Pub Date : 2016-04-03DOI: 10.4172/2168-9792.1000163
Anand Ss, Mathiyazaghan R
Unmanned Aerial Vehicles have gained well known attention in recent years for a numerous applications such as military, civilian surveillance operations as well as search and rescue missions. The UAVs are not controlled by professional pilots and users have less aviation experience. Therefore it seems to be purposeful to simplify the process of aircraft controlling. The objective is to design, fabricate and implement an unmanned aerial vehicle which is controlled by means of voice recognition. In the proposed system, voice commands are given to the quadcopter to control it autonomously. This system is navigated by the voice input. The control system responds to the voice input by voice recognition process and corresponding algorithms make the motors to run at specified speeds which controls the direction of the quadcopter.
{"title":"Design and Fabrication of Voice Controlled Unmanned Aerial Vehicle","authors":"Anand Ss, Mathiyazaghan R","doi":"10.4172/2168-9792.1000163","DOIUrl":"https://doi.org/10.4172/2168-9792.1000163","url":null,"abstract":"Unmanned Aerial Vehicles have gained well known attention in recent years for a numerous applications such as military, civilian surveillance operations as well as search and rescue missions. The UAVs are not controlled by professional pilots and users have less aviation experience. Therefore it seems to be purposeful to simplify the process of aircraft controlling. The objective is to design, fabricate and implement an unmanned aerial vehicle which is controlled by means of voice recognition. In the proposed system, voice commands are given to the quadcopter to control it autonomously. This system is navigated by the voice input. The control system responds to the voice input by voice recognition process and corresponding algorithms make the motors to run at specified speeds which controls the direction of the quadcopter.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-04-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116854855","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 : 2016-04-03DOI: 10.4172/2168-9792.1000165
H. Xuan, S. Cheng, L. Fang
High noise level of sonic boom is one of the most important reasons that the supersonic transport can’t be applied to civil aviation broadly. Sonic boom is a complicated problem relating to aircraft configuration design, aerodynamics, acoustics and so on. The traditional sonic boom minimization theory is an inverse design method with single object, which makes it difficult to be applied in multi-objective optimization, effectively. For the low sonic boom configuration optimization, the sonic boom noise level prediction method based on supersonic linear theory was developed. The sonic boom level of a basic configuration of supersonic business jet was computed and the cause of formation of sonic boom was analyzed, based on which the fuse and wing plane wais optimized to decrease the noise level of sonic boom. Compared with the basic configuration, the sonic boom level of optimized configuration decreased distinctively, with the overpressure decreasing 41% and the A-weighted noise level decreasing 7.55 decibel. The aerodynamic characteristics of optimized configuration were computed. Compared with the basic configuration, the drag decreased obviously at the cruise condition without moment change.
{"title":"The Research of Supersonic Aircraft Low Sonic Boom Configuration Design and Optimizations","authors":"H. Xuan, S. Cheng, L. Fang","doi":"10.4172/2168-9792.1000165","DOIUrl":"https://doi.org/10.4172/2168-9792.1000165","url":null,"abstract":"High noise level of sonic boom is one of the most important reasons that the supersonic transport can’t be applied to civil aviation broadly. Sonic boom is a complicated problem relating to aircraft configuration design, aerodynamics, acoustics and so on. The traditional sonic boom minimization theory is an inverse design method with single object, which makes it difficult to be applied in multi-objective optimization, effectively. For the low sonic boom configuration optimization, the sonic boom noise level prediction method based on supersonic linear theory was developed. The sonic boom level of a basic configuration of supersonic business jet was computed and the cause of formation of sonic boom was analyzed, based on which the fuse and wing plane wais optimized to decrease the noise level of sonic boom. Compared with the basic configuration, the sonic boom level of optimized configuration decreased distinctively, with the overpressure decreasing 41% and the A-weighted noise level decreasing 7.55 decibel. The aerodynamic characteristics of optimized configuration were computed. Compared with the basic configuration, the drag decreased obviously at the cruise condition without moment change.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-04-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130125143","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 : 2016-03-19DOI: 10.4172/2168-9792.1000162
W. Harasani
This paper presents a conceptual design decision making approach through operational modeling through the eyes of the airline. It put more emphasis on the engine maintenance, repair and overhaul, since engine maintenance is about 13% of the total cash cost. A key element of the research is a simulation program through Operation Simulation Modelling OSM, that has been built by the others to create an operational modelling environment to see the impact of different design technologies, or concepts, or compare different type of engines operation on a real environment through the eyes of the customer (i.e. the airline engineers and mechanics). The Rolls Royce engine (RB211-524D4) for a specific airline has been chosen to be the case study and validate the code in case of man-hours. Finally, it was found that OSM givens outcome for the baseline maintenance hours, and man hours needed give an difference 2.7% and 0.8% respectively.
{"title":"Operational Simulation Modeling in Legacy Engine Maintenance","authors":"W. Harasani","doi":"10.4172/2168-9792.1000162","DOIUrl":"https://doi.org/10.4172/2168-9792.1000162","url":null,"abstract":"This paper presents a conceptual design decision making approach through operational modeling through the eyes of the airline. It put more emphasis on the engine maintenance, repair and overhaul, since engine maintenance is about 13% of the total cash cost. A key element of the research is a simulation program through Operation Simulation Modelling OSM, that has been built by the others to create an operational modelling environment to see the impact of different design technologies, or concepts, or compare different type of engines operation on a real environment through the eyes of the customer (i.e. the airline engineers and mechanics). The Rolls Royce engine (RB211-524D4) for a specific airline has been chosen to be the case study and validate the code in case of man-hours. Finally, it was found that OSM givens outcome for the baseline maintenance hours, and man hours needed give an difference 2.7% and 0.8% respectively.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-03-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125274499","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 : 2016-02-29DOI: 10.4172/2168-9792.1000161
M. Alsarheed, A. Sedaghat
An aileron, part of the trailing edge of a fixed-wing airplane, is used to control aircraft’s movement around its longitudinal axis (roll). Ailerons have significant impacts on airfoil surface pressure and its lift and drag coefficients. Both panel and finite volume methods were used on a NACA 2412 airfoil with a 20% aileron in a cross flow. The aerodynamic performance of ailerons alone, in a biplane configuration, and in the ground effects has been computationally investigated using both the panel and the finite volume methods. Several parameters were analyzed including the effects of the attack angle of the airfoil, aileron deflection angle, the ride height from the ground, and the characteristics of biplanes. Results of both computational methods are presented and discussed for the aforementioned configurations of NACA 2412 airfoil with aileron.
{"title":"Computational Study of Ailerons in Cross Flows Ground Effects andBiplanes Configurations","authors":"M. Alsarheed, A. Sedaghat","doi":"10.4172/2168-9792.1000161","DOIUrl":"https://doi.org/10.4172/2168-9792.1000161","url":null,"abstract":"An aileron, part of the trailing edge of a fixed-wing airplane, is used to control aircraft’s movement around its longitudinal axis (roll). Ailerons have significant impacts on airfoil surface pressure and its lift and drag coefficients. Both panel and finite volume methods were used on a NACA 2412 airfoil with a 20% aileron in a cross flow. The aerodynamic performance of ailerons alone, in a biplane configuration, and in the ground effects has been computationally investigated using both the panel and the finite volume methods. Several parameters were analyzed including the effects of the attack angle of the airfoil, aileron deflection angle, the ride height from the ground, and the characteristics of biplanes. Results of both computational methods are presented and discussed for the aforementioned configurations of NACA 2412 airfoil with aileron.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-02-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132781804","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 : 2016-02-25DOI: 10.4172/2168-9792.1000160
Reddy Mvr
The aerodynamic characteristics of a helicopter rotor blade are highly dependent on the wake induced flow. The rotor blades, which are rotating wings, shed vortices which trail in helical path along the axis of rotation forming a wake. The velocity field induced by the vortex system influences the blade loading. The free wake model analysis is computationally intensive and numerically unstable in very low speed applications. For the aerodynamic analysis of a hovering rotor, Miller and Reddy have proposed simple wake models in which the spiral vortex wake is replaced by a system of vortex rings or vortex line elements in conjunction with lifting line theory to overcome some of the problems encountered in free-wake models. In the Proposed model of the rotor, the same lifting line model of the rotor is retained, but a further simplification of the vortex wake is proposed. This method requires relatively very small computing time compared to the above models, but without necessarily sacrificing the accuracy in estimating the aerodynamic blade loading.
{"title":"Aerodynamic Load Estimation of Helicopter Rotor in Hovering Flight","authors":"Reddy Mvr","doi":"10.4172/2168-9792.1000160","DOIUrl":"https://doi.org/10.4172/2168-9792.1000160","url":null,"abstract":"The aerodynamic characteristics of a helicopter rotor blade are highly dependent on the wake induced flow. The rotor blades, which are rotating wings, shed vortices which trail in helical path along the axis of rotation forming a wake. The velocity field induced by the vortex system influences the blade loading. The free wake model analysis is computationally intensive and numerically unstable in very low speed applications. For the aerodynamic analysis of a hovering rotor, Miller and Reddy have proposed simple wake models in which the spiral vortex wake is replaced by a system of vortex rings or vortex line elements in conjunction with lifting line theory to overcome some of the problems encountered in free-wake models. In the Proposed model of the rotor, the same lifting line model of the rotor is retained, but a further simplification of the vortex wake is proposed. This method requires relatively very small computing time compared to the above models, but without necessarily sacrificing the accuracy in estimating the aerodynamic blade loading.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"128 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121648529","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 : 2016-02-25DOI: 10.4172/2168-9792.1000158
Lamar Je
{"title":"Commentary on Aeronautics and Aerospace Engineering","authors":"Lamar Je","doi":"10.4172/2168-9792.1000158","DOIUrl":"https://doi.org/10.4172/2168-9792.1000158","url":null,"abstract":"","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-02-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133933530","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 : 2016-02-15DOI: 10.4172/2168-9792.1000159
R. Ghadawala, B. Singh, P. Kantroo
Earth Orbit is a limited resource and its sustainability is at stake. Various commercial solutions are recommended to handle the trash in the space. Studies are reflecting that at this pace especially when the global space community participation is rapidly increasing, incidents of collisions are highly possible and in case of damage for commercial space application based operations. This new era of a ‘space race’ has embarked a few conclusions raising not only technological concerns, but also a host of economic, legal/regulatory, and corporate responsibilities associated with debris remediation and mitigation. The intent behind this paper is to identify what elements would be necessary for an ADR concept to be considered both technical and non-technical and how to address them. Lastly the gravity of the situation of debris removal is also assessed through a comparative analysis of various case study methods across the global.
{"title":"Commercial Aspects of Active Debris Removal: Technical and LegalChallenges","authors":"R. Ghadawala, B. Singh, P. Kantroo","doi":"10.4172/2168-9792.1000159","DOIUrl":"https://doi.org/10.4172/2168-9792.1000159","url":null,"abstract":"Earth Orbit is a limited resource and its sustainability is at stake. Various commercial solutions are recommended to handle the trash in the space. Studies are reflecting that at this pace especially when the global space community participation is rapidly increasing, incidents of collisions are highly possible and in case of damage for commercial space application based operations. This new era of a ‘space race’ has embarked a few conclusions raising not only technological concerns, but also a host of economic, legal/regulatory, and corporate responsibilities associated with debris remediation and mitigation. The intent behind this paper is to identify what elements would be necessary for an ADR concept to be considered both technical and non-technical and how to address them. Lastly the gravity of the situation of debris removal is also assessed through a comparative analysis of various case study methods across the global.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"263 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-02-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125068953","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 : 2016-01-22DOI: 10.4172/2168-9792.1000155
W. Harasani
With a help of a local airline, the aim of this paper is to construct a cost efficiency charts, for three given aircraft to operate in three independent sectors. These chart are generated by an Excel code, the efficiency charts would be useful for airlines and fleet planners in their decision making process
{"title":"Generating Cost Efficiency Charts: A Comparison between B737, A319and A321","authors":"W. Harasani","doi":"10.4172/2168-9792.1000155","DOIUrl":"https://doi.org/10.4172/2168-9792.1000155","url":null,"abstract":"With a help of a local airline, the aim of this paper is to construct a cost efficiency charts, for three given aircraft to operate in three independent sectors. These chart are generated by an Excel code, the efficiency charts would be useful for airlines and fleet planners in their decision making process","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"81 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-01-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126083504","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 : 2016-01-22DOI: 10.4172/2168-9792.1000157
R. Retheesh, Boni Samuel, P. Radhakrishnan, Nampoori Vpn, A. Mujeeb
Surface roughness is a principal measure of product quality of the materials used for sophisticated applications. The present paper reports an experimental investigation of various parameters related to the surface roughness of the materials used for the aerospace applications by an inexpensive non-invasive technique known as speckle photography. Conventional non-destructive testing techniques such as X-Ray imaging, ultrasound scanning, microwave testing etc, have certain limitations on testing the surface characteristics of low modulus aerospace vehicle components. This paper explains characterization of surface roughness by analyzing certain roughness parameters such as intensity distribution, size distribution and contrast ratio of different low modulus materials used in aerospace applications. The optical setup employed for the work is simple and uses an inexpensive digital camera for grabbing the specimens under different static conditions
{"title":"Analysis of Various Surface Roughness Parameters of Low ModulusAerospace Materials Using Speckle Photography","authors":"R. Retheesh, Boni Samuel, P. Radhakrishnan, Nampoori Vpn, A. Mujeeb","doi":"10.4172/2168-9792.1000157","DOIUrl":"https://doi.org/10.4172/2168-9792.1000157","url":null,"abstract":"Surface roughness is a principal measure of product quality of the materials used for sophisticated applications. The present paper reports an experimental investigation of various parameters related to the surface roughness of the materials used for the aerospace applications by an inexpensive non-invasive technique known as speckle photography. Conventional non-destructive testing techniques such as X-Ray imaging, ultrasound scanning, microwave testing etc, have certain limitations on testing the surface characteristics of low modulus aerospace vehicle components. This paper explains characterization of surface roughness by analyzing certain roughness parameters such as intensity distribution, size distribution and contrast ratio of different low modulus materials used in aerospace applications. The optical setup employed for the work is simple and uses an inexpensive digital camera for grabbing the specimens under different static conditions","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-01-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120913806","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 : 2016-01-22DOI: 10.4172/2168-9792.1000156
M. Rossett
A system was developed to launch unmanned aerial vehicles (UAV) near cruising altitude by utilizing a kite based system. A kite was flown in the sky asking as an anchor in the sky. A UAV was brought up the tether and released. The tension, tether angles, and other flight characteristics of the kite were simulated and field tested. This data was used to determine the feasibility of the overall project.
{"title":"Kite Sky Anchor Analysis for Drone Launching System","authors":"M. Rossett","doi":"10.4172/2168-9792.1000156","DOIUrl":"https://doi.org/10.4172/2168-9792.1000156","url":null,"abstract":"A system was developed to launch unmanned aerial vehicles (UAV) near cruising altitude by utilizing a kite based system. A kite was flown in the sky asking as an anchor in the sky. A UAV was brought up the tether and released. The tension, tether angles, and other flight characteristics of the kite were simulated and field tested. This data was used to determine the feasibility of the overall project.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"47 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-01-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126105859","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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