Pub Date : 2013-09-05DOI: 10.4172/2168-9792.1000117
Jokela Jorma, Laapotti Heli, Engblom Janne, Harkke Ville
A number of triage support systems which use Radio Frequency Identification (RFID) have been introduced in recent years. This paper will focus on one mobile triage system; known as “mTriage” The purpose of this paper was to determine the applicability of Radio Frequency communication (RFID) technology and a “mobile triage” system in a simulated multicasualty situation by examining the system’s performance during a military winter exercise in Finland year 2009. This paper focuses on the medical personnel’s opinion on this matter, answering the question: Are the medical personnel who use the system in the field satisfied with its performance. Several field medics were asked to complete a questionnaire. The results of the evaluation were mainly positive. Conclusion was that mobile triage has potential to contribute to the management of mass casualty situations.
{"title":"Experiences of Using a Mobile RFID-Based Triage System","authors":"Jokela Jorma, Laapotti Heli, Engblom Janne, Harkke Ville","doi":"10.4172/2168-9792.1000117","DOIUrl":"https://doi.org/10.4172/2168-9792.1000117","url":null,"abstract":"A number of triage support systems which use Radio Frequency Identification (RFID) have been introduced in recent years. This paper will focus on one mobile triage system; known as “mTriage” The purpose of this paper was to determine the applicability of Radio Frequency communication (RFID) technology and a “mobile triage” system in a simulated multicasualty situation by examining the system’s performance during a military winter exercise in Finland year 2009. This paper focuses on the medical personnel’s opinion on this matter, answering the question: Are the medical personnel who use the system in the field satisfied with its performance. Several field medics were asked to complete a questionnaire. The results of the evaluation were mainly positive. Conclusion was that mobile triage has potential to contribute to the management of mass casualty situations.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"315 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-09-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123124874","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 : 2013-09-04DOI: 10.4172/2168-9792.1000118
A. Abène
A large number of studies of flow visualisations, developed on the upper surface of delta and of gothic wings, and of cones, have been carried out in the wind tunnel of the Valenciennes University’s Aerodynamics and Hydrodynamics Laboratory. These studies have provided a better understanding of the development and of the positioning of vortex structures and have enabled, in particular, the preferential nature of intervortex angles, thereby defined, to be determined. This study of the vortical structures developed on the upper surface of a double-delta wing has revealed that these vortex flows are quite complex and that vortex structures interact with one another. Indeed, it would seem that vortex behaviour has something of a universal nature. An angular conformity between primary and secondary vortex torques and the leading edges of the wing can be expressed by the law of filiation. Intervortex angles evolve with increasing incidence while fragmentation is a function of the apex angle. It would be interesting to recall that this particular spatial organisation of vortex structures, citing the concept of preferential angles, also appears in standard theories on aerodynamics as, for example, in those governing aerodynamic drag. Nevertheless, the link between interior and exterior vortex structures remains to be investigated further. Such studies might even prove the existence of a supplementary torque. In addition, the least resistance of secondary vortices in relation to their fragmentation inevitably calls for experiments to be undertaken with other possible combinations of slender bodies although these areas of research are beyond the scope of this article.
{"title":"Visualisation of Vortex Structures Developed on the Upper Surface of Double-Delta Wings","authors":"A. Abène","doi":"10.4172/2168-9792.1000118","DOIUrl":"https://doi.org/10.4172/2168-9792.1000118","url":null,"abstract":"A large number of studies of flow visualisations, developed on the upper surface of delta and of gothic wings, and of cones, have been carried out in the wind tunnel of the Valenciennes University’s Aerodynamics and Hydrodynamics Laboratory. These studies have provided a better understanding of the development and of the positioning of vortex structures and have enabled, in particular, the preferential nature of intervortex angles, thereby defined, to be determined. This study of the vortical structures developed on the upper surface of a double-delta wing has revealed that these vortex flows are quite complex and that vortex structures interact with one another. Indeed, it would seem that vortex behaviour has something of a universal nature. An angular conformity between primary and secondary vortex torques and the leading edges of the wing can be expressed by the law of filiation. Intervortex angles evolve with increasing incidence while fragmentation is a function of the apex angle. It would be interesting to recall that this particular spatial organisation of vortex structures, citing the concept of preferential angles, also appears in standard theories on aerodynamics as, for example, in those governing aerodynamic drag. Nevertheless, the link between interior and exterior vortex structures remains to be investigated further. Such studies might even prove the existence of a supplementary torque. In addition, the least resistance of secondary vortices in relation to their fragmentation inevitably calls for experiments to be undertaken with other possible combinations of slender bodies although these areas of research are beyond the scope of this article.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"99 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-09-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122414861","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 : 2013-08-21DOI: 10.4172/2168-9792.1000116
Clarence T. Chang, Chi-Ming Lee, J. Herbon, S. Kramer
NASA’s Environmentally Responsible Aviation (ERA) Project is working with industry to develop the fuel flexible combustor technologies for a new generation of low-emissions engine targeted for the 2020 timeframe. These new combustors will reduce Nitrogen Oxide (NOx) emissions to half of current state-of-the-art (SOA) combustors, while simultaneously reducing noise and fuel burn. The purpose of the low NOx fuel-flexible combustor research is to advance the Technology Readiness Level (TRL) and Integration Readiness Level (IRL) of a low NOx, fuel flexible combustor to the point where it can be integrated in the next generation of aircraft. To reduce project risk and optimize research benefit NASA chose to found two Phase 1 contracts. The first Phase 1 contracts went to engine manufactures and were awarded to: General Electric Company, and Pratt & Whitney Company. The second Phase 1 contracts went to fuel injector manufactures Goodrich Corporation, Parker Hannifin Corporation, and Woodward Fuel System Technology. In 2012, two sector combustors were tested at NASA’s ASCR. The results indicated 75% NOx emission reduction below the 2004 CAEP/6 regulation level.
NASA的环境责任航空(ERA)项目正在与工业界合作，为2020年的新一代低排放发动机开发燃料柔性燃烧室技术。这些新型燃烧器将把氮氧化物(NOx)排放量减少到目前最先进(SOA)燃烧器的一半，同时降低噪音和燃料消耗。低氮氧化物燃料柔性燃烧器研究的目的是提高低氮氧化物燃料柔性燃烧器的技术准备水平(TRL)和集成准备水平(IRL)，使其能够集成到下一代飞机上。为了降低项目风险和优化研究效益，NASA选择了两份第一阶段合同。第一阶段合同被授予发动机制造商，并被授予:通用电气公司和普惠公司。第二阶段第一阶段合同授予了燃油喷射器制造商Goodrich Corporation, Parker Hannifin Corporation和Woodward fuel System Technology。2012年，NASA的ASCR对两个扇形燃烧器进行了测试。结果表明，NOx排放量比2004年CAEP/6标准降低75%。
{"title":"NASA Environmentally Responsible Aviation Project Develops Next-Generation Low-Emissions Combustor Technologies (Phase I)","authors":"Clarence T. Chang, Chi-Ming Lee, J. Herbon, S. Kramer","doi":"10.4172/2168-9792.1000116","DOIUrl":"https://doi.org/10.4172/2168-9792.1000116","url":null,"abstract":"NASA’s Environmentally Responsible Aviation (ERA) Project is working with industry to develop the fuel flexible combustor technologies for a new generation of low-emissions engine targeted for the 2020 timeframe. These new combustors will reduce Nitrogen Oxide (NOx) emissions to half of current state-of-the-art (SOA) combustors, while simultaneously reducing noise and fuel burn. The purpose of the low NOx fuel-flexible combustor research is to advance the Technology Readiness Level (TRL) and Integration Readiness Level (IRL) of a low NOx, fuel flexible combustor to the point where it can be integrated in the next generation of aircraft. To reduce project risk and optimize research benefit NASA chose to found two Phase 1 contracts. The first Phase 1 contracts went to engine manufactures and were awarded to: General Electric Company, and Pratt & Whitney Company. The second Phase 1 contracts went to fuel injector manufactures Goodrich Corporation, Parker Hannifin Corporation, and Woodward Fuel System Technology. In 2012, two sector combustors were tested at NASA’s ASCR. The results indicated 75% NOx emission reduction below the 2004 CAEP/6 regulation level.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-08-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130400133","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 : 2013-07-04DOI: 10.4172/2168-9792.1000113
J. Isaac, S. Graham
When we think of CFD (computational fluid dynamics) in the aerospace and aeronautical industries, we often limit our thinking to the aerodynamic analysis of wing/tail structure or fuselages. But CFD analysis applies to almost all of the critical components and systems of an aircraft. For example, excessive heat in the electronic components can lead to failure and reliability issues. Fuel delivery and engine cooling systems must be optimized. Cabin air conditioning/heating systems need to be analyzed. And the industry cannot afford to either over-conservatively design these systems (excessive cost) or prove efficiency/reliability by building multiple physical prototypes, testing in labs, and then re-designing, which is a long and expensive process. Because of these issues, CFD comes into play early and throughout the design process for multiple components and systems in the aircraft.
{"title":"CFD in the Aerospace and Aeronautics Industries","authors":"J. Isaac, S. Graham","doi":"10.4172/2168-9792.1000113","DOIUrl":"https://doi.org/10.4172/2168-9792.1000113","url":null,"abstract":"When we think of CFD (computational fluid dynamics) in the aerospace and aeronautical industries, we often limit our thinking to the aerodynamic analysis of wing/tail structure or fuselages. But CFD analysis applies to almost all of the critical components and systems of an aircraft. For example, excessive heat in the electronic components can lead to failure and reliability issues. Fuel delivery and engine cooling systems must be optimized. Cabin air conditioning/heating systems need to be analyzed. And the industry cannot afford to either over-conservatively design these systems (excessive cost) or prove efficiency/reliability by building multiple physical prototypes, testing in labs, and then re-designing, which is a long and expensive process. Because of these issues, CFD comes into play early and throughout the design process for multiple components and systems in the aircraft.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"112 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-07-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134488828","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 : 2013-07-02DOI: 10.4172/2168-9792.1000115
R. Sabatini, Anish Kaharkar, C. Bartel, Tesheen Shaid
As part of our recent research to assess the potential of low-cost navigation sensors for Unmanned Aerial Vehicle (UAV) applications, we investigated the potential of carrier-phase Global Navigation Satellite System (GNSS) for attitude determination and control of small size UAVs. Recursive optimal estimation algorithms were developed for combining multiple attitude measurements obtained from different observation points (i.e., antenna locations), and their efficiencies were tested in various dynamic conditions. The proposed algorithms converged rapidly and produced the required output even during high dynamics manoeuvres. Results of theoretical performance analysis and simulation activities are presented in this paper, with emphasis on the advantages of the GNSS interferometric approach in UAV applications (i.e., low cost, high data-rate, low volume/weight, low signal processing requirements, etc.). The simulation activities focussed on the AEROSONDE UAV platform and considered the possible augmentation provided by interferometric GNSS techniques to a low-cost and low-weight/volume integrated navigation system (presented in the first part of this series) which employed a Vision-Based Navigation (VBN) system, a Micro- Electro-Mechanical Sensor (MEMS) based Inertial Measurement Unit (IMU) and code-range GNSS (i.e., GPS and GALILEO) for position and velocity computations. The integrated VBN-IMU-GNSS (VIG) system was augmented using the inteferometric GNSS Attitude Determination (GAD)sensor data and a comparison of the performance achieved with the VIG and VIG/GAD integrated Navigation and Guidance Systems (NGS) is presented in this paper. Finally, the data provided by these NGS are used to optimise the design of a hybrid controller employing Fuzzy Logic and Proportional-Integral-Derivative (PID) techniques for the AEROSONDE UAV.
{"title":"Carrier-phase GNSS Attitude Determination and Control for Small Unmanned Aerial Vehicle Applications","authors":"R. Sabatini, Anish Kaharkar, C. Bartel, Tesheen Shaid","doi":"10.4172/2168-9792.1000115","DOIUrl":"https://doi.org/10.4172/2168-9792.1000115","url":null,"abstract":"As part of our recent research to assess the potential of low-cost navigation sensors for Unmanned Aerial Vehicle (UAV) applications, we investigated the potential of carrier-phase Global Navigation Satellite System (GNSS) for attitude determination and control of small size UAVs. Recursive optimal estimation algorithms were developed for combining multiple attitude measurements obtained from different observation points (i.e., antenna locations), and their efficiencies were tested in various dynamic conditions. The proposed algorithms converged rapidly and produced the required output even during high dynamics manoeuvres. Results of theoretical performance analysis and simulation activities are presented in this paper, with emphasis on the advantages of the GNSS interferometric approach in UAV applications (i.e., low cost, high data-rate, low volume/weight, low signal processing requirements, etc.). The simulation activities focussed on the AEROSONDE UAV platform and considered the possible augmentation provided by interferometric GNSS techniques to a low-cost and low-weight/volume integrated navigation system (presented in the first part of this series) which employed a Vision-Based Navigation (VBN) system, a Micro- Electro-Mechanical Sensor (MEMS) based Inertial Measurement Unit (IMU) and code-range GNSS (i.e., GPS and GALILEO) for position and velocity computations. The integrated VBN-IMU-GNSS (VIG) system was augmented using the inteferometric GNSS Attitude Determination (GAD)sensor data and a comparison of the performance achieved with the VIG and VIG/GAD integrated Navigation and Guidance Systems (NGS) is presented in this paper. Finally, the data provided by these NGS are used to optimise the design of a hybrid controller employing Fuzzy Logic and Proportional-Integral-Derivative (PID) techniques for the AEROSONDE UAV.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-07-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130710750","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 : 2013-06-28DOI: 10.4172/2168-9792.1000112
M. H. Djavareshkian, Amirreza Faghihi
A new pressure based implicit procedure to solve the Euler and Navier-Stokes equations is developed to predict transonic viscous and inviscid flowsaround the pitching airfoil with high resolution scheme. In this process, nonorthogonal and non moving mesh with collocated finite volume formulation areused. In order to simulate pitching airfoil, oscillation of flow boundary condition is applied. The boundedness criteria for this procedure are determined from Normalized Variable Diagram (NVD) scheme. The procedure incorporates the k - e eddy-viscosity turbulence model. In the new algorithm, the computation time is considerably reduced. This process is tested for inviscid and turbulent transonic aerodynamic flows around pitching airfoil.The results are compared with other existing numerical solutions and with experiment data. The comparisons show that the resolution quality of the developed algorithm is considerable.
{"title":"Transonic Flow Simulation Around the Pitching Airfoil with Accurate Pressure-Based Algorithm","authors":"M. H. Djavareshkian, Amirreza Faghihi","doi":"10.4172/2168-9792.1000112","DOIUrl":"https://doi.org/10.4172/2168-9792.1000112","url":null,"abstract":"A new pressure based implicit procedure to solve the Euler and Navier-Stokes equations is developed to predict transonic viscous and inviscid flowsaround the pitching airfoil with high resolution scheme. In this process, nonorthogonal and non moving mesh with collocated finite volume formulation areused. In order to simulate pitching airfoil, oscillation of flow boundary condition is applied. The boundedness criteria for this procedure are determined from Normalized Variable Diagram (NVD) scheme. The procedure incorporates the k - e eddy-viscosity turbulence model. In the new algorithm, the computation time is considerably reduced. This process is tested for inviscid and turbulent transonic aerodynamic flows around pitching airfoil.The results are compared with other existing numerical solutions and with experiment data. The comparisons show that the resolution quality of the developed algorithm is considerable.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121408143","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 : 2013-06-04DOI: 10.4172/2168-9792.1000111
M. Molina, F. Murrieta, Sergiyenko O.Yu., Petranovskii, D. Hernández-Balbuena, Tyrsa, M. Rivas-López, Garcia-Cruz Xm
An analysis of a frequency measurement by rational approximations principle application in Aerospace Industry is introduced. The results obtained from a circuit simulation that implements the novel method previously mentioned for measurement are presented. Also, it is shown that the method can be implemented in affordable hardware.
{"title":"Frequency Measurement by Principle of Rational Approximation for Aerospace Frequency Domain Mechanical Parameter Sensors","authors":"M. Molina, F. Murrieta, Sergiyenko O.Yu., Petranovskii, D. Hernández-Balbuena, Tyrsa, M. Rivas-López, Garcia-Cruz Xm","doi":"10.4172/2168-9792.1000111","DOIUrl":"https://doi.org/10.4172/2168-9792.1000111","url":null,"abstract":"An analysis of a frequency measurement by rational approximations principle application in Aerospace Industry is introduced. The results obtained from a circuit simulation that implements the novel method previously mentioned for measurement are presented. Also, it is shown that the method can be implemented in affordable hardware.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120997182","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 : 2013-05-31DOI: 10.4172/2168-9792.1000114
R. Sabatini, M. Richardson, E. Roviaro
In recent years, laser radar (LIDAR) has become a promising technology for navigation and obstacle avoidance in helicopters and UAV, mainly because of its good wire detection performance on a wide range of incidence angles, and also due to its outstanding range and accuracy. In this paper we describe the activities carried out for the design, integration and test of the Laser Obstacle Avoidance System “Marconi” (LOAM) on helicopter and UAV platforms. After a brief description of the system architecture and sensor characteristics, emphasis is given to the performance models and processing algorithms required for obstacle detection/classification and calculation of alternative flight paths, as well as to the ground and flight test activities performed on various platforms.
{"title":"Development and flight test of an avionics LIDAR for helicopter and UAV low-level flight","authors":"R. Sabatini, M. Richardson, E. Roviaro","doi":"10.4172/2168-9792.1000114","DOIUrl":"https://doi.org/10.4172/2168-9792.1000114","url":null,"abstract":"In recent years, laser radar (LIDAR) has become a promising technology for navigation and obstacle avoidance in helicopters and UAV, mainly because of its good wire detection performance on a wide range of incidence angles, and also due to its outstanding range and accuracy. In this paper we describe the activities carried out for the design, integration and test of the Laser Obstacle Avoidance System “Marconi” (LOAM) on helicopter and UAV platforms. After a brief description of the system architecture and sensor characteristics, emphasis is given to the performance models and processing algorithms required for obstacle detection/classification and calculation of alternative flight paths, as well as to the ground and flight test activities performed on various platforms.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-05-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124059053","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 purpose of this paper is to implement a new systematic methodology for conducting conceptual design studies of an Unmanned Aerial Vehicle (UAV). During the design phase of any system, many variables, tasks, parameters and components should be taken into account. In this work we employ a system engineering powerful analysis technique based on Sensitivity Design Structure Matrix (SDSM). DSM provides a simple, compact, and visual representation of a complex system which supports innovative solutions to decomposition and integration problems. In this work, SDSM method, considered as a powerful technique in design analysis of complex systems, has been employed in design analysis of a light weight UAV. Applying this effective disintegration methodology, all the design parameters and their inherent interconnections could be specified and if the design structured matrix elements confront changes, based on any changes in internal or external design drivers, its propagating effects on the whole system concept could be directly traceable which in turn lead least effect on the total system variations. Finally this paper shows that disintegrated, sections-based design process architecture, like that used for the Sirang, as a light weight UAV, is optimal for product development, and it results in a low cost architecture for development of UAVs.
{"title":"A New Systematic Approach in UAV Design Analysis Based on SDSM Method","authors":"Kosari Amirreze, Dolatabadi Marzieh, Sanii Foad, Asadi Fatemeh","doi":"10.4172/2168-9792.S1-001","DOIUrl":"https://doi.org/10.4172/2168-9792.S1-001","url":null,"abstract":"The purpose of this paper is to implement a new systematic methodology for conducting conceptual design studies of an Unmanned Aerial Vehicle (UAV). During the design phase of any system, many variables, tasks, parameters and components should be taken into account. In this work we employ a system engineering powerful analysis technique based on Sensitivity Design Structure Matrix (SDSM). DSM provides a simple, compact, and visual representation of a complex system which supports innovative solutions to decomposition and integration problems. In this work, SDSM method, considered as a powerful technique in design analysis of complex systems, has been employed in design analysis of a light weight UAV. Applying this effective disintegration methodology, all the design parameters and their inherent interconnections could be specified and if the design structured matrix elements confront changes, based on any changes in internal or external design drivers, its propagating effects on the whole system concept could be directly traceable which in turn lead least effect on the total system variations. Finally this paper shows that disintegrated, sections-based design process architecture, like that used for the Sirang, as a light weight UAV, is optimal for product development, and it results in a low cost architecture for development of UAVs.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"136 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-05-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116405057","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 : 2013-05-04DOI: 10.4172/2168-9792.1000110
R. RobertoSabatini, M. Richardson, C. Bartel, Tesheen Shaid, S. Ramasamy
A low cost navigation system based on Vision Based Navigation (VBN) and other avionics sensors is presented, which is designed for small size Unmanned Aerial Vehicle (UAV) applications. The main objective of our research is to design a compact, lightweight and relatively inexpensive system capable of providing the required navigation performance in all phases of flight of a small UAV, with a special focus on precision approach and landing, where Vision Based Navigation (VBN) techniques can be fully exploited in a multisensory integrated architecture. Various existing techniques for VBN are compared and the Appearance-based Navigation (ABN) approach is selected for implementation. Feature extraction and optical flow techniques are employed to estimate flight parameters such as roll angle, pitch angle, deviation from the runway and body rates. Additionally, we address the possible synergies between VBN, Global Navigation Satellite System (GNSS) and MEMS-IMU (Micro-Electromechanical System Inertial Measurement Unit) sensors and also the use of Aircraft Dynamics Models (ADMs) to provide additional information suitable to compensate for the shortcomings of VBN and MEMS-IMU sensors in high-dynamics attitude determination tasks. An Extended Kalman Filter (EKF) is developed to fuse the information provided by the different sensors and to provide estimates of position, velocity and attitude of the UAV platform in real-time. Two different integrated navigation system architectures are implemented. The first uses VBN at 20 Hz and GPS at 1 Hz to augment the MEMS-IMU running at 100 Hz. The second mode also includes the ADM (computations performed at 100 Hz) to provide augmentation of the attitude channel. Simulation of these two modes is performed in a significant portion of the AEROSONDE UAV operational flight envelope and performing a variety of representative manoeuvres (i.e., straight climb, level turning, turning descent and climb, straight descent, etc.). Simulation of the first integrated navigation system architecture (VBN/IMU/GPS) shows that the integrated system can reach position, velocity and attitude accuracies compatible with CAT-II precision approach requirements. Simulation of the second system architecture (VBN/IMU/GPS/ADM) also shows promising results since the achieved attitude accuracy is higher using the ADM/VBS/IMU than using VBS/IMU only. However, due to rapid divergence of the ADM virtual sensor, there is a need for frequent re-initialisation of the ADM data module, which is strongly dependent on the UAV flight dynamics and the specific manoeuvring transitions performed.
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