This project deals with the control of the wing rock phenomena of a delta wing aircraft. a control schemeis
proposed to stabilize the system. The controlleris a feedback linearization controller. It is shown that the
proposed control scheme guarantee the asymptotic convergence to zero of all the states of the system. To
illustrate the performance of the proposed controller, simulation results are presented and discussed. It is found
that the proposed control scheme work well for the wing rock phenomena of a delta wing aircraft.
Backstepping linearization controller of the Delta Wing Rock PhenomenaIJERA Editor
This paper deals with the control of the wing rock phenomena of a delta wing aircraft. A control technique is
proposed to stabilize the system. The controller is a BACKSTEPPING controller. It is appeared that the
proposed solution of control guarantee the asymptotic convergence to zero of all the states of the system. To
show the performance of the proposed controller, simulation results are presented and discussed. It is found that
the control scheme work well for the wing rock phenomena of a delta wing aircraft.
A Variable Control Structure Controller for the Wing Rock Phenomenon IJERA Editor
This paper presents the design of a variable structure controller for the model of the wing rock phenomenon of a
delta wing aircraft. It is considered to be a continue study of the last two researches for the same phenomena
"Feedback linearization [15] and back stepping controller [14] ". A control technique is proposed to stabilize the
aircraft phenomena. The solution presented in this paper give a guarantee of asymptotic convergence to zero of
all variables of the system. MATLAB simulation used to show how the proposed control is working well for
such phenomena of a delta wing aircraft. The model of the phenomena in this paper will consider the same
model presented in the last two researches mentioned above.
ENHANCED DATA DRIVEN MODE-FREE ADAPTIVE YAW CONTROL OF UAV HELICOPTERijics
An enhanced data driven model-free adaptive yaw control tracking control scheme is proposed for the yaw
channel of an unmanned-aerial-vehicle (UAV) helicopter which is non-affine in the control input in this paper. Through dynamic linearization and observer techniques, the proposed control algorithm is only based on the pseudo-partial derivative (PPD) parameter estimation derived online from the I/O data of the yaw channel of an UAV helicopter, and Lyapunov-based stability analysis is utilized to prove all signals of
close-loop control system are bounded. Compared with the traditional model free adaptive control
(MFAC), the proposed enhanced MFAC algorithm can make the close-loop control system with stronger robustness and better anti-jamming ability. Finally, simulation results of the UAV yaw channel are offered to demonstrate the effectiveness of the proposed novel control technique.
In this paper, a new 3D chaotic system is controlled by generalized backstepping method. Generalized
backstepping method is similarity to backstepping method but generalized backstepping method is more
applications in systems than it. Backstepping method is used only to strictly feedback systems but
generalized backsteppingmethod expand this class. New 3D chaotic system is controlled in two participate
sections; stabilization and tracking reference input. Numerical simulations are presented to demonstrate
the effectiveness of the controlschemes.
A New Approach to Design a Reduced Order ObserverIJERD Editor
In this paper, a new method for designing a reduced order observer for linear time-invariant system is
proposed. The approach is based on matrix inversion with proper dimension. The arbitrariness associated with
the method proposed by O’Reilly is presented here and has been reduced with the help of pole-placement
technique. It also helps reducing the computations regarding the observer design parameters. Illustrative
numerical examples with simulation results are also included.
Backstepping linearization controller of the Delta Wing Rock PhenomenaIJERA Editor
This paper deals with the control of the wing rock phenomena of a delta wing aircraft. A control technique is
proposed to stabilize the system. The controller is a BACKSTEPPING controller. It is appeared that the
proposed solution of control guarantee the asymptotic convergence to zero of all the states of the system. To
show the performance of the proposed controller, simulation results are presented and discussed. It is found that
the control scheme work well for the wing rock phenomena of a delta wing aircraft.
A Variable Control Structure Controller for the Wing Rock Phenomenon IJERA Editor
This paper presents the design of a variable structure controller for the model of the wing rock phenomenon of a
delta wing aircraft. It is considered to be a continue study of the last two researches for the same phenomena
"Feedback linearization [15] and back stepping controller [14] ". A control technique is proposed to stabilize the
aircraft phenomena. The solution presented in this paper give a guarantee of asymptotic convergence to zero of
all variables of the system. MATLAB simulation used to show how the proposed control is working well for
such phenomena of a delta wing aircraft. The model of the phenomena in this paper will consider the same
model presented in the last two researches mentioned above.
ENHANCED DATA DRIVEN MODE-FREE ADAPTIVE YAW CONTROL OF UAV HELICOPTERijics
An enhanced data driven model-free adaptive yaw control tracking control scheme is proposed for the yaw
channel of an unmanned-aerial-vehicle (UAV) helicopter which is non-affine in the control input in this paper. Through dynamic linearization and observer techniques, the proposed control algorithm is only based on the pseudo-partial derivative (PPD) parameter estimation derived online from the I/O data of the yaw channel of an UAV helicopter, and Lyapunov-based stability analysis is utilized to prove all signals of
close-loop control system are bounded. Compared with the traditional model free adaptive control
(MFAC), the proposed enhanced MFAC algorithm can make the close-loop control system with stronger robustness and better anti-jamming ability. Finally, simulation results of the UAV yaw channel are offered to demonstrate the effectiveness of the proposed novel control technique.
In this paper, a new 3D chaotic system is controlled by generalized backstepping method. Generalized
backstepping method is similarity to backstepping method but generalized backstepping method is more
applications in systems than it. Backstepping method is used only to strictly feedback systems but
generalized backsteppingmethod expand this class. New 3D chaotic system is controlled in two participate
sections; stabilization and tracking reference input. Numerical simulations are presented to demonstrate
the effectiveness of the controlschemes.
A New Approach to Design a Reduced Order ObserverIJERD Editor
In this paper, a new method for designing a reduced order observer for linear time-invariant system is
proposed. The approach is based on matrix inversion with proper dimension. The arbitrariness associated with
the method proposed by O’Reilly is presented here and has been reduced with the help of pole-placement
technique. It also helps reducing the computations regarding the observer design parameters. Illustrative
numerical examples with simulation results are also included.
On tracking control problem for polysolenoid motor model predictive approach IJECEIAES
The Polysolenoid Linear Motor (PLM) have been playing a crucial role in many industrial aspects due to its functions, in which a straight motion is provided directly without mediate mechanical actuators. Recently, with several commons on mathematic model, some control methods for PLM based on Rotational Motor have been applied, but position, velocity and current constraints which are important in real systems have been ignored. In this paper, position tracking control problem for PLM was considered under state-independent disturbances via min-max model predictive control. The proposed controller forces tracking position errors converge to small region of origin and satisfies state including position, velocity and currents constraints. Further, a numerical simulation was implemented to validate the performance of the proposed controller.
Abstract inglese:
In recent years Graphic Processing Units have seen widespread adoption in many scientific fields, from Machine Learning (ML) to Genomics. Their use makes it possible to achieve significant speedups and improvements in power efficiency over computationally intensive algorithms compared to General Purpose Central Processing Units. However, algorithms require specific knowledge of the GPU architecture and expertise to achieve significant results. In this work, we describe a methodology for automatic GPU kernel optimization. Our methodology exploits the Berkeley Roofline Model to perform a performance analysis of the algorithm considered and aims to increase the accessibility of GPU programming automatizing the optimization process of the kernel. We provide an in-depth analysis of this methodology, an overview on the state of the art, and a description of a tool we developed that automatically applies our methodology to obtain a highly optimized GPU version of two of the most popular algorithms used in computational biology, the X-drop and Smith-Waterman algorithms. The Smith-Waterman algorithm is one of the most used algorithms in genomics pipelines. The algorithm finds the optimal local alignment between two genomic sequences, at the cost of being particularly compute-intensive. The popular X-drop algorithm reduces the time required by the alignment by searching only for high-quality alignments. The algorithms accelerated using our methodology achieve more than 6x and 3x speed-up, for the X-drop and Smith-Waterman algorithms respectively, with respect to the state of the art implementation of these algorithms.
Hankel Determinent for Certain Classes of Analytic FunctionsIJERA Editor
Let 1 A denote the class of functions
2
( )
n
n
n f z z a z analytic in the unit disc E {z : |z| <1}.
M denotes the class of functions in 1 A which satisfy the conditions 0
( ). ( )
z
f z f z
and for
0 1, 0
( )
( ( ))
( )
( )
) 1 ( Re
f z
zf z
f z
zf z
. We are interested in determining the sharp upper bound
for the functional
2
2 4 3 a a a for the class M .
Design of predictive controller for smooth set point tracking for fast dynami...eSAT Journals
Abstract Model Predictive Control is generally used for slow dynamic system. Here efforts are made to implement MPC controller for Fast dynamic System. Speed control of DC motor is taken as fast dynamic system for which the MPC controller would be implemented. To control the speed of the DC motor Generalized Predictive Control (GPC) algorithm is used. In this paper, ARIX model based GPC control is implemented in 2-DOF structure. Transfer function of the DC motor is derived using LABVIEW and system identification tool of MATLAB. From the response of the system, it can be seen that the GPC has improved the performance of the system rather than PID control algorithm from disturbance rejection point of view. Keywords: MPC (Model Predictive Controller), GPC (Generalized Predictive Controller), ARIX Model (Auto Regressive Integrated Exogenous Model).
DEVELOPMENT OF NEUROFUZZY CONTROL SYSTEM FOR THE GUIDANCE OF AIR TO AIR MISS...Ahmed Momtaz Hosny, PhD
ABSTRACT
In recent years, there has been an increasing interest in the fusion of neural networks and fuzzy logic specially in missile control problems. A technique for the preliminary design of a control system is presented using a neurofuzzy approach for a highly nonlinear MIMO 5_DOF AIM 9R model. The model reflects cross coupling effects between the longitudinal and lateral motions. Two neural network controllers are used for the low level control of each motion separately. The control effort of these networks is then blended by a fuzzy logic controller to obtain the overall control action.The fuzzy controller which is a Mamdani type inference system has 25 rule base designed to cope with model uncertainties specially in cross coupling between lateral and longitudinal motions. A computer simulation is performed to compare between various control techniques. The result showed the effectiveness of the hybrid system compared to other control strategies where fuzzy systems or neural networks are used separately.
A Comparison Study between Inferred State-Space and Neural Network Based Syst...Ahmed Momtaz Hosny, PhD
In this paper, system identifications of an unmanned aerial vehicle (UAV) based on inferred state space and multiple neural networks were presented. In this work an optimization approach was used to conclude an inferred state space and the multiple neural networks system identifications based on the genetic algorithms separately. The UAV is a multi-input multi-output (MIMO) nonlinear system. Models for such MIMO system are expected to be adaptive to dynamic behavior and robust to environment.
FT-IR and FT-Raman spectral analysis of 2-amino – 4,6- dimethylpyrimidineIJERA Editor
Normal coordinate calculations of 2-amino-4,6-dimetylpyrimidine have been carried out using wilson’s FG
matix mechanism on the basis of General valence force field (GVFF) for both in-plane and out-of-plane
vibrations. The potential energy constants obtained in this study are refined using numerical methods.
La chirurgia bariatrica come chirurgia metabolica: l'arma più imporatnte di cui disponiamo oggi per il trattamento, molto spesso definitivo, del diabete di tipo II
On tracking control problem for polysolenoid motor model predictive approach IJECEIAES
The Polysolenoid Linear Motor (PLM) have been playing a crucial role in many industrial aspects due to its functions, in which a straight motion is provided directly without mediate mechanical actuators. Recently, with several commons on mathematic model, some control methods for PLM based on Rotational Motor have been applied, but position, velocity and current constraints which are important in real systems have been ignored. In this paper, position tracking control problem for PLM was considered under state-independent disturbances via min-max model predictive control. The proposed controller forces tracking position errors converge to small region of origin and satisfies state including position, velocity and currents constraints. Further, a numerical simulation was implemented to validate the performance of the proposed controller.
Abstract inglese:
In recent years Graphic Processing Units have seen widespread adoption in many scientific fields, from Machine Learning (ML) to Genomics. Their use makes it possible to achieve significant speedups and improvements in power efficiency over computationally intensive algorithms compared to General Purpose Central Processing Units. However, algorithms require specific knowledge of the GPU architecture and expertise to achieve significant results. In this work, we describe a methodology for automatic GPU kernel optimization. Our methodology exploits the Berkeley Roofline Model to perform a performance analysis of the algorithm considered and aims to increase the accessibility of GPU programming automatizing the optimization process of the kernel. We provide an in-depth analysis of this methodology, an overview on the state of the art, and a description of a tool we developed that automatically applies our methodology to obtain a highly optimized GPU version of two of the most popular algorithms used in computational biology, the X-drop and Smith-Waterman algorithms. The Smith-Waterman algorithm is one of the most used algorithms in genomics pipelines. The algorithm finds the optimal local alignment between two genomic sequences, at the cost of being particularly compute-intensive. The popular X-drop algorithm reduces the time required by the alignment by searching only for high-quality alignments. The algorithms accelerated using our methodology achieve more than 6x and 3x speed-up, for the X-drop and Smith-Waterman algorithms respectively, with respect to the state of the art implementation of these algorithms.
Hankel Determinent for Certain Classes of Analytic FunctionsIJERA Editor
Let 1 A denote the class of functions
2
( )
n
n
n f z z a z analytic in the unit disc E {z : |z| <1}.
M denotes the class of functions in 1 A which satisfy the conditions 0
( ). ( )
z
f z f z
and for
0 1, 0
( )
( ( ))
( )
( )
) 1 ( Re
f z
zf z
f z
zf z
. We are interested in determining the sharp upper bound
for the functional
2
2 4 3 a a a for the class M .
Design of predictive controller for smooth set point tracking for fast dynami...eSAT Journals
Abstract Model Predictive Control is generally used for slow dynamic system. Here efforts are made to implement MPC controller for Fast dynamic System. Speed control of DC motor is taken as fast dynamic system for which the MPC controller would be implemented. To control the speed of the DC motor Generalized Predictive Control (GPC) algorithm is used. In this paper, ARIX model based GPC control is implemented in 2-DOF structure. Transfer function of the DC motor is derived using LABVIEW and system identification tool of MATLAB. From the response of the system, it can be seen that the GPC has improved the performance of the system rather than PID control algorithm from disturbance rejection point of view. Keywords: MPC (Model Predictive Controller), GPC (Generalized Predictive Controller), ARIX Model (Auto Regressive Integrated Exogenous Model).
DEVELOPMENT OF NEUROFUZZY CONTROL SYSTEM FOR THE GUIDANCE OF AIR TO AIR MISS...Ahmed Momtaz Hosny, PhD
ABSTRACT
In recent years, there has been an increasing interest in the fusion of neural networks and fuzzy logic specially in missile control problems. A technique for the preliminary design of a control system is presented using a neurofuzzy approach for a highly nonlinear MIMO 5_DOF AIM 9R model. The model reflects cross coupling effects between the longitudinal and lateral motions. Two neural network controllers are used for the low level control of each motion separately. The control effort of these networks is then blended by a fuzzy logic controller to obtain the overall control action.The fuzzy controller which is a Mamdani type inference system has 25 rule base designed to cope with model uncertainties specially in cross coupling between lateral and longitudinal motions. A computer simulation is performed to compare between various control techniques. The result showed the effectiveness of the hybrid system compared to other control strategies where fuzzy systems or neural networks are used separately.
A Comparison Study between Inferred State-Space and Neural Network Based Syst...Ahmed Momtaz Hosny, PhD
In this paper, system identifications of an unmanned aerial vehicle (UAV) based on inferred state space and multiple neural networks were presented. In this work an optimization approach was used to conclude an inferred state space and the multiple neural networks system identifications based on the genetic algorithms separately. The UAV is a multi-input multi-output (MIMO) nonlinear system. Models for such MIMO system are expected to be adaptive to dynamic behavior and robust to environment.
FT-IR and FT-Raman spectral analysis of 2-amino – 4,6- dimethylpyrimidineIJERA Editor
Normal coordinate calculations of 2-amino-4,6-dimetylpyrimidine have been carried out using wilson’s FG
matix mechanism on the basis of General valence force field (GVFF) for both in-plane and out-of-plane
vibrations. The potential energy constants obtained in this study are refined using numerical methods.
La chirurgia bariatrica come chirurgia metabolica: l'arma più imporatnte di cui disponiamo oggi per il trattamento, molto spesso definitivo, del diabete di tipo II
Ideare, creare e condividere contenuti di successo.
Dall'ufficio tecnico ai Social Network, come le aziende B2B possono creare contenuti e pianificare una strategia di successo in rete.
đánh giá một số chỉ tiêu vệ sinh thú y trên thịt heo và sản phẩm chế biến từ ...Vinh Quang
CHƯƠNG 1: T[NG QUAN TÀI LIaU ............................................................. 31.1. Vi khudn Staphylococcus aureus .............................................................. 31.1.1. Phân loGi ............................................................................................ 31.1.2. Hình thái ............................................................................................ 41.1.3. Đgc ñi1m ........................................................................................... 41.1.4. S' phân b ......................................................................................... 61.1.5. Các y!u t ñ-c l'c ............................................................................. 61.1.6. V+y nhiBm vi sinh v$t trên thCt ......................................................... 121.1.7. Tình hình nghiên cu ng- ñ-c th'c phdm do S.aureus trên th! giHi và Vit Nam ................................................................................................... 151.2. Vi khudn Salmonella sp. ......................................................................... 161.2.1. Phân loGi .......................................................................................... 161.2.2. Đgc ñi1m ca Salmonella ................................................................ 171.2.3. Ngu:n gc lây nhiBm ....................................................................... 231.2.4. Tình hình nghiên cu Salmonella trong th'c phdm trên th! giHi và trong nưHc ................................................................................................. 241.3. Borax ..................................................................................................... 261.3.1. Đgc ñi1m ca Borax ......................................................................... 261.3.2. Tình hình sk dlng Borax trong th'c phdm ....................................... 261.3.3. Tác hGi ca Hàn the vHi ñ-ng v$t và ngư/i .................................... 271.3.4. Tình hình nghiên cu t:n dư Hàn the trong th'c phdm tGi Vit Nam .................................................................................................................. 28CHƯƠNG 2: ĐoI TƯpNG – NrI DUNG – PHƯƠNG PHÁP NGHIÊN CvU ......................................................................................................................... 302.1. Đi tư)ng nghiên cu ............................................................................. 302.2. N-i dung nghiên cu .............................................................................. 30
iv2.3. Phương pháp nghiên cu ........................................................................ 30CHƯƠNG 3: KxT QUy THyO LUzN ........................................................... 353.1. Đi4u kin v sinh thú y ca các cơ sN gi!t m2, qu8y bày bán thCt heo N các ch) trên ñCa bàn thành ph Kon Tum, tFnh Kon Tum .
Neural Network Control Based on Adaptive Observer for Quadrotor HelicopterIJITCA Journal
A neural network control scheme with an adaptive observer is proposed in this paper to Quadrotor helicopter stabilization. The unknown part in Quadrotor dynamical model was estimated on line by a
Single Hidden Layer network. To solve the non measurable states problem a new adaptive observer was proposed. The main purpose here is to reduce the measurement noise amplification caused by conventional
high gain observer by introducing some changes in observer’s original structure that can minimize the variance and the amplitude of the noisy signal without increasing tracking error. The stability analysis of the overall closed-loop system/ observer is performed using the Lyapunov direct method. Simulation results are given to highlight the performances of the proposed scheme.
ENHANCED DATA DRIVEN MODE-FREE ADAPTIVE YAW CONTROL OF UAV HELICOPTERijcisjournal
An enhanced data driven model-free adaptive yaw control tracking control scheme is proposed for the yaw channel of an unmanned-aerial-vehicle (UAV) helicopter which is non-affine in the control input in this paper. Through dynamic linearization and observer techniques, the proposed control algorithm is only based on the pseudo-partial derivative (PPD) parameter estimation derived online from the I/O data of the yaw channel of an UAV helicopter, and Lyapunov-based stability analysis is utilized to prove all signals of close-loop control system are bounded. Compared with the traditional model free adaptive control (MFAC), the proposed enhanced MFAC algorithm can make the close-loop control system with stronger robustness and better anti-jamming ability. Finally, simulation results of the UAV yaw channel are offered to demonstrate the effectiveness of the proposed novel control technique.
DUAL NEURAL NETWORK FOR ADAPTIVE SLIDING MODE CONTROL OF QUADROTOR HELICOPTER...ijistjournal
An adaptive sliding mode control based on two neural networks is proposed in this paper for Quadrotor stabilization. This approach presents solutions to conventional control drawbacks as chattering phenomenon and dynamical model imprecision. For that reason two ANN for each quadrotor helicopter subsystem are implemented in the control loop, the first one is a Single Hidden Layer network used to approximate on line the equivalent control and the second feed-forward Network is used to estimate the ideal corrective term. The main purpose behind the use of ANN in the second part of SMC is to minimize the chattering phenomena and response time by finding optimal sliding gain and sliding surface slope. The learning algorithms of the two ANNs (equivalent and corrective controller) are obtained using the direct Lyapunov stability method. The simulation results are given to highlight the performances of the proposed control scheme.
DUAL NEURAL NETWORK FOR ADAPTIVE SLIDING MODE CONTROL OF QUADROTOR HELICOPTER...ijistjournal
An adaptive sliding mode control based on two neural networks is proposed in this paper for Quadrotor stabilization. This approach presents solutions to conventional control drawbacks as chattering phenomenon and dynamical model imprecision. For that reason two ANN for each quadrotor helicopter subsystem are implemented in the control loop, the first one is a Single Hidden Layer network used to approximate on line the equivalent control and the second feed-forward Network is used to estimate the ideal corrective term. The main purpose behind the use of ANN in the second part of SMC is to minimize the chattering phenomena and response time by finding optimal sliding gain and sliding surface slope. The learning algorithms of the two ANNs (equivalent and corrective controller) are obtained using the direct Lyapunov stability method. The simulation results are given to highlight the performances of the proposed control scheme.
This article considers different approaches for autopilot controller gain values adjustment. The correct autopilot
performance is tested using modeling methods. A variant of land-based autopilot is considered. Examined are
scenarios of UAV airplanes in level flight. The latter are applicable to tasks such as remote sensing, controlled
area surveillance, etc.
Research Inventy : International Journal of Engineering and Science is published by the group of young academic and industrial researchers with 12 Issues per year. It is an online as well as print version open access journal that provides rapid publication (monthly) of articles in all areas of the subject such as: civil, mechanical, chemical, electronic and computer engineering as well as production and information technology. The Journal welcomes the submission of manuscripts that meet the general criteria of significance and scientific excellence. Papers will be published by rapid process within 20 days after acceptance and peer review process takes only 7 days. All articles published in Research Inventy will be peer-reviewed.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
Neural Network Control Based on Adaptive Observer for Quadrotor HelicopterIJITCA Journal
A neural network control scheme with an adaptive observer is proposed in this paper to Quadrotor helicopter stabilization. The unknown part in Quadrotor dynamical model was estimated on line by a Single Hidden Layer network. To solve the non measurable states problem a new adaptive observer was proposed. The main purpose here is to reduce the measurement noise amplification caused by conventional high gain observer by introducing some changes in observer’s original structure that can minimize the variance and the amplitude of the noisy signal without increasing tracking error. The stability analysis of the overall closed-loop system/ observer is performed using the Lyapunov direct method. Simulation results are given to highlight the performances of the proposed scheme
T-S Fuzzy Observer and Controller of Doubly-Fed Induction GeneratorIJPEDS-IAES
This paper aims to ensure a stability and observability of doubly fed induction generator DFIG of a wind turbine based on the approach of fuzzy control type T-S PDC (Parallel Distributed Compensation) which determines the control laws by return state and fuzzy observers.First, the fuzzy TS model is used to precisely represent a nonlinear model of DFIG proposed and adopted in this work. Then, the stability analysis is based on the quadratic Lyapunov function to determine the gains that ensure the stability conditions.The fuzzy observer of DFIG is built to estimate non-measurable state vectors and the estimated states converging to the actual statements. The gains of observatory and of stability are obtained by solving a set of linear matrix inequality (LMI).Finally, numerical simulations are performed to verify the theoretical results and demonstrate satisfactory performance.
The research of 6-DOF flight simulator washout filter Control MethodIJRES Journal
Electric 6-DOF flight simulator used in large aircraft engineering simulation has great benefits,As a Flight Simulator vector parallel six degree of freedom motion system is a very important part of flight simulator. Feeling is the most important in Flight simulator test while flight.If a flight simulator can feel closer to the real feeling of flying aircraft, in is more better for trainning.According to the question above, In this paper, we will start from the control method,make research on electric 6-DOF flight simulator wash out the filter control method, we will research Longitudinal studies of flight parameters at takeoff position flight simulator. Using MATLAB simulation software to verify washout filter algorithm practicality simulator Simulation.
Unknown Input Observer for a Doubly Fed Induction Generator Subject to Distur...IJPEDS-IAES
This paper deals with the problem design of an unknown input observer
(UIO) for a Doubly Fed Induction Generator (DFIG) subject to disturbances.
These disturbances can be considered as unknown inputs (UI). The state
space model of the DFIG is obtained from the voltage equations of the stator
and rotor. Then, this latter is used for the design of an unknown input
observer (UIO) in order to estimate both the state and the unknown inputs of
the DFIG. Furthermore, the UIO gains are computed by solving a set of
linear matrix inequalities (LMIs). Simulations results are given to show the
performance and the effectiveness of the proposed method.
MATHEMATICAL MODELING OF COMPLEX REDUNDANT SYSTEM UNDER HEAD-OF-LINE REPAIREditor IJMTER
Suppose a composite system consisting of two subsystems designated as ‘P’ and
‘Q’ connected in series. Subsystem ‘P’ consists of N non-identical units in series, while the
subsystem ‘Q’ consists of three identical components in parallel redundancy.
The Neural Network-Combined Optimal Control System of Induction MotorIJECEIAES
This research aims to propose the optimal control method combined with the neuron network for an induction motor. In the proposed system, the induction motor is a nonlinear object which is controlled at each working point. At these working-points, the state equation of the induction motor is linear, so it is possible to apply the linear quadratic regular algorithm for the induction motor. Therefore, the parameters of the state feedback controller are the functions. The output-input relationships of these functions are set through the neural network. The numerical simulation results show that the quality of the control system of the induction motor is very high: The response speed always follows the desired speed with the short transition time and the small overshoot. Furthermore, the system is robust in the case of changing the load torque, and the parameters of the induction motor are incorrectly defined
Design of Digital Autopilot for Lateral Motion Control of an Aircraft Based o...IJERA Editor
The optimal digital autopilot needed to control of the roll for an aircraft in the presence of an arbitrary unmeasured disturbances is addressed in this paper. Such autopilot has to achieve a desired lateral motion control of this aircraft via minimizing the upper bound on the absolute value of the difference between the given and true roll angles. It is ensured by means of the two digital controllers. The inner controller is designed as the discrete-time PI controller in order to stabilize a given roll rate. This variable is formed by the external P controller. The necessary and sufficient conditions under which the two-circuit feedback discrete-time control system will be stable are derived. To optimize this control system, the controller parameters are derived utilizing the so-called l1-optimization approach advanced in modern control theory. A numerical example demonstrating the l1-optimization technique and results of some simulation experiments are presented to illustrate the performance of the l1-optimal controller. The robustness properties of this controller are established
OPTIMAL PID CONTROLLER DESIGN FOR SPEED CONTROL OF A SEPARATELY EXCITED DC MO...ijscmcj
This paper presents a new approach to determine the optimal proportional-integral-derivative controller
parameters for the speed control of a separately excited DC motor using firefly optimization technique.
Firefly algorithm is one of the recent evolutionary methods which are inspired by the Firefly’s behavior in
nature. The firefly optimization technique is successfully implemented using MATLAB software. A
comparison is drawn from the results obtained between the linear quadratic regulator and firefly
optimization techniques. Simulation results are presented to illustrate the performance and validity of the
design method.
Real Time Implementation of Fuzzy Adaptive PI-sliding Mode Controller for Ind...IJECEIAES
In this work, a fuzzy adaptive PI-sliding mode control is proposed for Induction Motor speed control. First, an adaptive PI-sliding mode controller with a proportional plus integral equivalent control action is investigated, in which a simple adaptive algorithm is utilized for generalized soft-switching parameters. The proposed control design uses a fuzzy inference system to overcome the drawbacks of the sliding mode control in terms of high control gains and chattering to form a fuzzy sliding mode controller. The proposed controller has implemented for a 1.5kW three-Phase IM are completely carried out using a dSPACE DS1104 digital signal processor based real-time data acquisition control system, and MATLAB/Simulink environment. Digital experimental results show that the proposed controller can not only attenuate the chattering extent of the adaptive PI-sliding mode controller but can provide high-performance dynamic characteristics with regard to plant external load disturbance and reference variations.
Attitude Control of Quadrotor Using PD Plus Feedforward Controller on SO(3)IJECEIAES
This paper proposes a simple scheme of Proportional-Derivative (PD) plus Feedforward controller on SO(3) to control the attitude of a quadrotor. This controller only needs the measurement of angular velocity to calculate the exponential coordinates of the rotation matrix. With rotation matrix as an error variable of the controller, the simulation shows that the controller is able to drive the attitude of the quadrotor from hovering condition to desired attitude and from an attitude condition goes to the hovering condition, despite the system is disturbed. When the system is convergent, the rotation error matrix will be a 3 3 identity matrix.
Similar to Feedback Linearization Controller Of The Delta WingRock Phenomena (20)
Hybrid optimization of pumped hydro system and solar- Engr. Abdul-Azeez.pdffxintegritypublishin
Advancements in technology unveil a myriad of electrical and electronic breakthroughs geared towards efficiently harnessing limited resources to meet human energy demands. The optimization of hybrid solar PV panels and pumped hydro energy supply systems plays a pivotal role in utilizing natural resources effectively. This initiative not only benefits humanity but also fosters environmental sustainability. The study investigated the design optimization of these hybrid systems, focusing on understanding solar radiation patterns, identifying geographical influences on solar radiation, formulating a mathematical model for system optimization, and determining the optimal configuration of PV panels and pumped hydro storage. Through a comparative analysis approach and eight weeks of data collection, the study addressed key research questions related to solar radiation patterns and optimal system design. The findings highlighted regions with heightened solar radiation levels, showcasing substantial potential for power generation and emphasizing the system's efficiency. Optimizing system design significantly boosted power generation, promoted renewable energy utilization, and enhanced energy storage capacity. The study underscored the benefits of optimizing hybrid solar PV panels and pumped hydro energy supply systems for sustainable energy usage. Optimizing the design of solar PV panels and pumped hydro energy supply systems as examined across diverse climatic conditions in a developing country, not only enhances power generation but also improves the integration of renewable energy sources and boosts energy storage capacities, particularly beneficial for less economically prosperous regions. Additionally, the study provides valuable insights for advancing energy research in economically viable areas. Recommendations included conducting site-specific assessments, utilizing advanced modeling tools, implementing regular maintenance protocols, and enhancing communication among system components.
Final project report on grocery store management system..pdfKamal Acharya
In today’s fast-changing business environment, it’s extremely important to be able to respond to client needs in the most effective and timely manner. If your customers wish to see your business online and have instant access to your products or services.
Online Grocery Store is an e-commerce website, which retails various grocery products. This project allows viewing various products available enables registered users to purchase desired products instantly using Paytm, UPI payment processor (Instant Pay) and also can place order by using Cash on Delivery (Pay Later) option. This project provides an easy access to Administrators and Managers to view orders placed using Pay Later and Instant Pay options.
In order to develop an e-commerce website, a number of Technologies must be studied and understood. These include multi-tiered architecture, server and client-side scripting techniques, implementation technologies, programming language (such as PHP, HTML, CSS, JavaScript) and MySQL relational databases. This is a project with the objective to develop a basic website where a consumer is provided with a shopping cart website and also to know about the technologies used to develop such a website.
This document will discuss each of the underlying technologies to create and implement an e- commerce website.
Quality defects in TMT Bars, Possible causes and Potential Solutions.PrashantGoswami42
Maintaining high-quality standards in the production of TMT bars is crucial for ensuring structural integrity in construction. Addressing common defects through careful monitoring, standardized processes, and advanced technology can significantly improve the quality of TMT bars. Continuous training and adherence to quality control measures will also play a pivotal role in minimizing these defects.
Vaccine management system project report documentation..pdfKamal Acharya
The Division of Vaccine and Immunization is facing increasing difficulty monitoring vaccines and other commodities distribution once they have been distributed from the national stores. With the introduction of new vaccines, more challenges have been anticipated with this additions posing serious threat to the already over strained vaccine supply chain system in Kenya.
Forklift Classes Overview by Intella PartsIntella Parts
Discover the different forklift classes and their specific applications. Learn how to choose the right forklift for your needs to ensure safety, efficiency, and compliance in your operations.
For more technical information, visit our website https://intellaparts.com
Courier management system project report.pdfKamal Acharya
It is now-a-days very important for the people to send or receive articles like imported furniture, electronic items, gifts, business goods and the like. People depend vastly on different transport systems which mostly use the manual way of receiving and delivering the articles. There is no way to track the articles till they are received and there is no way to let the customer know what happened in transit, once he booked some articles. In such a situation, we need a system which completely computerizes the cargo activities including time to time tracking of the articles sent. This need is fulfilled by Courier Management System software which is online software for the cargo management people that enables them to receive the goods from a source and send them to a required destination and track their status from time to time.
Overview of the fundamental roles in Hydropower generation and the components involved in wider Electrical Engineering.
This paper presents the design and construction of hydroelectric dams from the hydrologist’s survey of the valley before construction, all aspects and involved disciplines, fluid dynamics, structural engineering, generation and mains frequency regulation to the very transmission of power through the network in the United Kingdom.
Author: Robbie Edward Sayers
Collaborators and co editors: Charlie Sims and Connor Healey.
(C) 2024 Robbie E. Sayers
Immunizing Image Classifiers Against Localized Adversary Attacksgerogepatton
This paper addresses the vulnerability of deep learning models, particularly convolutional neural networks
(CNN)s, to adversarial attacks and presents a proactive training technique designed to counter them. We
introduce a novel volumization algorithm, which transforms 2D images into 3D volumetric representations.
When combined with 3D convolution and deep curriculum learning optimization (CLO), itsignificantly improves
the immunity of models against localized universal attacks by up to 40%. We evaluate our proposed approach
using contemporary CNN architectures and the modified Canadian Institute for Advanced Research (CIFAR-10
and CIFAR-100) and ImageNet Large Scale Visual Recognition Challenge (ILSVRC12) datasets, showcasing
accuracy improvements over previous techniques. The results indicate that the combination of the volumetric
input and curriculum learning holds significant promise for mitigating adversarial attacks without necessitating
adversary training.
Feedback Linearization Controller Of The Delta WingRock Phenomena
1. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 128|P a g e
Feedback Linearization Controller Of The Delta WingRock
Phenomena
Mohammed Alkandari1
, Mohammed Alhamdan2
Electrical Networks Department, High Institute of Energy, Public Authority of Applied Education and Training,
KUWAIT
ABSTRACT
This project deals with the control of the wing rock phenomena of a delta wing aircraft. a control schemeis
proposed to stabilize the system. The controlleris a feedback linearization controller. It is shown that the
proposed control scheme guarantee the asymptotic convergence to zero of all the states of the system. To
illustrate the performance of the proposed controller, simulation results are presented and discussed. It is found
that the proposed control scheme work well for the wing rock phenomena of a delta wing aircraft.
Key words: Wing Rock, Nonlinear Control of Wing Rock, Feedback Control
I. INTRODUCTION
Wing rock phenomena is a limit-cycle rolling motion by flight aircrafts with small aspect-ratio wings, or
with long pointed forebodies at angles of attack [1]. thewing rock phenomenais studied by many researchers,
because of its importance in the stability of an aircraft during attack maneuvers. It is also reported in [6] that the
such phenomena does not have a limit cycle can happen at an 80/65 degree double delta wing.
It is a nonlinear phenomenon experienced by aircraft in which oscillations and unstable behavior is
experienced [9]. This problem may affect flight effectiveness or even present a serious damage due to potential
instability of the aircraft [1]. This phenomenais extensively studied experimentally, giving in mathematical
models that describe the nonlinear rolling motion using simple differential equations as in [7],[8].
The wing rock model for a wing aircraft used in [1] is considered in this project. Wing rock is modeled as a
self-induced, rolling motion, which causes rolling moment to be a nonlinear function of the roll angle and the
roll-rate p . The coefficients of such nonlinear function is obtained by curve fitting with experimental data at
specific values of angle of muvering. In addition, yawing dynamicis added to the model by adding the yawing
rate r = - ( / t ) and ignoring the nonlinear term due to its small value compared with the other terms
II. MATHIMATICAL MODEL OF THE PHENOMENA
The transformation ( )z T x is defined such that:
(2.6)
The inverse transformation
1
( )x T z
exists and it is as follows.
1 1 4 5
2 4
3 5
4 2 4 5
2 2 3 2
5 1 1 2 2 1 2 1 2 2 1 2
2
3 4 5 5 2 4 5
( )
( ( ) ( ) ( ) ( ) ( ) ( ) ( )
( ) ( ) ( )) ( )
p r
p r
p
r r p r
z N x N x x
z N x
z N x
z N N x N x N x
z N N x t x t x t x t b x t b x t x t
L x t L x t L x t N x N N N x N x N x
RESEARCH ARTICLE OPEN ACCESS
2. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 129|P a g e
1 1 2 3
2 4 2 3
2 22
3 5 4 2 3 1 2 32
2 22 1
1 1 2 3 4 2 3 4 2 32 2 2
2 3 3
1 1
( )
1
( )
1 1
[ ( ( ) )( )]
1 1
[( ( ) ( ) )( )]
1
[
r
p
r
p
r
r
p
r
r r
p p
p p r r
N
x z z z
N N N
x z N z N z
N N
b N
x z N z N z N z z z z
L N N N N
N b
z z z z N z N z z N z N z
L N N N N N
N L z N L z N z N
L
4
4 2
5 3
]
1
1
z
x z
N
x z
N
(2.7)
Hence, the dynamic model of the wing rock phenomenon can be written as,
1 2
2 3
3 4
54
5 ( ) ( )
z
z
z
z
q x g x u
z
z
z
z
z
(2.8)
where:
III. FEEDBACK LINEARIZATION CONTROLLER FOR THE WING ROCK
PHENOMENON
3.1 Design of the Controller
Recall from the previous chapter that the wing rock phenomenon can be described using the following set
of differential equations:
2 2 3 2
1 1 2 2 1 2 1 2 2 1 2 4 5
2
5 2 4 5 3
( ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ))
( )
( )
( )
( )
[
]
p r
r p r
p
N N x t x t x t x t b x t b x t x t L x t L x t
N x N N N x N x N x
q x
L k x t
g x kN N L
3. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 130|P a g e
1 2( ) ( )x t x t
2 2 3 2
2 1 1 2 2 1 2 1 2 2 1 2( ) ( ) ( ) ( ) ( ) ( ) ( ) ( )x t x t x t x t x t b x t b x t x t 3 4 5( ) ( ) ( )rL x t L x t L x t
3 3( ) ( )x t kx t ku 4 5( ) ( )x t x t
5 2 4 5( ) ( ) ( ) ( )p rx t N x t N x t N x t (3.1)
Using the transformation defined in chapter 2, the above equations can be written as:
1 2
2 3
3 4
54
5 ( ) ( )
z
z
z
z
q x g x u
z
z
z
z
z
(3.2)
With,
2 2 3 2
1 1 2 2 1 2 1 2 2 1 2 4 5
2
5 2 4 5 3
( ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ))
( )
( )
( )
( )
[
]
p r
r p r
p
N N x t x t x t x t b x t b x t x t L x t L x t
N x N N N x N x N x
q x
L k x t
g x kN N L
In this chapter, a feedback linearization controller will be designed to control the wing rock phenomenon.
Let the scalars 1 2 3 4 5, , , , be chosen such that the polynomial
5 4 3 2
1 5 4 3 2 1( )s s s s s sP is a Hurwitz polynomial (i.e. , the roots of 1( ) 0sP are
located in the left half plane).
Proposition 3.1:
The feedback linearization controller
1 2 3 4 5 51 2 3 4
1
[ ]
( )
( )
g x
z z z z zu q x (3.3)
guarantees the asyptotic convergence of 51 2 3 4, , , ,z z z z z to zero as t .
Proof:
The closed loop system when the controller (3.3) is used is as follows:
4. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 131|P a g e
5 51 1 2 2 3 3 4 4
1 2
2 3
3 4
54
5 z z z z z
z
z
z
z
z
z
z
z
z
(3.4)
Define the vector z such that 51 2 3 4 ][ T
z z z z zz .
The closed loop system given by (3.4) can be written in compact form as:
z zz A (3.5)
where the matrix zA is such that:
The solution of the differential equation given by (3.5) is ) (0)( ) exp( zt zz t A . Since the matrix zA
is a stable matrix, the vector z(t) will converge to zero asymptotically as t .
Remark
The feedback linearization controller
1 2 3 4 5 51 2 3 4
1
[ ]
( )
( )
g x
z z z z zu q x
can be written in the original coordinates by using the transformation:
1 1 4 5
2 4
3 5
4 2 4 5
2 2 3 2
5 1 1 2 2 1 2 1 2 2 1 2
2
3 4 5 5 2 4 5
( )
( ( ) ( ) ( ) ( ) ( ) ( ) ( )
( ) ( ) ( )) ( )
p r
p r
p
r r p r
z N x N x x
z N x
z N x
z N N x N x N x
z N N x t x t x t x t b x t b x t x t
L x t L x t L x t N x N N N x N x N x
(3.6)
3.2 Simulation results
The poles of 1( ) 0P s are chosen to be -1, -2, -3, -4, -5, then
1 2 3 4 5
0 1 0 0 0
0 0 1 0 0
0 0 0 1 0
0 0 0 0 1
zA
5. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 132|P a g e
Hence,
1 2 3 4 515, 85, 225, 274, 120
The performance of the closed loop system is simulated using the MATLAB software and the results are
plotted for the states with initial values = [0.2 0 0 0 0]. Figure 8 – Figure 12 show the plots of
, , , ,p
t
respectively.
Figure 8 Roll angle (rad.)
Figure 9 Roll-rate (rad/sec)
5 4 3 2 1
1 1 2 3 4 5
5 4 3 2 1 5 4 3 2 1
1 2 3 4 5
( )
( 1)( 2)( 3)( 4)( 5)
15 85 225 274 120
P s s s s s s
s s s s s
s s s s s s s s s s
6. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 133|P a g e
Figure 10 Aileron deflection angle (rad.)
Figure 11 sideslip angle (rad)
Figure 12 sideslip rate (rad/sec)
IV. CONCLUSION
The figures show that all the states converge to zero asymptotically. Hence, it can be concluded that the
proposed feedback linearization controller works well for the stabilization of the wing rock phenomenon.
7. Mohammed Alkandari Int. Journal of Engineering Research and Applications www.ijera.com
ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -3) May 2015, pp.128-134
www.ijera.com 134|P a g e
REFERENCE
papers.
[1] Tewari, A. “Nonlinear optimal control of wing rock including yawing motion,” paper No AIAA 2000-
4251,proceedings of AIAA Guidance, Navigation and control conference, Denver, CO.
[2] DR. mohammed Zeirebi transformation function in Appendix[II].
[3] Monahemi, M.M., and Krstic, M., "Control of Wing Rock Motion Using Adaptive Feedback
Linearization", J. of Guidance, Control, and Dynamics, Vol.19, No.4,1996, pp.905-912.
[4] Singh, S.N., Yim, W., and Wells, W.R., "Direct Adaptive and Neural Control of Wing Rock Motion of
Slender Delta Wings", J. of Guidance, Control, and Dynamics, Vol.18, No.l, 1995, pp.25-30.
[5] Internet Exploring.
[6] Pelletier, A. and Nelson, R. C., ``Dynamic Behavior of An 80/65 Double-Delta Wing in Roll,'' AIAA
98-4353.
[7] Raul Ordonez and Kevin M., ``Wing Rock Regulation with a time-Varying Angle of Attack,''
Proceedings of IEEE (ISIC 2000).
[8] Zenglian Liu, Chun-Yi Su, and Jaroslav Svoboda., ``A Novel Wing-Rock Control Approach Using
Hysteresis Compensation '' Proceedings of American Control Conference, Denver, Colorado June 4-
6,2003.
[9] Santosh V. Joshi, A. G. Sreenatha, and J. Chandrasekhar ``Suppression of Wing Rock of Slender Delta
Wings Using A Single Neuron Controller'' IEEE Transaction on control system technology, Vol. 6 No.
5 September 1998
[10] Z. L. Liu, C. -Y. Su, and J. Svoboda ``Control of Wing Rock Using Fuzzy PD Controller'' IEEE
International Conference on Fuzzy Systems. 2003
[11] Chin-Teng Lin, Tsu-Tian Lee, Chun-Fei Hsu and Chih-Min Lin ``Hybrid Adaptive Fussy ontrol Wing
Rock Motion System with H infinity Robust Performance'' Department of Electrical and Control
Engineering, National Chiao-Tung University, Hsinchu 300, Taiwan, Republic of China.
[12] Chun-Fei Hsu and Chih-min Lin “ Neural-Network-Based adaptive Control of Wing Rock Motion ''
Department of Electrical and Control Engineering, Yuan-Ze University, Chung-Li, Tao-Yuan,
320,Taiwan, Republic of China.
[13] M. D. Chen, C. C. Chien, C. Y. Cheng, M. C. Lai “ On the Control of a Simplified Rocking Delta Wing
Model '' Department of Electrical Engineering, USC, Los Angeles, CA 90089-2563
BOOKS
[1] Numerical Solution Of Nonlinear State-Equations