terminal method raises the convergence speed, improves the desired trajectory tracking accuracy and ensures that the system modes are placed on the sliding surface in a short, limited time. The absolute errors for the proportional derivative sliding mode controller, fast terminal sliding mode controller and improved fast terminal sliding mode controller are about 244, 139 and 113. The trajectories along all three coordinate axes in the proportional derivative sliding mode controller, fast terminal sliding mode controller and improved fast terminal sliding mode controller were tracked in 8 seconds, 5 seconds and 4 seconds. The results show how the fuzzy-fast terminal sliding mode control with the saturation function is the better choice of controller and how the fuzzy system is able to adapt to the momentary fluctuations and cover them successfully.
Aerospace Science and Technology
Amir Moghtadaei Rad
Abstract
In this article, a complete model including cross-coupling of azimuth and elevation axes, the effect of axis friction, non-perpendicularity and imbalance of axes was implemented for the platform with two degrees of freedom. Since this model includes 3 loops of current, stability and tracking from the ...
Read More
In this article, a complete model including cross-coupling of azimuth and elevation axes, the effect of axis friction, non-perpendicularity and imbalance of axes was implemented for the platform with two degrees of freedom. Since this model includes 3 loops of current, stability and tracking from the inside to the outside, it was necessary to design a suitable controller for each loop separately from the inside to the outside after linearizing the obtained model. Also, due to the presence of two channels, azimuth and elevation, it was necessary to repeat and design 3 controllers for both channels separately. Since the purpose of this article is to compare the performance of different controllers, PID, Fuzzy, Fuzzy PID and Fuzzy self-tuning controllers for both channels and all loops, their design and performance in time and frequency domains were analyzed. At the end, relative advantages of each controller according to different parameters of the system were presented in a comparative table.