Pub Date : 2016-09-03DOI: 10.4172/2168-9792.1000172
T. DeFelice, D. Axisa
This paper introduces an engineering approach to develop autonomous unmanned aircraft systems technology for integration in future weather modification (cloud seeding) programs with the goal to improve operational efficiency and evaluation accuracy. It builds upon the process already established in a previous paper by Axisa and DeFelice who constructed a framework underlying the development of new technologies for use in cloud seeding activities, identifying their potential benefits and limitations and providing initial guidance
{"title":"Developing the Framework for Integrating Autonomous Unmanned Aircraft Systems into Cloud Seeding Activities","authors":"T. DeFelice, D. Axisa","doi":"10.4172/2168-9792.1000172","DOIUrl":"https://doi.org/10.4172/2168-9792.1000172","url":null,"abstract":"This paper introduces an engineering approach to develop autonomous unmanned aircraft systems technology for integration in future weather modification (cloud seeding) programs with the goal to improve operational efficiency and evaluation accuracy. It builds upon the process already established in a previous paper by Axisa and DeFelice who constructed a framework underlying the development of new technologies for use in cloud seeding activities, identifying their potential benefits and limitations and providing initial guidance","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130139464","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}
Pub Date : 2016-08-02DOI: 10.4172/2168-9792.C1.014
Zhongping Lee, S. Shang
S disk depth (ZSD), a measurement of the maximum viewable depth of a white or black-and-white disk with a diameter about 30 cm when lowered into water, holds the longest (from at least 1880’s) records of water transparency. This ZSD data record is found not only important for the study of climate change, but also useful for seagoers. However, there has been no standard ZSD product from all satellite ocean color missions. This may in part lie in that there was no robust algorithm to estimate ZSD of global oceans from ocean color measurements, although numerous empirical relationships were developed for various locations. In addition, the classical visibility theory suggests that ZSD is proportional to the inverse of (K+c), with K the diffuse attenuation coefficient and c the beam attenuation coefficient. Because c is significantly (2-5 or more) larger than K and that c could not be analytically retrieved from ocean color remote sensing, it has been perceived that there could be no analytical or semi-analytical algorithm for ZSD from ocean color measurements. A recent study found that this classical interpretation of ZSD is flawed, and a new theoretical relationship is developed for ZSD. With concurrent measurements of ZSD and remote-sensing reflectance (Rrs) of wide range of aquatic environments, the performance of the estimation of ZSD with Rrs as inputs by the classical and the new approaches is evaluated. The excellent results of the new relationship indicate a robust system to produce global ZSD from satellite ocean color measurements.
{"title":"Secchi disk depth: Evaluation of an algorithm based on new visibility theory","authors":"Zhongping Lee, S. Shang","doi":"10.4172/2168-9792.C1.014","DOIUrl":"https://doi.org/10.4172/2168-9792.C1.014","url":null,"abstract":"S disk depth (ZSD), a measurement of the maximum viewable depth of a white or black-and-white disk with a diameter about 30 cm when lowered into water, holds the longest (from at least 1880’s) records of water transparency. This ZSD data record is found not only important for the study of climate change, but also useful for seagoers. However, there has been no standard ZSD product from all satellite ocean color missions. This may in part lie in that there was no robust algorithm to estimate ZSD of global oceans from ocean color measurements, although numerous empirical relationships were developed for various locations. In addition, the classical visibility theory suggests that ZSD is proportional to the inverse of (K+c), with K the diffuse attenuation coefficient and c the beam attenuation coefficient. Because c is significantly (2-5 or more) larger than K and that c could not be analytically retrieved from ocean color remote sensing, it has been perceived that there could be no analytical or semi-analytical algorithm for ZSD from ocean color measurements. A recent study found that this classical interpretation of ZSD is flawed, and a new theoretical relationship is developed for ZSD. With concurrent measurements of ZSD and remote-sensing reflectance (Rrs) of wide range of aquatic environments, the performance of the estimation of ZSD with Rrs as inputs by the classical and the new approaches is evaluated. The excellent results of the new relationship indicate a robust system to produce global ZSD from satellite ocean color measurements.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115501374","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}
Pub Date : 2016-06-30DOI: 10.4172/2168-9792.1000164
K. Kis, P. Taylor, G. Wittmann
We computed magnetic field gradients at satellite altitude, over Europe with emphasis on the Kursk Magnetic Anomaly (KMA). They were calculated using the CHAMP satellite total magnetic anomalies. Our computations were done to determine how the magnetic field observations data from the new ESA/Swarm satellites could be utilized to determine the structure of the magnetization of the Earth’s crust, especially in the region of the KMA. Ten years of CHAMP data were used to simulate the Swarm data. An initial east magnetic anomaly gradient map of Europe was computed and subsequently the North, East and Vertical magnetic gradients for the KMA region were calculated. The vertical gradient of the KMA was also determined using Hilbert transforms. Inversion of the total KMA was derived using Simplex and Simulated Annealing algorithms. The depths of the upper and lower boundaries are calculated downward from the 324 km elevation of the satellite. Our resulting inversion depth model is a horizontal quadrangle. The maximum errors are determined by the model parameter errors.
{"title":"Determination of the Earths Magnetic Field Gradients from SatellitesMeasurements and Their Inversion over the Kursk Magnetic Anomaly","authors":"K. Kis, P. Taylor, G. Wittmann","doi":"10.4172/2168-9792.1000164","DOIUrl":"https://doi.org/10.4172/2168-9792.1000164","url":null,"abstract":"We computed magnetic field gradients at satellite altitude, over Europe with emphasis on the Kursk Magnetic Anomaly (KMA). They were calculated using the CHAMP satellite total magnetic anomalies. Our computations were done to determine how the magnetic field observations data from the new ESA/Swarm satellites could be utilized to determine the structure of the magnetization of the Earth’s crust, especially in the region of the KMA. Ten years of CHAMP data were used to simulate the Swarm data. An initial east magnetic anomaly gradient map of Europe was computed and subsequently the North, East and Vertical magnetic gradients for the KMA region were calculated. The vertical gradient of the KMA was also determined using Hilbert transforms. Inversion of the total KMA was derived using Simplex and Simulated Annealing algorithms. The depths of the upper and lower boundaries are calculated downward from the 324 km elevation of the satellite. Our resulting inversion depth model is a horizontal quadrangle. The maximum errors are determined by the model parameter errors.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127061247","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}
Pub Date : 2016-06-30DOI: 10.4172/2168-9792.1000171
D. Udayakumar, S. Kannan, Vimal Ch, R. Sriram, C. Ganapathi
The flow over multi-element airfoils has been numerically investigated in ANSYS fluent and has been compare the aerodynamic parameters with the standard NACA airfoils 4412 and 0012. The 2D viscous, transient, pressure model equations together with the k-ω turbulence model were applied to this numerical simulation utilizing the multiblock unstructured grids of sphere of influence type. Numerical results showed that the aerodynamic parameters of multi element airfoils with tail effect are much optimum than the standard NACA airfoils. Also the analysis is made on different flap and slat angles of different conditions and the optimization of multi element airfoils has been performed.
{"title":"Aerodynamic Analysis of Multi Element Airfoil","authors":"D. Udayakumar, S. Kannan, Vimal Ch, R. Sriram, C. Ganapathi","doi":"10.4172/2168-9792.1000171","DOIUrl":"https://doi.org/10.4172/2168-9792.1000171","url":null,"abstract":"The flow over multi-element airfoils has been numerically investigated in ANSYS fluent and has been compare the aerodynamic parameters with the standard NACA airfoils 4412 and 0012. The 2D viscous, transient, pressure model equations together with the k-ω turbulence model were applied to this numerical simulation utilizing the multiblock unstructured grids of sphere of influence type. Numerical results showed that the aerodynamic parameters of multi element airfoils with tail effect are much optimum than the standard NACA airfoils. Also the analysis is made on different flap and slat angles of different conditions and the optimization of multi element airfoils has been performed.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123308509","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}
Pub Date : 2016-06-30DOI: 10.4172/2168-9792.1000170
Pradhani Nl, A. Rajesh, Ganesha Prasad Ms
A computational prediction of combustion is a challenging task due complexity involved in the flow parameters. The design of can-type combustor has been considered for a special purpose using producer gas as fuel to run the turbine blades of a turbocharger. Producer gas used for power generation has zero effect, even though it emits CO2 into the atmosphere. The application has its background in finding an optimal turbocharger for matching the requirements of an IC engine. Non-premixed combustor is taken into account because producer gas having high temperature around 300 K when entering into combustion chamber, thus it is unsafe to operate in the premixed mode to prevent explosion in the air-fuel inlet and also simplifies the design. By changing the inlet air injection angle will affect the combustion parameters like low pressure drop, NOx level, outlet temperature, and wall temperature not to exceed 700 K. A mild steel material has been selected for computational prediction of flow behaviors under typical engine condition in can-type combustor. Thus for the initial consideration, basic design of a can-type combustor without a liner has been modeled. The specifications were met and checked for different combination of primary and secondary air injection duct and a most feasible configuration is obtained. The main aim is to optimize the characteristics of a combustor for a turbocharger test rig, i.e. the combustor designed has to be meet optimum condition, which is prevailing in the producer gas engine (formerly diesel engine).
{"title":"CFD Analysis on Can-Type Combustor and Variation of Air Injection Angle under Typical Engine Condition","authors":"Pradhani Nl, A. Rajesh, Ganesha Prasad Ms","doi":"10.4172/2168-9792.1000170","DOIUrl":"https://doi.org/10.4172/2168-9792.1000170","url":null,"abstract":"A computational prediction of combustion is a challenging task due complexity involved in the flow parameters. The design of can-type combustor has been considered for a special purpose using producer gas as fuel to run the turbine blades of a turbocharger. Producer gas used for power generation has zero effect, even though it emits CO2 into the atmosphere. The application has its background in finding an optimal turbocharger for matching the requirements of an IC engine. Non-premixed combustor is taken into account because producer gas having high temperature around 300 K when entering into combustion chamber, thus it is unsafe to operate in the premixed mode to prevent explosion in the air-fuel inlet and also simplifies the design. By changing the inlet air injection angle will affect the combustion parameters like low pressure drop, NOx level, outlet temperature, and wall temperature not to exceed 700 K. A mild steel material has been selected for computational prediction of flow behaviors under typical engine condition in can-type combustor. Thus for the initial consideration, basic design of a can-type combustor without a liner has been modeled. The specifications were met and checked for different combination of primary and secondary air injection duct and a most feasible configuration is obtained. The main aim is to optimize the characteristics of a combustor for a turbocharger test rig, i.e. the combustor designed has to be meet optimum condition, which is prevailing in the producer gas engine (formerly diesel engine).","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"99 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127260296","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}
Pub Date : 2016-06-12DOI: 10.4172/2168-9792.1000169
H. Wang, L. Guo, P. Wu
China's Space Station will be launched in the year 2018; this space station is China's largest space science experiment and application platform until now. This paper mainly introduces the function composition of payload operation and application system of China’s space station, system architecture, hardware architecture and the new technology we use to implement the payload operation and application ground system of China's space station.
{"title":"Design and Realization of Payload Operation and Application System ofChinas Space Station","authors":"H. Wang, L. Guo, P. Wu","doi":"10.4172/2168-9792.1000169","DOIUrl":"https://doi.org/10.4172/2168-9792.1000169","url":null,"abstract":"China's Space Station will be launched in the year 2018; this space station is China's largest space science experiment and application platform until now. This paper mainly introduces the function composition of payload operation and application system of China’s space station, system architecture, hardware architecture and the new technology we use to implement the payload operation and application ground system of China's space station.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"309 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-06-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124390958","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}
Pub Date : 2016-05-05DOI: 10.4172/2168-9792.C1.013
Marc Skinner
{"title":"Current issues in Space Situational Awareness (SSA) and Space Traffic Management (STM)","authors":"Marc Skinner","doi":"10.4172/2168-9792.C1.013","DOIUrl":"https://doi.org/10.4172/2168-9792.C1.013","url":null,"abstract":"","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-05-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123163766","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}
Pub Date : 2016-05-03DOI: 10.4172/2168-9792.1000168
Eslam E. AbdelGhany, O. Abdellatif, G. Elhariry, E. Khalil
In this research we have obtained the drag and lift coefficients, velocity, pressure and path lines contours using CFD which can also be determined by using wind tunnel experimental test. This process is relatively difficult and surely price more than CFD technique cost for the same problem solution. Thus we have gone through analytical method then it can be validated by experimental testing. A CFD procedure is described for determination aerodynamic characteristics of subsonic NACA653218 airfoil. Firstly, the airfoil model shape, boundary conditions and meshes were all formed in GAMBIT® 2.3.16 as a pre-processor. The second step in a CFD model should be to examine the effect of the mesh size on the solution results. In order to save time take case for a grid with around 100000 cells. The third step is validation of the CFD NACA653218 airfoil shape model by different turbulence models with available experimental data for the same model and operation conditions. The temperature of free stream is 288.2 K, which is the same as the environmental temperature. At the given temperature, the density of the air is ρ=1.225kg/m3, the pressure is 101325 Pa and the viscosity is μ=1.7894×10-5 kg/m s. A segregate, implicit solver is utilized (FLUENT® processor) estimate were prepared for angles of attack variety from -5 to 16°. The Spalart-Allmaras turbulence model is more accurate than standard k – e model, RNG k – e model and standard model k–e models. For lift coefficient, it is found maximum error by Spalart-Allmaras model about 12% lower than other turbulence models. For drag coefficient, it is found maximum error by Spalart-Allmaras model about 25% lower than other turbulence models. For pitching moment coefficient, it is found maximum error by Spalart-Allmaras model about 30% lower than other turbulence models.
{"title":"NACA653218 Airfoil Aerodynamic Properties","authors":"Eslam E. AbdelGhany, O. Abdellatif, G. Elhariry, E. Khalil","doi":"10.4172/2168-9792.1000168","DOIUrl":"https://doi.org/10.4172/2168-9792.1000168","url":null,"abstract":"In this research we have obtained the drag and lift coefficients, velocity, pressure and path lines contours using CFD which can also be determined by using wind tunnel experimental test. This process is relatively difficult and surely price more than CFD technique cost for the same problem solution. Thus we have gone through analytical method then it can be validated by experimental testing. A CFD procedure is described for determination aerodynamic characteristics of subsonic NACA653218 airfoil. Firstly, the airfoil model shape, boundary conditions and meshes were all formed in GAMBIT® 2.3.16 as a pre-processor. The second step in a CFD model should be to examine the effect of the mesh size on the solution results. In order to save time take case for a grid with around 100000 cells. The third step is validation of the CFD NACA653218 airfoil shape model by different turbulence models with available experimental data for the same model and operation conditions. The temperature of free stream is 288.2 K, which is the same as the environmental temperature. At the given temperature, the density of the air is ρ=1.225kg/m3, the pressure is 101325 Pa and the viscosity is μ=1.7894×10-5 kg/m s. A segregate, implicit solver is utilized (FLUENT® processor) estimate were prepared for angles of attack variety from -5 to 16°. The Spalart-Allmaras turbulence model is more accurate than standard k – e model, RNG k – e model and standard model k–e models. For lift coefficient, it is found maximum error by Spalart-Allmaras model about 12% lower than other turbulence models. For drag coefficient, it is found maximum error by Spalart-Allmaras model about 25% lower than other turbulence models. For pitching moment coefficient, it is found maximum error by Spalart-Allmaras model about 30% lower than other turbulence models.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-05-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122569805","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}
Pub Date : 2016-04-28DOI: 10.4172/2168-9792.1000167
Rathina Kumar, J. Jayanthi
Autopilot system is a highly critical avionics system in modern aircraft as it steers the aircraft automatically. The autopilot is a highly complex system driven by a complex logic and is one of the major reasons for the accidents in automated airliner. The autopilot logic consists of the mode-transition logic which in automated mode steers the aircraft based on the aircraft aerodynamics. In the automated mode the correct and efficient working of the modetransition is highly critical; hence a high assurance approach is required to analyze the logic for its functionality and performance. In this paper, we present a semi-formal method based approach to analyze and validate the Mode-Transition Logic (MTL) for an indigenously developed commercial aircraft in the vertical and lateral directions. The MTL is analyzed and validated for its correct, complete, and reliable functionality and operation using Stateflow. The modeled MTL logic is validated for the allowed transitions based on the input combinations against the requirements for functionality and safety. The outcome of the approach shows encouraging results with respect to assurance in functionality, performance and safety in comparison to the conventional manual approach of testing. Similar semiformal based approach can be used to reduce the design effort in the design and development of complex system designs as compared to the manual analysis.
{"title":"Analyze the Mode Transition Logic of Automatic Flight Control System using Semi-Formal Approach","authors":"Rathina Kumar, J. Jayanthi","doi":"10.4172/2168-9792.1000167","DOIUrl":"https://doi.org/10.4172/2168-9792.1000167","url":null,"abstract":"Autopilot system is a highly critical avionics system in modern aircraft as it steers the aircraft automatically. The autopilot is a highly complex system driven by a complex logic and is one of the major reasons for the accidents in automated airliner. The autopilot logic consists of the mode-transition logic which in automated mode steers the aircraft based on the aircraft aerodynamics. In the automated mode the correct and efficient working of the modetransition is highly critical; hence a high assurance approach is required to analyze the logic for its functionality and performance. In this paper, we present a semi-formal method based approach to analyze and validate the Mode-Transition Logic (MTL) for an indigenously developed commercial aircraft in the vertical and lateral directions. The MTL is analyzed and validated for its correct, complete, and reliable functionality and operation using Stateflow. The modeled MTL logic is validated for the allowed transitions based on the input combinations against the requirements for functionality and safety. The outcome of the approach shows encouraging results with respect to assurance in functionality, performance and safety in comparison to the conventional manual approach of testing. Similar semiformal based approach can be used to reduce the design effort in the design and development of complex system designs as compared to the manual analysis.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116951074","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}
Pub Date : 2016-04-28DOI: 10.4172/2168-9792.1000166
B. Dineshkumar, B. ShishiraNayana, D. ShravyaShree
Rocket motors are widely used to generate thrust or impulsive force to impart a desired velocity to flight vehicle to transport its payload to the intended destination. The working principle of Rocket motor is mainly Newton’s 2nd and 3rd laws. Rocket motors are non-air breathing propulsion class i.e., won’t require oxygen from the atmosphere for combustion of the fuel which is stored in the rocket motor. During the operating conditions of the motor hardware, it will be subjected to high temperatures and pressure loads. Structural and thermal design has to carried out for a given input parameters and analysis to be carried out to check the stress levels and temperatures on the hardware. The present paper deals with structural design of motor hardware. The main input parameters considered are the maximum operating pressure and maximum diameter of the Motor hardware. The material properties considered are up to 100°C. Structural analysis and fracture analysis are to carry out after the design of each component of the rocket motor hardware. For design, the motor hardware is considered as a pressure vessel. To compute parameters like thickness some initial assumptions were made. 2D drawing is developed using Auto Cad software and structural analysis is carried out in ANSYS. This software employs finite element analysis techniques to generate the solution. Hence the displacement magnitude, von mises stress and strain developed within the motor is pictorially visualized. Fracture analysis is also carried out on the material.
{"title":"Design and Structural Analysis of Solid Rocket Motor Casing Hardwareused in Aerospace Applications","authors":"B. Dineshkumar, B. ShishiraNayana, D. ShravyaShree","doi":"10.4172/2168-9792.1000166","DOIUrl":"https://doi.org/10.4172/2168-9792.1000166","url":null,"abstract":"Rocket motors are widely used to generate thrust or impulsive force to impart a desired velocity to flight vehicle to transport its payload to the intended destination. The working principle of Rocket motor is mainly Newton’s 2nd and 3rd laws. Rocket motors are non-air breathing propulsion class i.e., won’t require oxygen from the atmosphere for combustion of the fuel which is stored in the rocket motor. During the operating conditions of the motor hardware, it will be subjected to high temperatures and pressure loads. Structural and thermal design has to carried out for a given input parameters and analysis to be carried out to check the stress levels and temperatures on the hardware. The present paper deals with structural design of motor hardware. The main input parameters considered are the maximum operating pressure and maximum diameter of the Motor hardware. The material properties considered are up to 100°C. Structural analysis and fracture analysis are to carry out after the design of each component of the rocket motor hardware. For design, the motor hardware is considered as a pressure vessel. To compute parameters like thickness some initial assumptions were made. 2D drawing is developed using Auto Cad software and structural analysis is carried out in ANSYS. This software employs finite element analysis techniques to generate the solution. Hence the displacement magnitude, von mises stress and strain developed within the motor is pictorially visualized. Fracture analysis is also carried out on the material.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123437356","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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