In the present numerical study, the thermal performance and fluid flow properties have been investigated to show the effect of single-orifice and multiple-orifice impingement of synthetic jets for dimensionless orifice-toplate distance (H/D) of lower than one. Investigations have been done for an actuation frequency of f=500 Hz, 0.10 ≤ H/D ≤ 0.75, and dimensionless pitch ratio of 1.25 ≤ Do/D ≤ 1.75. The results were validated with experimental results from the literature, and a fair agreement was obtained. The results showed that at low nozzle-to-plate spacing, lower target plate temperatures could be obtained. It was observed that with the use of multiple orifices at especially higher Do/D higher heat transfer values are present. The study was performed to add knowledge to the electronics and aviation industries where high temperatures in small cavities occur.
{"title":"Numerical investigation of single and multiple impinging synthetic jets on the flow field and heat transfer at low orifice-to-plate distances","authors":"Eda Ergur, T. Calisir","doi":"10.5937/fme2303273e","DOIUrl":"https://doi.org/10.5937/fme2303273e","url":null,"abstract":"In the present numerical study, the thermal performance and fluid flow properties have been investigated to show the effect of single-orifice and multiple-orifice impingement of synthetic jets for dimensionless orifice-toplate distance (H/D) of lower than one. Investigations have been done for an actuation frequency of f=500 Hz, 0.10 ≤ H/D ≤ 0.75, and dimensionless pitch ratio of 1.25 ≤ Do/D ≤ 1.75. The results were validated with experimental results from the literature, and a fair agreement was obtained. The results showed that at low nozzle-to-plate spacing, lower target plate temperatures could be obtained. It was observed that with the use of multiple orifices at especially higher Do/D higher heat transfer values are present. The study was performed to add knowledge to the electronics and aviation industries where high temperatures in small cavities occur.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":1.6,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88231103","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Aluminum is a light and soft material that is difficult to machine. It is the most produced non-ferrous metal and undergoes extensive machining for the development of a wide range of products. Advances in industry inspire the need to find sustainable ways of machining aluminum and its alloys using conventional machining processes. In the study reported in this paper, two sets of experiments were conducted to investigate the machinability of aluminum 7075 using a plain carbide tool under a dry environment, i.e., no lubrication. In the first set, four rough experiments were conducted where three important machining parameters, i.e., cutting speed CS (115-495 RPM), depth of cut DOC (0.8-1.5 mm), and Feed rate FR (0.08-0.2 mm/rev) have been varied at two levels each to check the behavior of responses or machinability indicators, i.e., surface roughness and tool wear, at machining parameters' highest and lowest values. Based on the results of the first set of experiments, the ranges and levels of parameters have been fixed in the second set for a detailed study of the machinability of aluminum. A total of nine experiments based upon Taguchi's robust design of experiment technique with orthogonal array L9 have been conducted where an additional machining parameter, i.e., machining time MT, has been introduced. The effect of machining parameters on tool wear and surface roughness has been studied in detail, and it is found that the dry machining of aluminum is possible without the early failure of the tool. Dry machining with low values of CS, DOC, FR, and medium MT is desirable for better machinability, i.e., minimum roughness and tool wear, an optimum combination of machining parameter cutting speed-115 RPM, depth of cut-0.8 mm, feed rate-0.12 mm/rev, and machining time-90 seconds. The findings of the present work will assist engineers and researchers in attaining quality, productivity, and sustainability while manufacturing parts and components from aluminum to be used in the automotive, defense, and aerospace sectors.
{"title":"Investigation on machinability of aluminum 7075 under dry environment","authors":"Raymond Magabe, Kapil Gupta","doi":"10.5937/fme2304470m","DOIUrl":"https://doi.org/10.5937/fme2304470m","url":null,"abstract":"Aluminum is a light and soft material that is difficult to machine. It is the most produced non-ferrous metal and undergoes extensive machining for the development of a wide range of products. Advances in industry inspire the need to find sustainable ways of machining aluminum and its alloys using conventional machining processes. In the study reported in this paper, two sets of experiments were conducted to investigate the machinability of aluminum 7075 using a plain carbide tool under a dry environment, i.e., no lubrication. In the first set, four rough experiments were conducted where three important machining parameters, i.e., cutting speed CS (115-495 RPM), depth of cut DOC (0.8-1.5 mm), and Feed rate FR (0.08-0.2 mm/rev) have been varied at two levels each to check the behavior of responses or machinability indicators, i.e., surface roughness and tool wear, at machining parameters' highest and lowest values. Based on the results of the first set of experiments, the ranges and levels of parameters have been fixed in the second set for a detailed study of the machinability of aluminum. A total of nine experiments based upon Taguchi's robust design of experiment technique with orthogonal array L9 have been conducted where an additional machining parameter, i.e., machining time MT, has been introduced. The effect of machining parameters on tool wear and surface roughness has been studied in detail, and it is found that the dry machining of aluminum is possible without the early failure of the tool. Dry machining with low values of CS, DOC, FR, and medium MT is desirable for better machinability, i.e., minimum roughness and tool wear, an optimum combination of machining parameter cutting speed-115 RPM, depth of cut-0.8 mm, feed rate-0.12 mm/rev, and machining time-90 seconds. The findings of the present work will assist engineers and researchers in attaining quality, productivity, and sustainability while manufacturing parts and components from aluminum to be used in the automotive, defense, and aerospace sectors.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135611937","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In the context of the industrialization era, robots are gradually replacing workers in some production stages. There is an irreversible trend toward incorporating image processing techniques in the realm of robot control. In recent years, vision-based techniques have achieved significant milestones. However, most of these techniques require complex setups, specialized cameras, and skilled operators for burden computation. This paper presents an efficient vision-based solution for object detection and grasping in indoor environments. The framework of the system, encompassing geometrical constraints, robot control theories, and the hardware platform, is described. The proposed method, covering calibration to visual estimation, is detailed for handling the detection and grasping task. Our approach's efficiency, feasibility, and applicability are evident from the results of both theoretical simulations and experiments.
{"title":"Using an HSV-based approach for detecting and grasping an object by the industrial manipulator system","authors":"Ha Ngo","doi":"10.5937/fme2304512n","DOIUrl":"https://doi.org/10.5937/fme2304512n","url":null,"abstract":"In the context of the industrialization era, robots are gradually replacing workers in some production stages. There is an irreversible trend toward incorporating image processing techniques in the realm of robot control. In recent years, vision-based techniques have achieved significant milestones. However, most of these techniques require complex setups, specialized cameras, and skilled operators for burden computation. This paper presents an efficient vision-based solution for object detection and grasping in indoor environments. The framework of the system, encompassing geometrical constraints, robot control theories, and the hardware platform, is described. The proposed method, covering calibration to visual estimation, is detailed for handling the detection and grasping task. Our approach's efficiency, feasibility, and applicability are evident from the results of both theoretical simulations and experiments.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135612312","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In the present investigation, the behavior of compressible flow in planar nozzles with throat length is analyzed to determine the flow velocity range and pressure fluctuations in the throat section. The flow field was simulated in 2D computational domains with the ANSYS-Fluent R16.2 code. The RANS model was applied for steady-state flow. The governing equations used are the conservation of mass, momentum, energy, and the ideal gas equation of state. The Sutherland equation was used for the viscosity as a function of temperature. The Spalart-Allmaras turbulence model was used to model the flow turbulence, which was validated with experimental pressure data. In the throat section, for the central region of the flow, as the throat length increases, the flow fluctuates and decelerates. Oblique shock waves are produced, and a shock train region is formed. The flow velocity is transonic and is in the Mach number range of 1 to 1.2, and the static pressure is in the range of 0.37 to 0.52. Therefore, as a result of flow fluctuations, throat length has a significant effect on flow development.
{"title":"Numerical analysis of the shock train evolution in planar nozzles with throat length","authors":"San Tolentino, Jorge Mírez, Simón Caraballo","doi":"10.5937/fme2304595t","DOIUrl":"https://doi.org/10.5937/fme2304595t","url":null,"abstract":"In the present investigation, the behavior of compressible flow in planar nozzles with throat length is analyzed to determine the flow velocity range and pressure fluctuations in the throat section. The flow field was simulated in 2D computational domains with the ANSYS-Fluent R16.2 code. The RANS model was applied for steady-state flow. The governing equations used are the conservation of mass, momentum, energy, and the ideal gas equation of state. The Sutherland equation was used for the viscosity as a function of temperature. The Spalart-Allmaras turbulence model was used to model the flow turbulence, which was validated with experimental pressure data. In the throat section, for the central region of the flow, as the throat length increases, the flow fluctuates and decelerates. Oblique shock waves are produced, and a shock train region is formed. The flow velocity is transonic and is in the Mach number range of 1 to 1.2, and the static pressure is in the range of 0.37 to 0.52. Therefore, as a result of flow fluctuations, throat length has a significant effect on flow development.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135612326","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Actuator fault poses a challenge to the attitude control of spacecraft. Fault-tolerant control (active or passive) is often used to overcome this challenge. Active methods have better performance than passive methods and can manage a broader range of faults. However, their implementation is more difficult. One reason for this difficulty is the critical reaction time. The system may become unrecoverable if the actual reaction time becomes larger than the critical reaction time. This paper proposes using a feedforward neural network to reduce the actual reaction time in the active fault-tolerant control of spacecraft. Besides this improvement, using a feedforward neural network can increase the success percentage. Success percentage is the ratio of successful simulations to the total number of simulations. Simulation results show that for 200 simulations with random faults and initial conditions, the actual reaction time decreases by 73%, and the success percentage increases by 25%. Based on these results, the proposed controller is a good candidate for practical applications.
{"title":"Increasing performance of spacecraft active fault-tolerant control using neural networks","authors":"R. Moradi","doi":"10.5937/fme2301039m","DOIUrl":"https://doi.org/10.5937/fme2301039m","url":null,"abstract":"Actuator fault poses a challenge to the attitude control of spacecraft. Fault-tolerant control (active or passive) is often used to overcome this challenge. Active methods have better performance than passive methods and can manage a broader range of faults. However, their implementation is more difficult. One reason for this difficulty is the critical reaction time. The system may become unrecoverable if the actual reaction time becomes larger than the critical reaction time. This paper proposes using a feedforward neural network to reduce the actual reaction time in the active fault-tolerant control of spacecraft. Besides this improvement, using a feedforward neural network can increase the success percentage. Success percentage is the ratio of successful simulations to the total number of simulations. Simulation results show that for 200 simulations with random faults and initial conditions, the actual reaction time decreases by 73%, and the success percentage increases by 25%. Based on these results, the proposed controller is a good candidate for practical applications.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":1.6,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90868693","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
A numerical investigation of combustion inside single and twin-spark engines was performed to study the effect of a spark plug, positions and spark timings on engine performance. Improvement in engine performance is one of the automotive industry's primary research areas. Consequently, the study's results can be utilised to optimise engine configurations to achieve maximum performance. The investigation was conducted using a finite volume-based open-source software, OpenFOAM, for computational simulations. Simulations were conducted using the XiEngineFOAM solver with a transport equation for modelling flame fronts. The Standard k-e turbulence model was used to predict turbulence parameters. The simulation was conducted for compression and power stroke (crank angle between - 180° and 180°), assuming an even distribution of the air-fuel mixture within the pentroof 4-valve engine cylinder. Simulations were conducted for four cases, including variations in the position and timing of spark plugs in single-spark and twin-spark engines. According to the results of the simulations, the single-spark engine provides the best performance when the spark plug is ignited early and positioned at the cylinder's centre. When placed at an optimal position determined by flame travel and collision, the twin-spark engine gives the best performance at the highest difference between the spark timings of the two spark plugs.
{"title":"Numerical investigation on effect of spark plug configuration on performance in an engine cylinder","authors":"Mehul Bakhshi, Ranjan Pritanshu, Anuj Shukla","doi":"10.5937/fme2304585m","DOIUrl":"https://doi.org/10.5937/fme2304585m","url":null,"abstract":"A numerical investigation of combustion inside single and twin-spark engines was performed to study the effect of a spark plug, positions and spark timings on engine performance. Improvement in engine performance is one of the automotive industry's primary research areas. Consequently, the study's results can be utilised to optimise engine configurations to achieve maximum performance. The investigation was conducted using a finite volume-based open-source software, OpenFOAM, for computational simulations. Simulations were conducted using the XiEngineFOAM solver with a transport equation for modelling flame fronts. The Standard k-e turbulence model was used to predict turbulence parameters. The simulation was conducted for compression and power stroke (crank angle between - 180° and 180°), assuming an even distribution of the air-fuel mixture within the pentroof 4-valve engine cylinder. Simulations were conducted for four cases, including variations in the position and timing of spark plugs in single-spark and twin-spark engines. According to the results of the simulations, the single-spark engine provides the best performance when the spark plug is ignited early and positioned at the cylinder's centre. When placed at an optimal position determined by flame travel and collision, the twin-spark engine gives the best performance at the highest difference between the spark timings of the two spark plugs.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135611035","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Mohamed Abdellatif, Hicham Chibane, Sébastien Dubois, Guio de, Thierry Roland
Design parameters are a crucial element of the product design process. However, design parameter models are often used to solve specific design problems. Generalizing design parameters is an approach to tackle more design problems. This study contributes to resolving certain limitations associated with modeling and representing the design parameters. This paper presents a generalized table of parameters (GTP) for modeling system parameters. This table is linked to a contextual database based on data and information collected from scientific databases, experts' interviews, and Computer-Aided Design (CAD) and Finite Element Modeling (FEM) software analysis and usage. The proposed representative table shows the robustness of integrating multiple sources of information to present a holistic and generalized view of the design system. The quality of the provided data in the table is assessed by applying certain evaluating dimensions and indicators. A case study will be presented on the lattice structure within a specific context in the mechanical field.
{"title":"Method to build a generalized table of parameters in engineering design of technical systems: Lattice structure as a case study","authors":"Mohamed Abdellatif, Hicham Chibane, Sébastien Dubois, Guio de, Thierry Roland","doi":"10.5937/fme2304480a","DOIUrl":"https://doi.org/10.5937/fme2304480a","url":null,"abstract":"Design parameters are a crucial element of the product design process. However, design parameter models are often used to solve specific design problems. Generalizing design parameters is an approach to tackle more design problems. This study contributes to resolving certain limitations associated with modeling and representing the design parameters. This paper presents a generalized table of parameters (GTP) for modeling system parameters. This table is linked to a contextual database based on data and information collected from scientific databases, experts' interviews, and Computer-Aided Design (CAD) and Finite Element Modeling (FEM) software analysis and usage. The proposed representative table shows the robustness of integrating multiple sources of information to present a holistic and generalized view of the design system. The quality of the provided data in the table is assessed by applying certain evaluating dimensions and indicators. A case study will be presented on the lattice structure within a specific context in the mechanical field.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135612327","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Samruddhi Salunke, Suryapratap S. Shinde, Tanmay B. Gholap, D. Sahoo
Comparative Computational Analysis of NATO 5.56 mm, APM2 7.62 mm and AK-47 7.82 mm Bullet Moving at Mach 2.0 in Close Vicinity to the Wall Various rifles require unique bullets. Each bullet has its capability, speed, and impact on the target. In metropolitan warfare, several bullets are shot close to the solid walls. These near walls affect the pressure distribution over the entire asymmetric bullet. The influence of a reflected shock depends on the angle at which it was reflected and the altitude from the ground to the body of the bullet. The current research emphasizes three bullets of varying diameters used in different types of guns. The first bullet is of NATO 5.56 mm, the second is APM2's 7.62 mm bullet, and the third is a 7.82 mm bullet from an AK-47 rifle. For 2-D steady computations, the supersonic speed of Mach 2 is considered to analyze the flowfield across all three bullets. The heights of the bullet are taken considering the height-to-diameter ratios (h/D ratio) from 0.5 to 3.0. The Mach contour drawn from the numerical simulations is used to analyze the flowfield, and aerodynamic coefficients like lift, drag, and moment are also plotted to analyze the ground effects on the projectile. The comparative analysis showed that the trend of shock wave reflections was similar in the bullets till h/D of 1.5. The APM2 bullet experienced maximum drag, followed by AK-47's 7.82 mm and NATO's 5.56 mm bullet. The 7.82 mm bullet experienced maximum lifting force at h/D = 1.0 due to its larger surface area than the other two ammo. The 7.82 mm bullet experienced a nose-up moment, whereas the other two faced a nose-down moment. As the altitude of the bullets from the ground increased, the ground effect appearing on the bullets reduced. The present comparative analysis research shows that it is suitable to fire an AK-47 bullet from h/D greater than 2.0 and the other two bullets from an altitude greater than or equal to h/D of 3.0.
{"title":"Comparative computational analysis of NATO 5.56 mm, APM2 7.62 mm and AK-47 7.82 mm bullet moving at Mach 2.0 in close vicinity to the wall","authors":"Samruddhi Salunke, Suryapratap S. Shinde, Tanmay B. Gholap, D. Sahoo","doi":"10.5937/fme2301081s","DOIUrl":"https://doi.org/10.5937/fme2301081s","url":null,"abstract":"Comparative Computational Analysis of NATO 5.56 mm, APM2 7.62 mm and AK-47 7.82 mm Bullet Moving at Mach 2.0 in Close Vicinity to the Wall Various rifles require unique bullets. Each bullet has its capability, speed, and impact on the target. In metropolitan warfare, several bullets are shot close to the solid walls. These near walls affect the pressure distribution over the entire asymmetric bullet. The influence of a reflected shock depends on the angle at which it was reflected and the altitude from the ground to the body of the bullet. The current research emphasizes three bullets of varying diameters used in different types of guns. The first bullet is of NATO 5.56 mm, the second is APM2's 7.62 mm bullet, and the third is a 7.82 mm bullet from an AK-47 rifle. For 2-D steady computations, the supersonic speed of Mach 2 is considered to analyze the flowfield across all three bullets. The heights of the bullet are taken considering the height-to-diameter ratios (h/D ratio) from 0.5 to 3.0. The Mach contour drawn from the numerical simulations is used to analyze the flowfield, and aerodynamic coefficients like lift, drag, and moment are also plotted to analyze the ground effects on the projectile. The comparative analysis showed that the trend of shock wave reflections was similar in the bullets till h/D of 1.5. The APM2 bullet experienced maximum drag, followed by AK-47's 7.82 mm and NATO's 5.56 mm bullet. The 7.82 mm bullet experienced maximum lifting force at h/D = 1.0 due to its larger surface area than the other two ammo. The 7.82 mm bullet experienced a nose-up moment, whereas the other two faced a nose-down moment. As the altitude of the bullets from the ground increased, the ground effect appearing on the bullets reduced. The present comparative analysis research shows that it is suitable to fire an AK-47 bullet from h/D greater than 2.0 and the other two bullets from an altitude greater than or equal to h/D of 3.0.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":1.6,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76497177","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The paper uses the state feedback technique to provide a control design method for a dynamic linear 6-degree-of-freedom (DOF) model of an Airbreathing Hypersonic Vehicle (AHV). A linear model of AHV with a state space model is developed for the open loop simulation for the level flight with Mach number 5 and a height of 65000 ft (19812 m). The dynamic stability of AHV is analyzed, and state feedback with the pole placement method is implemented for the controller design. The dynamic stability, response, and comparison for the PI and PID controller are presented for the aileron deflection da and rudder deflection dr for the AHV linear model.
采用状态反馈技术，为吸气式高超声速飞行器(AHV)的动态线性6自由度模型提供了一种控制设计方法。针对马赫数为5、高度为65000 ft (19812 m)的水平飞行，建立了一种具有状态空间模型的AHV线性模型，分析了AHV的动态稳定性，采用极点放置法进行状态反馈，设计了AHV控制器。对AHV线性模型的副翼偏转数据和方向舵偏转dr进行了动态稳定性、响应性和PI控制器与PID控制器的比较。
{"title":"Control design using PID with state feedback for Air-breathing Hypersonic Vehicle","authors":"Rites Singh, O. Prakash, S. Joshi","doi":"10.5937/fme2302221s","DOIUrl":"https://doi.org/10.5937/fme2302221s","url":null,"abstract":"The paper uses the state feedback technique to provide a control design method for a dynamic linear 6-degree-of-freedom (DOF) model of an Airbreathing Hypersonic Vehicle (AHV). A linear model of AHV with a state space model is developed for the open loop simulation for the level flight with Mach number 5 and a height of 65000 ft (19812 m). The dynamic stability of AHV is analyzed, and state feedback with the pole placement method is implemented for the controller design. The dynamic stability, response, and comparison for the PI and PID controller are presented for the aileron deflection da and rudder deflection dr for the AHV linear model.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":1.6,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82134743","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
M. Vorkapić, Danijela Živojinović, D. Kreculj, Toni Ivanov, Marija Baltić, A. Simonović
Reverse engineering (RE) aims to design a new replacement part based on the existing part. The goal is to perform a quality reproduction of the physical part with the best possible mechanical characteristics aiming to find optimal solutions regarding the shape and dimensions of the part. The procedure is implemented through a series of steps: creating a digital 3D model, improving model parameters, and realizing products using additive technologies. In this paper, a review and implementation of the fundamental methodologies of RE were carried out on the example of a damaged protective cover with an unknown geometry and material essential for the function of a discontinued device with no technical documentation and spare parts. An optical scanning method, 3D CAD, FEA, and additive manufacturing were used to realize the reproduced part. It was shown that by utilizing RE the lifecycle of the device could be significantly extended with minimal cost.
{"title":"Application of additive technology and reverse engineering in the realization of damaged obsolete parts","authors":"M. Vorkapić, Danijela Živojinović, D. Kreculj, Toni Ivanov, Marija Baltić, A. Simonović","doi":"10.5937/fme2301031v","DOIUrl":"https://doi.org/10.5937/fme2301031v","url":null,"abstract":"Reverse engineering (RE) aims to design a new replacement part based on the existing part. The goal is to perform a quality reproduction of the physical part with the best possible mechanical characteristics aiming to find optimal solutions regarding the shape and dimensions of the part. The procedure is implemented through a series of steps: creating a digital 3D model, improving model parameters, and realizing products using additive technologies. In this paper, a review and implementation of the fundamental methodologies of RE were carried out on the example of a damaged protective cover with an unknown geometry and material essential for the function of a discontinued device with no technical documentation and spare parts. An optical scanning method, 3D CAD, FEA, and additive manufacturing were used to realize the reproduced part. It was shown that by utilizing RE the lifecycle of the device could be significantly extended with minimal cost.","PeriodicalId":12218,"journal":{"name":"FME Transactions","volume":null,"pages":null},"PeriodicalIF":1.6,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81168955","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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