Pub Date : 2015-10-24DOI: 10.4172/2168-9792.1000144
A. Rajesh, A. Bt
Tri-cycle arrangement landing gear is extensively used as it is simple; convenient both structurally as well as aerodynamically. Though it is advantageous over other configuration is has its own draw backs. Factors like its weight drag, sudden application of load, acoustics, fatigue etc tend to slow down its performance and life. Among main landing gear and nose landing gear; the former carries about 85% of total weight of aircraft and latter carries around 12-15% of weight. The nose landing gear is also a source of noise and its effect is prominent when compared to main landing gear. In this project the executive jet aircraft are studied thoroughly and a nose landing gear similar to those of executive jets is modeled using CATIA. The same geometry is imported to ANSYS ICEM and flow on the body is analyzed for different angle of attack. Pressure variation, temperature, density and velocity distribution around the body is noted and then Coefficient for Lift and Drag are plotted against angle of attack for obtained results. It is also important to check the strength and stiffness of designed landing gear. Hence using ANSYS APDL and Explicit; Static structural and Impact test has been carried out for designed geometry. Stress distribution and deformation was noted for two distinct materials such as steel and aluminum alloy and primary results of acoustics has been compared with the available data.
{"title":"Design and Analysis Aircraft Nose and Nose Landing Gear","authors":"A. Rajesh, A. Bt","doi":"10.4172/2168-9792.1000144","DOIUrl":"https://doi.org/10.4172/2168-9792.1000144","url":null,"abstract":"Tri-cycle arrangement landing gear is extensively used as it is simple; convenient both structurally as well as aerodynamically. Though it is advantageous over other configuration is has its own draw backs. Factors like its weight drag, sudden application of load, acoustics, fatigue etc tend to slow down its performance and life. Among main landing gear and nose landing gear; the former carries about 85% of total weight of aircraft and latter carries around 12-15% of weight. The nose landing gear is also a source of noise and its effect is prominent when compared to main landing gear. In this project the executive jet aircraft are studied thoroughly and a nose landing gear similar to those of executive jets is modeled using CATIA. The same geometry is imported to ANSYS ICEM and flow on the body is analyzed for different angle of attack. Pressure variation, temperature, density and velocity distribution around the body is noted and then Coefficient for Lift and Drag are plotted against angle of attack for obtained results. It is also important to check the strength and stiffness of designed landing gear. Hence using ANSYS APDL and Explicit; Static structural and Impact test has been carried out for designed geometry. Stress distribution and deformation was noted for two distinct materials such as steel and aluminum alloy and primary results of acoustics has been compared with the available data.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"61 9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131082891","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 : 2015-10-15DOI: 10.4172/2168-9792.1000143
PadmanabanS, Mahendran Sme
The scope of the project is to Enhancing Flight Data Monitoring and Analysis can increase Flight Safety assists an operator to identify, quantify, assess and address operational risks. This analysis can be effectively used to support a range of airworthiness and operational safety tasks. The scope of this project is to de-code the recorded avionics parameter of interest based on the OEM’s recommendation by using the logical extraction of data from the data frame of the recorder based on ARINC standard and Air born software standard. This project involves different processes from Data down loading from the DFDR, Raw data extraction, Optimum Parameter configuration, Logical Event configuration, Logical calculation of various flight scenarios, Comparison with FCOM, Flight Health monitoring, Exceedance Analysis based on regulatory guidance, Statistical analysis of various avionics parameter’s impact on flight safety. The recommendation and solution found will be represented by various graphs and chart. Graphs of the checked parameters to show their evolution during cruise, take-off and landing phases of a same flight and an analysis of the validity of parameters based on graphs and corresponding tables, A check on the chronological structure of the complete recording, based on the aircraft flight history. It will be used for identifying and defining the risk index, and the inclusion and exclusion of the necessary maintenance programs based on the OEM.
{"title":"Enhancing Flight Data Monitoring and Analysis can Increase Flight Safety","authors":"PadmanabanS, Mahendran Sme","doi":"10.4172/2168-9792.1000143","DOIUrl":"https://doi.org/10.4172/2168-9792.1000143","url":null,"abstract":"The scope of the project is to Enhancing Flight Data Monitoring and Analysis can increase Flight Safety assists an operator to identify, quantify, assess and address operational risks. This analysis can be effectively used to support a range of airworthiness and operational safety tasks. The scope of this project is to de-code the recorded avionics parameter of interest based on the OEM’s recommendation by using the logical extraction of data from the data frame of the recorder based on ARINC standard and Air born software standard. This project involves different processes from Data down loading from the DFDR, Raw data extraction, Optimum Parameter configuration, Logical Event configuration, Logical calculation of various flight scenarios, Comparison with FCOM, Flight Health monitoring, Exceedance Analysis based on regulatory guidance, Statistical analysis of various avionics parameter’s impact on flight safety. The recommendation and solution found will be represented by various graphs and chart. Graphs of the checked parameters to show their evolution during cruise, take-off and landing phases of a same flight and an analysis of the validity of parameters based on graphs and corresponding tables, A check on the chronological structure of the complete recording, based on the aircraft flight history. It will be used for identifying and defining the risk index, and the inclusion and exclusion of the necessary maintenance programs based on the OEM.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114740516","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 : 2015-08-28DOI: 10.4172/2168-9792.1000142
M. Trivedi, R. M. Tallapragada, A. Branton, Dahryn Trivedi, G. Nayak, Omprakash Latiyal, S. Jana
Aluminium carbide (Al4C3) has gained extensive attention due to its abrasive and creep resistance properties. Aim of the present study was to evaluate the impact of biofield treatment on physical and structural properties of Al4C3 powder. The Al4C3 powder was divided into two parts i.e. control and treated. Control part was remained as untreated and treated part received biofield treatment. Subsequently, control and treated Al4C3 samples were characterized using X-ray diffraction (XRD), surface area analyser and Fourier transform infrared spectroscopy (FTIR). XRD data revealed that lattice parameter and unit cell volume of treated Al4C3 samples were increased by 0.33 and 0.66% respectively, as compared to control. The density of treated Al4C3 samples was reduced upto 0.65% as compared to control. In addition, the molecular weight and crystallite size of treated Al4C3 samples were increased upto 0.66 and 249.53% respectively as compared to control. Furthermore, surface area of treated Al4C3 sample was increased by 5% as compared to control. The FT-IR spectra revealed no significant change in absorption peaks of treated Al4C3 samples as compared to control. Thus, XRD and surface area results suggest that biofield treatment has substantially altered the physical and structural properties of treated Al4C3 powder
{"title":"Characterization of Physical and Structural Properties of Aluminium Carbide Powder: Impact of Biofield Treatment","authors":"M. Trivedi, R. M. Tallapragada, A. Branton, Dahryn Trivedi, G. Nayak, Omprakash Latiyal, S. Jana","doi":"10.4172/2168-9792.1000142","DOIUrl":"https://doi.org/10.4172/2168-9792.1000142","url":null,"abstract":"Aluminium carbide (Al4C3) has gained extensive attention due to its abrasive and creep resistance properties. Aim of the present study was to evaluate the impact of biofield treatment on physical and structural properties of Al4C3 powder. The Al4C3 powder was divided into two parts i.e. control and treated. Control part was remained as untreated and treated part received biofield treatment. Subsequently, control and treated Al4C3 samples were characterized using X-ray diffraction (XRD), surface area analyser and Fourier transform infrared spectroscopy (FTIR). XRD data revealed that lattice parameter and unit cell volume of treated Al4C3 samples were increased by 0.33 and 0.66% respectively, as compared to control. The density of treated Al4C3 samples was reduced upto 0.65% as compared to control. In addition, the molecular weight and crystallite size of treated Al4C3 samples were increased upto 0.66 and 249.53% respectively as compared to control. Furthermore, surface area of treated Al4C3 sample was increased by 5% as compared to control. The FT-IR spectra revealed no significant change in absorption peaks of treated Al4C3 samples as compared to control. Thus, XRD and surface area results suggest that biofield treatment has substantially altered the physical and structural properties of treated Al4C3 powder","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-08-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121373744","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 : 2015-08-28DOI: 10.4172/2168-9792.1000141
M. Raju
Numerical simulations are performed for flow over Phoenix entry vehicle at Mars at zero angle of Attack and Mach number 10. Flow field features like bow shock, shear layers, expansion fan and separation bubble will be captured using CFD commercial package FLUENT. The computed wall data of pressure and temperature will be compared with experimental results at Mars atmospheric conditions. This project deals with the study of flow over Phoenix entry vehicle at Mach number 10. The concept of atmospheric entry has applications in various fields. Vehicles that typically undergo this process include exo-orbital trajectories. In this project, the type of entry vehicle considered is entry capsule, which enters Mars atmosphere from an orbit. The primary design consideration of entry capsule requires large spherical nose radius of their fore body that gives high aerodynamic drag and a short body length for reducing the total structural weight and the ballistic coefficient.
{"title":"CFD Analysis of Mars Phoenix Capsules at Mach Number 10","authors":"M. Raju","doi":"10.4172/2168-9792.1000141","DOIUrl":"https://doi.org/10.4172/2168-9792.1000141","url":null,"abstract":"Numerical simulations are performed for flow over Phoenix entry vehicle at Mars at zero angle of Attack and Mach number 10. Flow field features like bow shock, shear layers, expansion fan and separation bubble will be captured using CFD commercial package FLUENT. The computed wall data of pressure and temperature will be compared with experimental results at Mars atmospheric conditions. This project deals with the study of flow over Phoenix entry vehicle at Mach number 10. The concept of atmospheric entry has applications in various fields. Vehicles that typically undergo this process include exo-orbital trajectories. In this project, the type of entry vehicle considered is entry capsule, which enters Mars atmosphere from an orbit. The primary design consideration of entry capsule requires large spherical nose radius of their fore body that gives high aerodynamic drag and a short body length for reducing the total structural weight and the ballistic coefficient.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-08-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116563498","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 : 2015-08-03DOI: 10.4172/2168-9792.1000140
Bartsch Ric
In 2002 Australia became the first nation to promulgate certification standards for the commercial use of drones or Unmanned Aircraft Systems (UAS). Since that time the Australian Civil Aviation Safety Authority (CASA) has played a key role both domestically and internationally through the International Civil Aviation Organization (ICAO) in assisting to develop technical guidance materials that will enable contracting states to develop UAS regulations. An arduous component of this task is the fact that all existing aircraft are capable of being unmanned. Moreover, given the unbounded nature of aircraft operations, UAS regulations necessarily require international harmonisation. But the objective of developing universal UAS standards is still far from being finalised while the accelerating pace of UAS technological development continues to challenge traditional regulatory regimes and legal systems throughout the world. This paper considers the broader legal issues associated with civilian UAS operations and their integration into unsegregated civilian airspace. In particular the Australian UAS regulatory experience is examined with some unique constitutional limitations identified in relation to the application of the so-called ‘commingling theory’. It is contended that such limitations may render void existing UAS regulation in certain situations – many of which are likely to have adverse privacy implications. This paper strongly asserts that if the commercial benefits attendant to UAS operations is to be fully realised then their risks to society must be controlled through domestic legislation that is harmonised with internationally agreed standards.
{"title":"Unmanned and Uncontrolled: The Commingling Theory and the Legality of Unmanned Aircraft System Operations","authors":"Bartsch Ric","doi":"10.4172/2168-9792.1000140","DOIUrl":"https://doi.org/10.4172/2168-9792.1000140","url":null,"abstract":"In 2002 Australia became the first nation to promulgate certification standards for the commercial use of drones or Unmanned Aircraft Systems (UAS). Since that time the Australian Civil Aviation Safety Authority (CASA) has played a key role both domestically and internationally through the International Civil Aviation Organization (ICAO) in assisting to develop technical guidance materials that will enable contracting states to develop UAS regulations. An arduous component of this task is the fact that all existing aircraft are capable of being unmanned. Moreover, given the unbounded nature of aircraft operations, UAS regulations necessarily require international harmonisation. But the objective of developing universal UAS standards is still far from being finalised while the accelerating pace of UAS technological development continues to challenge traditional regulatory regimes and legal systems throughout the world. This paper considers the broader legal issues associated with civilian UAS operations and their integration into unsegregated civilian airspace. In particular the Australian UAS regulatory experience is examined with some unique constitutional limitations identified in relation to the application of the so-called ‘commingling theory’. It is contended that such limitations may render void existing UAS regulation in certain situations – many of which are likely to have adverse privacy implications. This paper strongly asserts that if the commercial benefits attendant to UAS operations is to be fully realised then their risks to society must be controlled through domestic legislation that is harmonised with internationally agreed standards.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-08-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130434486","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 : 2015-07-10DOI: 10.4172/2168-9792.1000139
W. ScottSmith
According to Quantum Electrodynamics (QED), a hidden source of great momentum and energy, called the EM Quantum Vacuum, fills the Universe. A Quantum light-sail will use refraction to induce asymmetric boundary conditions in the isotropic EM radiation pressure of the Quantum Vacuum. In terms of Newton’s First Law, these asymmetric radiation-pressures act as outside-forces that push harder on one side of a light-sail than on its opposite side. This radiation-pressure will provide the motive force for a new class of macroscopic prime-movers, a kind of massless propulsion; a new environmental-energy conversion device.
{"title":"Casimir-Like Macroscopic Propulsion and Environmental-Energy Conversion","authors":"W. ScottSmith","doi":"10.4172/2168-9792.1000139","DOIUrl":"https://doi.org/10.4172/2168-9792.1000139","url":null,"abstract":"According to Quantum Electrodynamics (QED), a hidden source of great momentum and energy, called the EM Quantum Vacuum, fills the Universe. A Quantum light-sail will use refraction to induce asymmetric boundary conditions in the isotropic EM radiation pressure of the Quantum Vacuum. In terms of Newton’s First Law, these asymmetric radiation-pressures act as outside-forces that push harder on one side of a light-sail than on its opposite side. This radiation-pressure will provide the motive force for a new class of macroscopic prime-movers, a kind of massless propulsion; a new environmental-energy conversion device.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-07-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126906303","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 : 2015-05-10DOI: 10.4172/2168-9792.1000138
Fayssal Hadjez, B. Necib
The airline industry has been marked by numerous incidents. One of the first, who accompanied the start of operation of the first airliners with jet engines, was directly related to the portholes. Indeed, the banal form of the windows was the source of stress concentrations, which combined with the appearance of micro cracks, caused the explosion in flight of the unit. Since that time, all aircraft openings receive special attention in order to control and reduce their impact on the aircraft structure. In this paper we focus on the representation and quantification of stress concentrations at the windows of a regional jet flying at 40000 feet. To do this, we use a numerical method, similar to what is done at major aircraft manufacturers. The Patran/Nastran software will be used the finite element software to complete our goals.
{"title":"Stress Analysis of an Aircraft Fuselage with and without Portholes usingCAD/CAE Process","authors":"Fayssal Hadjez, B. Necib","doi":"10.4172/2168-9792.1000138","DOIUrl":"https://doi.org/10.4172/2168-9792.1000138","url":null,"abstract":"The airline industry has been marked by numerous incidents. One of the first, who accompanied the start of operation of the first airliners with jet engines, was directly related to the portholes. Indeed, the banal form of the windows was the source of stress concentrations, which combined with the appearance of micro cracks, caused the explosion in flight of the unit. Since that time, all aircraft openings receive special attention in order to control and reduce their impact on the aircraft structure. In this paper we focus on the representation and quantification of stress concentrations at the windows of a regional jet flying at 40000 feet. To do this, we use a numerical method, similar to what is done at major aircraft manufacturers. The Patran/Nastran software will be used the finite element software to complete our goals.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114336584","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 : 2015-03-25DOI: 10.4172/2168-9792.1000137
A. Abderrahmane
This study has been given prominence and confirmed by extensive documentation while recent visualizations observed in a wind tunnel have revealed that rectilinear vortex flows from different angles interacting with one another above warheads. My experimental research has indicated the many and very specific series, by visualizations of wisps of smoke trails, of vortex structures of a preferential nature above a warhead where β=68.6°. The positioning of those structures has thus been determined with regard to the application of very general criteria governing the stability of vortex flows. What have also been exposed are the specific aspects of vortex flows together with some comments concerning the bursting of vortices above the warhead. The purpose of this study is to optimize the connection between marine, air and land forms such as sails, the wings of aircraft, cars and trains – and the stability of fluid flows around such forms.
{"title":"The Study by Visualization of Vortex Structures on a Warhead Wing,Apex Angle (Ã)=68.6°","authors":"A. Abderrahmane","doi":"10.4172/2168-9792.1000137","DOIUrl":"https://doi.org/10.4172/2168-9792.1000137","url":null,"abstract":"This study has been given prominence and confirmed by extensive documentation while recent visualizations observed in a wind tunnel have revealed that rectilinear vortex flows from different angles interacting with one another above warheads. My experimental research has indicated the many and very specific series, by visualizations of wisps of smoke trails, of vortex structures of a preferential nature above a warhead where β=68.6°. The positioning of those structures has thus been determined with regard to the application of very general criteria governing the stability of vortex flows. What have also been exposed are the specific aspects of vortex flows together with some comments concerning the bursting of vortices above the warhead. The purpose of this study is to optimize the connection between marine, air and land forms such as sails, the wings of aircraft, cars and trains – and the stability of fluid flows around such forms.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2015-03-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125262138","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 : 2014-12-03DOI: 10.4172/2168-9792.1000136
S. Brischetto
{"title":"Innovative Multilayered Structures for a New Generation of Aircraft and Spacecraft","authors":"S. Brischetto","doi":"10.4172/2168-9792.1000136","DOIUrl":"https://doi.org/10.4172/2168-9792.1000136","url":null,"abstract":"","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2014-12-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114149556","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 : 2014-10-29DOI: 10.4172/2168-9792.1000135
R. Barrett
As aircraft design techniques become more and more automated with greater numbers of more powerful computational machines becoming available, exacting approaches like “knowledge based design” and “knowledge based engineering” (KBE) are becoming quite commonplace. Indeed, the field of KBE has roots stretching back many decades [1-3]. These KBE tools have in the past decade been systematically moved from detailed component design towards the arena of preliminary aircraft design [3-6]. While KBE and other computational tools are compatible with structural optimization with highly defined loads and operational conditions, such techniques are fundamentally challenged when loads are ill defined or when highly nonlinear factors are included. Another issue challenging such tools as they are being integrated into preliminary design is that they highlight a “computational mismatch” in that expensive, computationally costly methods are being used to arrive at the third and fourth significant figure of aircraft weights, when in preliminary design, only two are generally needed or appropriate for the task at hand.
{"title":"Statistical Time and Market Predictive Engineering Design (STAMPED) Techniques for Aerospace Preliminary Design: Regional TurbopropApplication","authors":"R. Barrett","doi":"10.4172/2168-9792.1000135","DOIUrl":"https://doi.org/10.4172/2168-9792.1000135","url":null,"abstract":"As aircraft design techniques become more and more automated with greater numbers of more powerful computational machines becoming available, exacting approaches like “knowledge based design” and “knowledge based engineering” (KBE) are becoming quite commonplace. Indeed, the field of KBE has roots stretching back many decades [1-3]. These KBE tools have in the past decade been systematically moved from detailed component design towards the arena of preliminary aircraft design [3-6]. While KBE and other computational tools are compatible with structural optimization with highly defined loads and operational conditions, such techniques are fundamentally challenged when loads are ill defined or when highly nonlinear factors are included. Another issue challenging such tools as they are being integrated into preliminary design is that they highlight a “computational mismatch” in that expensive, computationally costly methods are being used to arrive at the third and fourth significant figure of aircraft weights, when in preliminary design, only two are generally needed or appropriate for the task at hand.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"577 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2014-10-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123406967","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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