Pub Date : 2016-07-18DOI: 10.1109/ICMAE.2016.7549576
E. Çetin, A. T. Kutay
The aim of this study is to design a landing control system and test it on X-Plane flight simulator. Model-Following control and H-Infinity output feedback control methods are used to design the controller. In the flare part of the automatic landing system, it is desired to reduce the rate of descent in order to make aircraft touch down softly. This is accomplished by exponential decay trajectory. The trajectory which is drawn by the referenced model is followed by the linearized aircraft model. The error between commanded altitude and the current altitude converges to zero before touch down. Controller gains used in the model-following control design are calculated by using the H-Infinity output feedback control method since not all the state variables will be available for feedback in actual flight. Aircraft control commands for the flare control design in Matlab-Simulink environment are sent to the aircraft model in X-Plane flight simulator via User Datagram Protocol (UDP) and then the measured aircraft output variables are received simultaneously. The results provided in this study show that the aircraft in X-Plane flight simulator which has a nonlinear environment can be controlled by the model-following controller to satisfy the landing flare requirements. Robustness of the controller will also be evaluated against modeling errors and external disturbances.
{"title":"Automatic landing flare control design by model-following control and flight test on X-Plane flight simulator","authors":"E. Çetin, A. T. Kutay","doi":"10.1109/ICMAE.2016.7549576","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549576","url":null,"abstract":"The aim of this study is to design a landing control system and test it on X-Plane flight simulator. Model-Following control and H-Infinity output feedback control methods are used to design the controller. In the flare part of the automatic landing system, it is desired to reduce the rate of descent in order to make aircraft touch down softly. This is accomplished by exponential decay trajectory. The trajectory which is drawn by the referenced model is followed by the linearized aircraft model. The error between commanded altitude and the current altitude converges to zero before touch down. Controller gains used in the model-following control design are calculated by using the H-Infinity output feedback control method since not all the state variables will be available for feedback in actual flight. Aircraft control commands for the flare control design in Matlab-Simulink environment are sent to the aircraft model in X-Plane flight simulator via User Datagram Protocol (UDP) and then the measured aircraft output variables are received simultaneously. The results provided in this study show that the aircraft in X-Plane flight simulator which has a nonlinear environment can be controlled by the model-following controller to satisfy the landing flare requirements. Robustness of the controller will also be evaluated against modeling errors and external disturbances.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"78 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":"127011369","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.2016.7549535
Zied Sahraoui, K. Mehdi, Moez Ben Jaber
Chatter in cutting process is harmful to the productivity by its harmful effects such as poor surface quality and reduced productivity. Modeling and analyzing machining stability become necessary to understand the process dynamics and especially to predict the stability in machining operations. Stability lobe diagrams are among the methods that have been adopted to analyze system stability by indicating the boundary between stable and unstable zone. The diagrams are generated function of the depth or width of cut and the spindle speed. In this paper we will present a 3-DOFs analytical analysis of a turning cutting process stability of a steel 42 CD 4 workpiece (hollow cylinder) at low cutting speed including generation of stability lobe diagrams, workpiece displacements and cutting efforts time-variation curves.
{"title":"Analytical analysis of stability in turning","authors":"Zied Sahraoui, K. Mehdi, Moez Ben Jaber","doi":"10.1109/ICMAE.2016.7549535","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549535","url":null,"abstract":"Chatter in cutting process is harmful to the productivity by its harmful effects such as poor surface quality and reduced productivity. Modeling and analyzing machining stability become necessary to understand the process dynamics and especially to predict the stability in machining operations. Stability lobe diagrams are among the methods that have been adopted to analyze system stability by indicating the boundary between stable and unstable zone. The diagrams are generated function of the depth or width of cut and the spindle speed. In this paper we will present a 3-DOFs analytical analysis of a turning cutting process stability of a steel 42 CD 4 workpiece (hollow cylinder) at low cutting speed including generation of stability lobe diagrams, workpiece displacements and cutting efforts time-variation curves.","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":"133538840","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.2016.7549604
Cheng Xiao-ning, Gu Chao-Chao
It is easy for Low Earth Orbit (LEO) spacecraft to accumulate charged particles during its flight, resulting in the surface potential rises, producing the discharge phenomenon and generating serious harm to the craft. This paper is based on the kinetic theory of gases, the theory of plasma in Maxwell velocity distribution function and spacecraft surface current balance equation, calculating the general expression of surface potential with plasma density, plasma temperature and spacecraft speed under the condition of no light. The results show that the surface potential of the spacecraft almost has a linear relationship with the flight speed and the plasma temperature while plasma density has little effect on the surface potential of spacecraft.
{"title":"Surface charging numeration of LEO spacecraft","authors":"Cheng Xiao-ning, Gu Chao-Chao","doi":"10.1109/ICMAE.2016.7549604","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549604","url":null,"abstract":"It is easy for Low Earth Orbit (LEO) spacecraft to accumulate charged particles during its flight, resulting in the surface potential rises, producing the discharge phenomenon and generating serious harm to the craft. This paper is based on the kinetic theory of gases, the theory of plasma in Maxwell velocity distribution function and spacecraft surface current balance equation, calculating the general expression of surface potential with plasma density, plasma temperature and spacecraft speed under the condition of no light. The results show that the surface potential of the spacecraft almost has a linear relationship with the flight speed and the plasma temperature while plasma density has little effect on the surface potential of spacecraft.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"33 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":"130748585","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.2016.7549555
Jing Gao, Guanxin Hong
In view of the correlation function matrix, a 3D atmospheric turbulence field based on the Von Karman model is generated with the Monte Carlo simulation, which realizes the deduction and application of the complex Von Karman model. The ability of the simulation to approach the theoretical result is unlimited. The whitening degree of the random number sequence and the precision and efficiency of the atmospheric turbulence simulations are improved. This atmospheric turbulence field is identical with the Von Karman model for the numerical tests and has perfect statistical characteristics and simulation precision. The simulation method in this paper could be used in flight simulation.
{"title":"Numerical simulation for 3D atmospheric turbulence field","authors":"Jing Gao, Guanxin Hong","doi":"10.1109/ICMAE.2016.7549555","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549555","url":null,"abstract":"In view of the correlation function matrix, a 3D atmospheric turbulence field based on the Von Karman model is generated with the Monte Carlo simulation, which realizes the deduction and application of the complex Von Karman model. The ability of the simulation to approach the theoretical result is unlimited. The whitening degree of the random number sequence and the precision and efficiency of the atmospheric turbulence simulations are improved. This atmospheric turbulence field is identical with the Von Karman model for the numerical tests and has perfect statistical characteristics and simulation precision. The simulation method in this paper could be used in flight simulation.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"3 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":"131230193","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.2016.7549553
K. Dvořák
Free form surface modeling is one of the most advanced procedures of creating digital models in CAD. Use of free surface for creating solid models has become increasingly relevant in terms of technological possibilities of production in the subsequent phases of the product lifecycle. Multi-axis computer-controlled machines are standard even in small workshops and rapid prototyping is undergoing progressive development and deployment of industry. Initial geometry is a system of free curves in space. Free-form surfaces are reference geometry for shape complex solid objects. Applicability of free formed bodies for implementing subsequent manufacturing processes depends on the consistency of surfaces enveloping model. Using exact quantitative analysis of the free-form surface is difficult and inappropriate. The presented paper describes analysis methods of initial free curves and subsequent free areas in order to identify and assess the consistency and smoothness of the surface for the use the model in the subsequent phases of the product lifecycle.
{"title":"Modeling strategy of freeforms on the basis of qualitative analysis","authors":"K. Dvořák","doi":"10.1109/ICMAE.2016.7549553","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549553","url":null,"abstract":"Free form surface modeling is one of the most advanced procedures of creating digital models in CAD. Use of free surface for creating solid models has become increasingly relevant in terms of technological possibilities of production in the subsequent phases of the product lifecycle. Multi-axis computer-controlled machines are standard even in small workshops and rapid prototyping is undergoing progressive development and deployment of industry. Initial geometry is a system of free curves in space. Free-form surfaces are reference geometry for shape complex solid objects. Applicability of free formed bodies for implementing subsequent manufacturing processes depends on the consistency of surfaces enveloping model. Using exact quantitative analysis of the free-form surface is difficult and inappropriate. The presented paper describes analysis methods of initial free curves and subsequent free areas in order to identify and assess the consistency and smoothness of the surface for the use the model in the subsequent phases of the product lifecycle.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"94 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":"115904858","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.2016.7549598
F. Rea, M. Arena, M. Noviello, R. Pecora, F. Amoroso
Aircraft wings are usually optimized for a specific mission design point. However, since they operate in a wide variety of flight conditions, some of these have conflicting impacts on aircraft design process, as a single configuration may be efficient in one instance but perform poorly in others. A shape-shifting surface, or usually referred as “morphing”, potentially enables transport aircraft to reach maximum performance in any flight conditions. Within the framework of the Joint Technology Initiative Clean Sky (JTI-CS) project, and during the first phase of the Green Regional Aircraft Integrated Technological Demonstration (GRA-ITD), the authors focused on the design and technological demonstration of an innovative bi-modal morphing outer wing flap to be installed on the next generation open rotor green regional aircraft. A novel active rib layout was designed to enable the articulation of the entire flap structure by means of multi-box arrangement. In order to prove structural load-carrying capabilities with the reference to a relevant environment, the full-scale morphing flap was properly analyzed by means of detailed finite element model analysis. To the authors' knowledge, there is no morphing concept in literature based on a similar architecture based on distributed servo-mechanical actuators. Hence, a rational review of the potential problems associated with actuators off-design conditions has been conducted to investigate the maturity of the concept and safety issues concerning the flap ground static test. In addition, useful insights have been provided to effectively detect potential failure conditions in service.
{"title":"Preliminary failure analysis of an innovative morphing flap tailored for large civil aircraft applications","authors":"F. Rea, M. Arena, M. Noviello, R. Pecora, F. Amoroso","doi":"10.1109/ICMAE.2016.7549598","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549598","url":null,"abstract":"Aircraft wings are usually optimized for a specific mission design point. However, since they operate in a wide variety of flight conditions, some of these have conflicting impacts on aircraft design process, as a single configuration may be efficient in one instance but perform poorly in others. A shape-shifting surface, or usually referred as “morphing”, potentially enables transport aircraft to reach maximum performance in any flight conditions. Within the framework of the Joint Technology Initiative Clean Sky (JTI-CS) project, and during the first phase of the Green Regional Aircraft Integrated Technological Demonstration (GRA-ITD), the authors focused on the design and technological demonstration of an innovative bi-modal morphing outer wing flap to be installed on the next generation open rotor green regional aircraft. A novel active rib layout was designed to enable the articulation of the entire flap structure by means of multi-box arrangement. In order to prove structural load-carrying capabilities with the reference to a relevant environment, the full-scale morphing flap was properly analyzed by means of detailed finite element model analysis. To the authors' knowledge, there is no morphing concept in literature based on a similar architecture based on distributed servo-mechanical actuators. Hence, a rational review of the potential problems associated with actuators off-design conditions has been conducted to investigate the maturity of the concept and safety issues concerning the flap ground static test. In addition, useful insights have been provided to effectively detect potential failure conditions in service.","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":"126051873","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.2016.7549571
Prabhjot Kaur Dhawan, Seongkyu Lee
This paper presents the validation and numerical parameter study of a semi-empirical trailing edge noise model. Turbulent boundary layer trailing edge noise is the main contributor of wind turbine noise and aircraft airframe noise. To predict this self-noise generated due to the interaction between a turbulent boundary layer flow and an airfoil trailing edge, a semi-empirical model was developed in NASA. The model has been widely used in academia and industry to predict the trailing edge noise. The capabilities and limitations of this semi-empirical model is further studied in this paper by comparing the predictions of the model with experimental data that were presented in a recent Benchmark Problems for Airframe Noise Computations (BANC) workshop. In order to better understand the behavior of trailing edge noise with operating conditions, numerical parameter study is investigated by varying variables such as chord length, Reynolds number, and Mach number.
{"title":"Validation and numerical parameter study of a semi-empirical trailing edge noise model","authors":"Prabhjot Kaur Dhawan, Seongkyu Lee","doi":"10.1109/ICMAE.2016.7549571","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549571","url":null,"abstract":"This paper presents the validation and numerical parameter study of a semi-empirical trailing edge noise model. Turbulent boundary layer trailing edge noise is the main contributor of wind turbine noise and aircraft airframe noise. To predict this self-noise generated due to the interaction between a turbulent boundary layer flow and an airfoil trailing edge, a semi-empirical model was developed in NASA. The model has been widely used in academia and industry to predict the trailing edge noise. The capabilities and limitations of this semi-empirical model is further studied in this paper by comparing the predictions of the model with experimental data that were presented in a recent Benchmark Problems for Airframe Noise Computations (BANC) workshop. In order to better understand the behavior of trailing edge noise with operating conditions, numerical parameter study is investigated by varying variables such as chord length, Reynolds number, and Mach number.","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":"128443021","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}
Recently optimal design for engineering structures is being a research hotspot, and the core technology is structural optimization technology, which is being used in more and more fields. In this paper, its research progress was reviewed which was consists of research condition and prospect in future. Firstly, the fundamental concept of structural optimization was introduced, and then structural optimization levels such as size optimization, shape optimization, and topology optimization and its application in aerospace field were presented. Afterwards, optimization algorithms like optimality criteria methods, mathematical programming methods, and genetic algorithms were reviewed, and finally, probable research directions of structural optimization technology in the future were prospected.
{"title":"Research progress of engineering structural optimization in aerospace field","authors":"Lei Liu, Aijun Ma, Hongying Liu, Xuemei Feng, Meng Shi, Rui Dong, Yaxiong Zhao","doi":"10.1109/ICMAE.2016.7549602","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549602","url":null,"abstract":"Recently optimal design for engineering structures is being a research hotspot, and the core technology is structural optimization technology, which is being used in more and more fields. In this paper, its research progress was reviewed which was consists of research condition and prospect in future. Firstly, the fundamental concept of structural optimization was introduced, and then structural optimization levels such as size optimization, shape optimization, and topology optimization and its application in aerospace field were presented. Afterwards, optimization algorithms like optimality criteria methods, mathematical programming methods, and genetic algorithms were reviewed, and finally, probable research directions of structural optimization technology in the future were prospected.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"90 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":"116835915","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.2016.7549504
Hu Ting
An analysis of lightning current conduction and the resulting damage to the composite material on aircraft was implemented in this paper by adopting the thermoelectric coupling through ABAQUS simulation. On the basis of the existing lightning simulation experiments, a three-dimensional finite element model of composite laminate was built; the electrical and thermal boundary condition together with the coupled material properties was introduced. As a result, the thermal distribution of lightning current and the damage process of composite laminate were therefore obtained from the simulation. It can be derived from the result that the shape as well as the size of the damage varies on different composite layers: by comparing the results of the four typical inducting lightning currents with the same peak magnitude as well as the damage generated in different layers, it is conclude that the damage area and the damage depth are proportional to the action integral.
{"title":"Thermoelectric coupling simulation lightning damage of aircraft composite","authors":"Hu Ting","doi":"10.1109/ICMAE.2016.7549504","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549504","url":null,"abstract":"An analysis of lightning current conduction and the resulting damage to the composite material on aircraft was implemented in this paper by adopting the thermoelectric coupling through ABAQUS simulation. On the basis of the existing lightning simulation experiments, a three-dimensional finite element model of composite laminate was built; the electrical and thermal boundary condition together with the coupled material properties was introduced. As a result, the thermal distribution of lightning current and the damage process of composite laminate were therefore obtained from the simulation. It can be derived from the result that the shape as well as the size of the damage varies on different composite layers: by comparing the results of the four typical inducting lightning currents with the same peak magnitude as well as the damage generated in different layers, it is conclude that the damage area and the damage depth are proportional to the action integral.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"103 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":"122048914","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.2016.7549572
H. Mohammadkarimi, H. Nobahari, A. Sharifi
In this paper, a novel algorithm for correcting the error of attitude in inertial navigation systems is introduced. Since the oftenly used differential equations of the navigation errors show the small rotation angles instead of the error of Euler angles, the nonlinear equation between the small rotation angles and the error of Euler angles, are derived. To obtain an approximative solution for the derived equations, third order multiplication of the small rotation angles are ignored and error of Euler angles are expressed explicitly as functions of the Euler angles and the small rotation angles. Based on the obtained solution, a new algorithm for attitude correction in inertial navigation is developed. A comprehensive numerical simulation is performed and superiority of the proposed algorithm than the usual method used for attitude correction, is shown. The proposed algorithm has smaller error in calculation of Euler angles. Also, the proposed method saves the orthogonality and normality conditions of the transformation matrix.
{"title":"A new approximative method for attitude correction in inertial navigation systems","authors":"H. Mohammadkarimi, H. Nobahari, A. Sharifi","doi":"10.1109/ICMAE.2016.7549572","DOIUrl":"https://doi.org/10.1109/ICMAE.2016.7549572","url":null,"abstract":"In this paper, a novel algorithm for correcting the error of attitude in inertial navigation systems is introduced. Since the oftenly used differential equations of the navigation errors show the small rotation angles instead of the error of Euler angles, the nonlinear equation between the small rotation angles and the error of Euler angles, are derived. To obtain an approximative solution for the derived equations, third order multiplication of the small rotation angles are ignored and error of Euler angles are expressed explicitly as functions of the Euler angles and the small rotation angles. Based on the obtained solution, a new algorithm for attitude correction in inertial navigation is developed. A comprehensive numerical simulation is performed and superiority of the proposed algorithm than the usual method used for attitude correction, is shown. The proposed algorithm has smaller error in calculation of Euler angles. Also, the proposed method saves the orthogonality and normality conditions of the transformation matrix.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"59 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":"121790072","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：