Structure
Saeed Ahmadpour Kasgari
Abstract
Paying attention to the increasing use of metal-polymer composites in aerial and space structures and their economic efficiency, it is possible to achieve a more economical and high-quality connection by determining the appropriate parameters. The purpose of this article is to calculate the optimal parameters ...
Read More
Paying attention to the increasing use of metal-polymer composites in aerial and space structures and their economic efficiency, it is possible to achieve a more economical and high-quality connection by determining the appropriate parameters. The purpose of this article is to calculate the optimal parameters for the friction stir welding (FSW) process to properly join aluminum to polymer. Polycarbonate sheets and aluminum alloy sheets, widely used materials in the aerospace industry, were employed for FSW. Initially, a traditional FSW was conducted without additional material. Subsequently, for two samples, a layer of epoxy glue was placed between the two sheets, followed by FSW. On the second sample, a restorative FSW was performed with a 10 mm comb stirrer head. The results indicated that the most optimal condition was a spindle speed of 1400 r/min and a welding speed of 50 mm/min, particularly for the sample with epoxy glue and repair welding. Traditional FSW showed flaws, while FSW with adhesive displayed fewer defects. Repair welding significantly influenced the FSW joint, enhancing the cleanliness of the macroscopic appearance of the weld surface. In the tensile test, it was observed that the tensile strength of the repair weld exceeded that of the joint welded by two traditional methods and with glue. Microscopic results revealed more holes in FSW with two traditional methods and with glue, gradually reducing defects during repair welding.
Structure
Alireza Zarezadeh; Mohammad Hossein Allaee; Mohsen Heydari Beni; Ali Davar; Jafar Eskandari Jam
Abstract
The filament winding process is one of the most important and widely used processes in the manufacture of composite structures in order to achieve high strength and rigidity. In this process, there are important parameters such as fiber tension, how the fibers are twisted, the effect of layering, twisting ...
Read More
The filament winding process is one of the most important and widely used processes in the manufacture of composite structures in order to achieve high strength and rigidity. In this process, there are important parameters such as fiber tension, how the fibers are twisted, the effect of layering, twisting angle, fiber twisting pattern of fibers, type of material suitable for twisting, etc. , which can play a significant role in this the strength of the processstructure. In this regard, the twisting pattern has been less studied by researchers less than other parameters. In this research, the effect of fiber twisting pattern on the hydrostatic pressure threshold of epoxy glass cylinder has been investigated. For this purpose, first, glass/epoxy cylinders with 4 four different twisting patterns were made with ± 54 arrangement and subjected to hydrostatic test with internal pressures of 5-50 bar, where the amount of radial displacement in the middle of the cylinder was measured experimentally. In the following, the amount of radial displacement of cylinders due to the internal pressure was is also modeled using numerical analysis (Abaqus) and compared with experimental results. In order to validate the experimental and numerical results, theoretical model was used and the results were compared. All of the results obtained were in acceptable limits and showed that the twist pattern having with finer texture has a higher compressive strength. Also, the simulation results showed a good agreement with the experimental results
Structure
hassan Naseh; Hadiseh Karimaei; mohammad lesani
Abstract
In this paper, the structural optimization of a space capsule has been discussed by approximating a thin-walled cylindrical shell with a certain length under the axial compression force and constant lateral pressure. Design variables include the outer diameter and cylinder thickness. The purpose of optimization ...
Read More
In this paper, the structural optimization of a space capsule has been discussed by approximating a thin-walled cylindrical shell with a certain length under the axial compression force and constant lateral pressure. Design variables include the outer diameter and cylinder thickness. The purpose of optimization is to minimize the mass and maximize the frequency of the first vibration shape mode of the cylinder. The design constraints include the buckling load multiplier (buckling safety factor) above 1.5 and Von Mises stress below 100 MPa. In this article, first, according to the permissible limits of the design variables, a design of experiment (DOE) and then a sensitivity analysis was carried out to check the sensitivity of the objective functions and constraints to the design variables. After numerically solving the output values with the help of Ansys software and preparing the response surface, the optimal design point has been identified with the help of the two objectives optimization Genetic algorithm. Then, with the numerical simulation of the optimal point, the accuracy of the values obtained from the response surface method was checked and their accuracy was confirmed. The results show that at the selected design point, Von Mises stress becomes less than its allowed value, i.e. 100 MPa, and also the buckling load factor is more than twice its minimum allowed value. However, this point has the smallest distance from the origin and the optimum point has been chosen as the knee point
Structure
mohammadreza alijani nargesi; hasan haddadpour; Saeed Shakhesi
Abstract
One of the key issues in the operations of on orbit servicing to unmanned satellites is to provide a safe and reliable docking process. This paper investigates the dynamic behavior of a flexible probe in the central docking mechanism of unmanned satellites. For simulating the impact phenomenon, ...
Read More
One of the key issues in the operations of on orbit servicing to unmanned satellites is to provide a safe and reliable docking process. This paper investigates the dynamic behavior of a flexible probe in the central docking mechanism of unmanned satellites. For simulating the impact phenomenon, a dynamic analysis software (MSC. Adams) has been applied and a three-dimensional model has created based on the assumption of a flexible clamped beam as a shock absorber. The results are in good agreement with similar theoretical and experimental results. additionally, it is possible to consider the parameters such as the type of connection between the beam and the concentrated mass, angular and translational velocity of chaser and target satellites, in order to determine the optimum condition to perform a successful docking operation. The results of this study indicate that the use of a spherical joint for the ball attached to the probe, significantly reduces the maximum value of impact force. Also, the rotation of the sphere leads to less change in the linear and angular velocity of the target satellite and increases the probability of successful mating of the satellites. On the other hand, the movement of the conical area relative to the target satellite reduces the maximum impact force and shock resulting on the satellites structure. As a result, the chance of successful docking increases.
Structure
Yaser Vahidshad; Faegheh Soltanmohammad
Abstract
Many factors affect the quality of brazing process, including temperature, time, clearance, surface roughness and alloy elements. Actually, they influence on the formation of intermetallic compounds in brazed joints. Since intermetallic compounds are brittle, they considerably degrade the mechanical ...
Read More
Many factors affect the quality of brazing process, including temperature, time, clearance, surface roughness and alloy elements. Actually, they influence on the formation of intermetallic compounds in brazed joints. Since intermetallic compounds are brittle, they considerably degrade the mechanical properties of joints. In this study, the mechanical strength and microstructural characterization of AISI 316 brazed joints with BNi2 filler metal in different temperature has been investigated. Brazing temperatures changed from 1050 °C, 1100 °C, 1150 °C and 1200 °C for a holding time of 60 min then, the influence of this variable on the brazing strength were examined. Tensile test samples were evaluated at room temperature and metallography samples and fractured tensile sample scanned by a microscope. The results showed that the higher brazing temperature leads to diffusion of boron element into base metal and less volume formation of intermetallic compound phase in the brazing joint and consequently more tensile strength
Control dynamics
Ehsan Maani miandoab; Ehsan Zabihian; Hossein Najafi
Abstract
In all types of satellites, communication systems are utilized for data transmission between satellite and ground stations. pointing the communication antennas to the ground is necessary for the correct mission transmission information. The vibration of the satellite antenna leads to deforming antenna ...
Read More
In all types of satellites, communication systems are utilized for data transmission between satellite and ground stations. pointing the communication antennas to the ground is necessary for the correct mission transmission information. The vibration of the satellite antenna leads to deforming antenna pattern, creating noise and reducing connection quality. Moreover, working the attitude control actuators near the antenna's natural frequency leads to its resonance and large amplitude vibration in the antenna and satellite structure. Thus it is necessary to identify the satellite antenna dynamic behavior as natural frequency and damping ratio. In this paper, the satellite antenna is intended as a smart beam, based on the free vibration of clamped-free beam shape of satellite antenna and sensing its vibration by the piezoelectric sensor, its dynamic characteristic as damping and frequency is identified and verified by comparing the results with experimental ones. The considered mathematical model is very accurate and this model can be used to determine the dynamic behavior of the antenna in different satellite secondary structures.
Structure
Arvin Taghizadeh Tabrizi; Hossein Aghajani; Farhad Farhang Laleh
Abstract
Although regarding low density and high ratio of strength to weight of titanium, the application of this metal is restricted in space industry due to its low surface properties including low wear resistance which could lead to the cold weld. For improving this property of titanium, applying protective ...
Read More
Although regarding low density and high ratio of strength to weight of titanium, the application of this metal is restricted in space industry due to its low surface properties including low wear resistance which could lead to the cold weld. For improving this property of titanium, applying protective coatings is effective. The physical parameters of wear resistance, adhesion and surface microhardness are impressive and could avoid occurance of cold weld. Therefore, in the present study, by applying plasma nitriding on chromium layer on titanium used in space structures, its tribological behavior (wear resistance, adhesion and surface microhardness) has been investigated. The results confirmed the formation of nitride chromium thin layer on titanium substrate due to the applying plasma nitriding on the chromium layer , which increasing the surface microhardness up to 1109 HV and improving the wear resistance and adhesion subsequently. The coefficient of friction is also decreased to 0.16,which can well prevent the occurrence of cold weld
Structure
mohamad bagher bahrami
Abstract
One of the most critical design points in satellites is to achieve the minimum mass (weight) by meeting all the requirements and constraints (strength, location and vibration). In this regard, the structure can play a very important role because the structural designer has more freedom of action in determining ...
Read More
One of the most critical design points in satellites is to achieve the minimum mass (weight) by meeting all the requirements and constraints (strength, location and vibration). In this regard, the structure can play a very important role because the structural designer has more freedom of action in determining the design of the structure compared to other subsystems. In the present study, the process of designing the structure of a small satellite with the aim of achieving the lowest possible weight and maintaining the prevailing requirements such as vibration constraints hasbeen investigated. The process used to achieve the above goal is to change the geometric dimensions of the structure. Satellite modeling steps with all subsystems have been performed in SolidWorks software and modal, quasi-static and random vibrations analyzes have been performed in ansys software. Also, By using the ability to optimize the genetic algorithm in this software, the geometric parameters of the structure such as the thickness of the amplifiers have been obtained in such a way that the structure has reached the lowest possible weight and meet the prevailing conditions for vibration constraints, strength and random vibrations. The results show that by choosing the right thickness of amplifiers, the weight and frequency of the first satellite mode can be reduced significantly, and at the same time, the optimal final structure can satisfy all the constraints applied by the launcher and provide sufficient strength and rigidity
Structure
S. Javid Mirahmadi; Mohsen Hamedi; Maedeh sadat Zoei
Abstract
Ti-6Al-4V is one of the most common materials in the aerospace industry. For example, satellite fuel tanks are made of this alloy. Among manufacturing processes, forming processes is one of the most widely used areas in the manufacture of Ti-6Al-4V components. Due to the importance of determining the ...
Read More
Ti-6Al-4V is one of the most common materials in the aerospace industry. For example, satellite fuel tanks are made of this alloy. Among manufacturing processes, forming processes is one of the most widely used areas in the manufacture of Ti-6Al-4V components. Due to the importance of determining the allowable deformation limit in the successful design of the Ti-6Al-4V forming process, in this paper, the amount of critical damage was studied. For this purpose, parts with double-cone geometry with grooves on the maximum diameter with two initial microstructure, lamellar and equiaxed, were fabricated and subjected to hot compression testing. The results showed that the initial equiaxed microstructure provides good accumulated damage tolerance. Up to 2.38, 2.67, and 5.89 accumulated damage values, according to Cockcroft-Latham, Brozo, and McClintock criteria, respectively, no crack was observed on the samples. However, with an initial lamellar microstructure, the damage tolerance was significantly reduced. The critical damage value based on Cockcroft-Latham, Brozzo and McClintock criteria was 1.05±0.02, 1.03±0.02, and 2.56±0.05, respectively
Structure
Maedeh sadat Zoei; hadi gorabi; mohammadreza asharf khorasani; saeed asghari; S. Javid Mirahmadi
Abstract
Space systems in Low Earth Orbit (LEO) expose to the destructive parameter of atomic oxygen. In long-term missions, the rate of degradation of the material resulting from the reaction with atomic oxygen is significant and reduces the performance of the structure. Due to the harmful effects of atomic ...
Read More
Space systems in Low Earth Orbit (LEO) expose to the destructive parameter of atomic oxygen. In long-term missions, the rate of degradation of the material resulting from the reaction with atomic oxygen is significant and reduces the performance of the structure. Due to the harmful effects of atomic oxygen on materials, the choice of atomic oxygen resistant materials or the use of durable surface coatings is very common. In this study, the corrosion resistance of atomic oxygen of an interconnector part of a solar cell has studied by applying a silicone base coating. In order to investigate the corrosion behavior of atomic oxygen, ground test method with equivalent conditions of LEO orbit has used by DC plasma equipment. Initially, the parameters of the atomic oxygen corrosion ground test determined under the equivalent conditions of the LEO orbit. The results of atomic oxygen application in this study showed that the amount of atomic oxygen erosion yield of silicon coating is significantly lower than the amount of atomic oxygen erosion yield of silver substrate. The study of the coating surface after applying atomic oxygen by SEM images led to the determination of the optimal coating thickness. EDX results showed that after applying atomic oxygen, no significant change in the chemical composition of the coating has achieved
