Pub Date : 2016-08-25DOI: 10.1109/ICMAE.2016.7549579
M. Yahyaoui
A lateral-directional flight control system for asymmetrical thrust is designed and applied to different aircraft models in the MATALAB/SIMULINK environment. The controller uses the full linearized lateral-directional dynamic model and includes a classical inner loop stability augmentation system. The approach consists of demanding zero yaw velocity and a specific bank angle toward the operative engine. By adjusting the gain of a proportional regulator and properly choosing the inner loop gains, the control system generates the aileron and rudder command laws which yield a stabilized straight flight, where the consigned value for the bank angle is obtained, along with zero yaw rate, zero roll rate and the correct sideslip angle. For validation purposes, controller results are compared to values obtained directly through solving the steady state lateral directional equations of motion with one engine inoperative and good agreement is demonstrated. The time required by the autopilot to reach stabilized flight is around five to eight seconds for all cases considered.
{"title":"A control system for flight at asymmetrical thrust","authors":"M. Yahyaoui","doi":"10.1109/ICMAE.2016.7549579","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549579","url":null,"abstract":"A lateral-directional flight control system for asymmetrical thrust is designed and applied to different aircraft models in the MATALAB/SIMULINK environment. The controller uses the full linearized lateral-directional dynamic model and includes a classical inner loop stability augmentation system. The approach consists of demanding zero yaw velocity and a specific bank angle toward the operative engine. By adjusting the gain of a proportional regulator and properly choosing the inner loop gains, the control system generates the aileron and rudder command laws which yield a stabilized straight flight, where the consigned value for the bank angle is obtained, along with zero yaw rate, zero roll rate and the correct sideslip angle. For validation purposes, controller results are compared to values obtained directly through solving the steady state lateral directional equations of motion with one engine inoperative and good agreement is demonstrated. The time required by the autopilot to reach stabilized flight is around five to eight seconds for all cases considered.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123380175","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 : 2016-08-25DOI: 10.1109/ICMAE.2016.7549563
A. Zaytsev
Surrogate modeling problems often include variable fidelity data. Most approaches consider the case of two available levels of fidelity, while engineers can have data with more than two samples sorted by fidelity. We consider Gaussian process regression framework that can construct surrogate models with arbitrary number of fidelity levels. While straightforward implementation struggles from numerical instability and numerical problems, our approach adopts Bayesian paradigm and provides direct control of numerical properties of surrogate model construction problems. Benchmark of the presented approach consists of various artificial and real data problems with the focus on surrogate modeling of an airfoil and a C-shape press.
{"title":"Reliable surrogate modeling of engineering data with more than two levels of fidelity","authors":"A. Zaytsev","doi":"10.1109/ICMAE.2016.7549563","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549563","url":null,"abstract":"Surrogate modeling problems often include variable fidelity data. Most approaches consider the case of two available levels of fidelity, while engineers can have data with more than two samples sorted by fidelity. We consider Gaussian process regression framework that can construct surrogate models with arbitrary number of fidelity levels. While straightforward implementation struggles from numerical instability and numerical problems, our approach adopts Bayesian paradigm and provides direct control of numerical properties of surrogate model construction problems. Benchmark of the presented approach consists of various artificial and real data problems with the focus on surrogate modeling of an airfoil and a C-shape press.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122947899","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 : 2016-08-25DOI: 10.1109/ICMAE.2016.7549586
Anshu Tiwari, Anuj S. Vora, N. K. Sinha
In this paper, bifurcation analysis of a full six degrees of freedom model of an airship is carried out both in unconstrained and constrained conditions. Equations of motion of airship are first modified to a suitable form and a standard as well as constrained bifurcation analysis performed with respect to airship control and design parameters. Typical modes of airship dynamics and regions of stable flights are identified via this analysis. Loss of stability and mode responsible for onset of instability at critical parameter values are also identified.
{"title":"Airship trim and stability analysis using bifurcation techniques","authors":"Anshu Tiwari, Anuj S. Vora, N. K. Sinha","doi":"10.1109/ICMAE.2016.7549586","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549586","url":null,"abstract":"In this paper, bifurcation analysis of a full six degrees of freedom model of an airship is carried out both in unconstrained and constrained conditions. Equations of motion of airship are first modified to a suitable form and a standard as well as constrained bifurcation analysis performed with respect to airship control and design parameters. Typical modes of airship dynamics and regions of stable flights are identified via this analysis. Loss of stability and mode responsible for onset of instability at critical parameter values are also identified.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122365266","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 : 2016-08-25DOI: 10.1109/ICMAE.2016.7549606
Wen Wang, Chao Yan, Yu Huang, Sheng Wang
Overset on viscous grid is an important application of overset grid method. The projection algorithm for viscous grid is a crucial algorithm of viscous grid overlapping and has been extended to the cell-centered system. Some special handling is done to enhance the robustness of the projection algorithm. A steady DLR-F6 wing body flow is performed, and good agreement of computational results with experimental data has been achieved, showing that this algorithm has a strong applicability to complex geometry.
{"title":"Enhancement of viscous grid projection algorithm and application","authors":"Wen Wang, Chao Yan, Yu Huang, Sheng Wang","doi":"10.1109/ICMAE.2016.7549606","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549606","url":null,"abstract":"Overset on viscous grid is an important application of overset grid method. The projection algorithm for viscous grid is a crucial algorithm of viscous grid overlapping and has been extended to the cell-centered system. Some special handling is done to enhance the robustness of the projection algorithm. A steady DLR-F6 wing body flow is performed, and good agreement of computational results with experimental data has been achieved, showing that this algorithm has a strong applicability to complex geometry.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117120396","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 : 2016-08-25DOI: 10.1109/ICMAE.2016.7549615
Luke Feetham, N. Aouf, O. Dubois-matra, C. Bourdarias
This paper describes the acquisition of a collection of representative image datasets for use in the development of autonomous planetary descent and landing navigation systems. These datasets were recently obtained using the VISILAB test-bench at ESA-ESTEC in The Netherlands, and represent realistic powered descent trajectories over a Lunar-type surface, but can also be relevant to a wide range of other mission types. The datasets will be made available upon request for research purposes by the academic community.
{"title":"Image datasets for autonomous planetary landing algorithm development","authors":"Luke Feetham, N. Aouf, O. Dubois-matra, C. Bourdarias","doi":"10.1109/ICMAE.2016.7549615","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549615","url":null,"abstract":"This paper describes the acquisition of a collection of representative image datasets for use in the development of autonomous planetary descent and landing navigation systems. These datasets were recently obtained using the VISILAB test-bench at ESA-ESTEC in The Netherlands, and represent realistic powered descent trajectories over a Lunar-type surface, but can also be relevant to a wide range of other mission types. The datasets will be made available upon request for research purposes by the academic community.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130601228","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 : 2016-08-25DOI: 10.1109/ICMAE.2016.7549551
M. M. Deshpande, H. Jawale, H. T. Thorat
Strain Gauge based force transducers are widely used in instrumentation and primary sensing elements in Force and torque measurements. At present, force transducers are necessarily force and moment transducer. The analysis of three force and three moments is the basis for evaluation of forces in three directions. These transducers are typically popular as six-axis force / moment transducer. Due to evaluation of three forces and three moments, the mathematical analysis becomes complex. These six variables warrant intricate models (shapes) of transducer to facilitate compliant surfaces to sense force / moments in specific direction. The moment estimations may not be required in typical robotic assembly platforms where theses sensors are performing a role as feedback devices. The proposed transducer ignores moments (even though they exists) and considers only force components. The sensors (strain gauge) pasted to three mutually perpendicular compliant surfaces. The transducer is randomly loaded, giving force components in three directions. One of the components will have effect on other two due to cross sensitivity. Thus load sensed in any mutually perpendicular direction is algebraic sum of force in that direction and a cross component of remaining two axis forces as result of cross sensitivity. A simple mathematical model is developed to arrive at actual forces in three directions to factor the effect of cross sensitivity. A tailor-made data acquisition card and an algorithm is developed to sense real-time forces. These transducers have wide range of applications.
{"title":"Development, calibration and testing of three axis force sensor","authors":"M. M. Deshpande, H. Jawale, H. T. Thorat","doi":"10.1109/ICMAE.2016.7549551","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549551","url":null,"abstract":"Strain Gauge based force transducers are widely used in instrumentation and primary sensing elements in Force and torque measurements. At present, force transducers are necessarily force and moment transducer. The analysis of three force and three moments is the basis for evaluation of forces in three directions. These transducers are typically popular as six-axis force / moment transducer. Due to evaluation of three forces and three moments, the mathematical analysis becomes complex. These six variables warrant intricate models (shapes) of transducer to facilitate compliant surfaces to sense force / moments in specific direction. The moment estimations may not be required in typical robotic assembly platforms where theses sensors are performing a role as feedback devices. The proposed transducer ignores moments (even though they exists) and considers only force components. The sensors (strain gauge) pasted to three mutually perpendicular compliant surfaces. The transducer is randomly loaded, giving force components in three directions. One of the components will have effect on other two due to cross sensitivity. Thus load sensed in any mutually perpendicular direction is algebraic sum of force in that direction and a cross component of remaining two axis forces as result of cross sensitivity. A simple mathematical model is developed to arrive at actual forces in three directions to factor the effect of cross sensitivity. A tailor-made data acquisition card and an algorithm is developed to sense real-time forces. These transducers have wide range of applications.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132275267","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 : 2016-07-18DOI: 10.1109/ICMAE.2016.7549570
Takumi Fujimori, Minoru Watanabe
Optically reconfigurable gate arrays (ORGAs) comprise a holographic memory, a laser array, and an optically reconfigurable gate array VLSI. According to holographic memory properties, the reconfiguration speed and radiation tolerance of ORGAs depend on the number of bright bits included in a configuration context. This paper therefore proposes a method of reducing the number of bright bits included in a configuration context using negative logic implementation. Since the method is architecture-independent, the method offers the important benefit that it is never necessary to modify the architecture of optically reconfigurable gate array VLSIs. This paper describes experimental demonstrations of the reconfiguration speed and radiation-tolerance advantages of the method.
{"title":"Architecture-independent negative logic implementation for optically reconfigurable gate arrays","authors":"Takumi Fujimori, Minoru Watanabe","doi":"10.1109/ICMAE.2016.7549570","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549570","url":null,"abstract":"Optically reconfigurable gate arrays (ORGAs) comprise a holographic memory, a laser array, and an optically reconfigurable gate array VLSI. According to holographic memory properties, the reconfiguration speed and radiation tolerance of ORGAs depend on the number of bright bits included in a configuration context. This paper therefore proposes a method of reducing the number of bright bits included in a configuration context using negative logic implementation. Since the method is architecture-independent, the method offers the important benefit that it is never necessary to modify the architecture of optically reconfigurable gate array VLSIs. This paper describes experimental demonstrations of the reconfiguration speed and radiation-tolerance advantages of the method.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114643380","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 : 2016-07-18DOI: 10.1109/ICMAE.2016.7549506
J. Bakunowicz, T. Kopecki, T. Lis, P. Mazurek
This paper presents results of numerical and experimental examination of thin-walled structures which model certain parts of aircraft structures subject to bending and torsion. The considered type of load and deformation corresponds to the state of such structures typical for in-flight conditions. A physical model of the analysed structure in several versions with and without stiffeners was made of composite materials. It was assumed that post-critical deformations of the structure are admissible within the limit loads. Results of non-linear numerical analyses carried out with the use of the finite element method applied to several variant structures with various types of stiffeners are compared with results of measurements taken on corresponding models.
{"title":"Effect of stiffeners on nature of post-critical deformations of thin-walled composite aircraft structures: A combined numerical-experimental study","authors":"J. Bakunowicz, T. Kopecki, T. Lis, P. Mazurek","doi":"10.1109/ICMAE.2016.7549506","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549506","url":null,"abstract":"This paper presents results of numerical and experimental examination of thin-walled structures which model certain parts of aircraft structures subject to bending and torsion. The considered type of load and deformation corresponds to the state of such structures typical for in-flight conditions. A physical model of the analysed structure in several versions with and without stiffeners was made of composite materials. It was assumed that post-critical deformations of the structure are admissible within the limit loads. Results of non-linear numerical analyses carried out with the use of the finite element method applied to several variant structures with various types of stiffeners are compared with results of measurements taken on corresponding models.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"98 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121377828","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 : 2016-07-18DOI: 10.1109/ICMAE.2016.7549562
I. Kurt, Mahmut Paksoy, S. Cetin, R. Guclu, S. Sezer
This paper presents a semi-active fuzzy logic control (FLC) strategy designed for a semi-trailer truck suspension system which consists of magnetorheological (MR) damper and linear spring. The objective of the controller is to improve the ride comfort by suppressing the vibrations that result from the road irregularities. The dynamic system is modelled in MATLAB/Simulink simulation environment. Simulations are carried out under standardized random road excitation generated according to ISO 8608 to investigate dynamic behaviour of seven degrees of freedom (DOFs) semi-trailer truck model. The Bouc-Wen model is utilized to characterize the hysteresis phenomenon of the MR dampers. Performance of designed controller is evaluated and the results indicate the effectiveness of the applied control algorithm on the vibration reduction compared to uncontrolled suspension system.
{"title":"Vibration reduction of semi-trailer truck using MR dampers: A fuzzy logic control approach","authors":"I. Kurt, Mahmut Paksoy, S. Cetin, R. Guclu, S. Sezer","doi":"10.1109/ICMAE.2016.7549562","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549562","url":null,"abstract":"This paper presents a semi-active fuzzy logic control (FLC) strategy designed for a semi-trailer truck suspension system which consists of magnetorheological (MR) damper and linear spring. The objective of the controller is to improve the ride comfort by suppressing the vibrations that result from the road irregularities. The dynamic system is modelled in MATLAB/Simulink simulation environment. Simulations are carried out under standardized random road excitation generated according to ISO 8608 to investigate dynamic behaviour of seven degrees of freedom (DOFs) semi-trailer truck model. The Bouc-Wen model is utilized to characterize the hysteresis phenomenon of the MR dampers. Performance of designed controller is evaluated and the results indicate the effectiveness of the applied control algorithm on the vibration reduction compared to uncontrolled suspension system.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"163 27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114193324","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 : 2016-07-18DOI: 10.1109/ICMAE.2016.7549518
A. Sharifi, H. Nobahari
The flight of unmanned aerial vehicles is often associated with model uncertainties, measurement noises, and environmental disturbances such as wind gust. To mitigate these challenges, the accurate estimation of states is vital. Moreover, the wind model and its parameters should also be estimated and compensated during the flight. In this paper, a multiple model filter is implemented for this purpose. To investigate the performance of the multiple model filter, three different models including constant wind, “1-cosine” model and wind shear model are considered. The multiple model filter utilizes three extended Kalman filter to simultaneously estimate the model of wind, the parameters of the model as well as the current states. Simulation results show that the multiple model filter provides good performance and the wind model is properly estimated. Moreover, small estimation errors, obtained from the simulations, prove the good performance of this approach in estimation of states, wind model, and its parameters.
{"title":"Multiple model filters applied to wind model estimation for a fixed wing UAV","authors":"A. Sharifi, H. Nobahari","doi":"10.1109/ICMAE.2016.7549518","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549518","url":null,"abstract":"The flight of unmanned aerial vehicles is often associated with model uncertainties, measurement noises, and environmental disturbances such as wind gust. To mitigate these challenges, the accurate estimation of states is vital. Moreover, the wind model and its parameters should also be estimated and compensated during the flight. In this paper, a multiple model filter is implemented for this purpose. To investigate the performance of the multiple model filter, three different models including constant wind, “1-cosine” model and wind shear model are considered. The multiple model filter utilizes three extended Kalman filter to simultaneously estimate the model of wind, the parameters of the model as well as the current states. Simulation results show that the multiple model filter provides good performance and the wind model is properly estimated. Moreover, small estimation errors, obtained from the simulations, prove the good performance of this approach in estimation of states, wind model, and its parameters.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127666858","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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