CONCEPT OF OPERATIONS TO SYSTEM DESIGN AND DEVELOPMENT-AN INTEGRATED SYSTEM FOR AIRCRAFT MISSION FEASIBILITY ANALYSIS USING STK ENGINE, MATLAB AND LABVIEW
In recent times, there has been a significant rise in usage of aircrafts in surveillance and reconnaissance missions. Not all the aircrafts survive the harsh testing conditions put forth by the enemy regions. Aircraft Survivability Analysis gives the measure of the chances of survival for different counter strategies. The mission would be recalculated if particular sortie does not fall within the physical boundary of the performance of an aircraft. This is required both for the success of the mission and the survivability of the aircraft in the harsh enemy conditions.
A system is envisioned comprising of the accurate modeling of the physical world and the accurate model of control system. An interoperable system which can work seamlessly together will provide mission planners, System integrators, aeronautical/aerospace engineers a milieu wherein the Control System designer who is found wanted as far as the physical world is concerned is given a system which can simulate the real world in lab conditions. To achieve this, we combine the two most promising environments prevalent in the industry today namely Systems tool kit for modeling the operational environment MATLAB and LabVIEW for modeling the control system environment. Using a Math script window of LabVIEW, we have designed the aircraft model and controlling the variables of an aircraft using a simulation loop of a LabVIEW. The different flight conditions were arrived using Orthogonal Array (OA) based on different Aircraft weight, Altitude, Mach number configurations. This attempts to span the aircrafts across the regimes in aircrafts flight envelope. A system comprising of both, with seamless UDP based connection between the two is developed to expedite the process of development of feasible control system design and verification which allows the aircrafts to undertake complex mission. This system we believe would answer questions of limits of the aircrafts maneuverability and survivability in terms of its limitation concerning control system design and development of commercial fighter aircrafts, UAV's and Quad copters.
This document describes U PPAAL PORT, a new tool for component-based design and analysis of embedded systems. U PPAAL PORT uses partial-order reduction techniques to efficiently model check hierarchical component models specified in the SaveCCM modeling language. It is implemented as an extension of the U PPAAL model checking engine and can interface with the SAVE-IDE modeling environment. Case studies demonstrate the tool's ability to analyze component models of systems like an adaptive cruise controller and a turntable production unit.
This document discusses automata-based programming and control. It proposes representing programs as systems of automated control objects, with behavior described using interacting finite state machines. Advantages include formal verification and generation of code directly from automata specifications. The approach aims to improve software quality by specifying programs visually with automata instead of traditional text-based coding. Several examples of industrial information control systems developed using this approach are also mentioned.
On an LAS-integrated soft PLC system based on WorldFIP fieldbusISA Interchange
Communication efficiency is lowered and real-time performance is not good enough in discrete control based on traditional WorldFIP field intelligent nodes in case that the scale of control in field is large. A soft PLC system based on WorldFIP fieldbus was designed and implemented. Link Activity Scheduler (LAS) was integrated into the system and field intelligent I/O modules acted as networked basic nodes. Discrete control logic was implemented with the LAS-integrated soft PLC system. The proposed system was composed of configuration and supervisory sub-systems and running sub-systems. The configuration and supervisory sub-system was implemented with a personal computer or an industrial personal computer; running subsystems were designed and implemented based on embedded hardware and software systems. Communication and schedule in the running subsystem was implemented with an embedded sub-module; discrete control and system self-diagnosis were implemented with another embedded sub-module. Structure of the proposed system was presented. Methodology for the design of the sub-systems was expounded. Experiments were carried out to evaluate the performance of the proposed system both in discrete and process control by investigating the effect of network data transmission delay induced by the soft PLC in WorldFIP network and CPU workload on resulting control performances. The experimental observations indicated that the proposed system is practically applicable.
This material provides guidelines in form of a presentation of the Context Awareness - component of the Adaptation Plane.
The Context Awareness is a component which implements a mechanism to identify the current context under which the CITADEL framework as well as an application is used/operated.
To identify the current context, the Context Awareness will use run-time data provided by the Monitoring Plane as input on one hand and a pre-defined context model on the other hand.
Tracking and control problem of an aircraftANSUMAN MISHRA
Here our main focus is to monitor and maneuver the flight for a particular distance in a time-scale with absolute control. For this a rigorous formulation of flight mechanics and theories associated with advanced control systems are simplified and analyzed to obtain a feasible & optimized solution.
It is also important to remember that this idea basically involves handling problems of maneuvering control and other pilot-issues of an inner-loop flight-control system and does not dwell on outer loop control systems .
The operational significance of this maneuver is that it allows the pilot to slew quickly without increasing the normal acceleration and turning.
This document discusses the configuration of a state monitoring module. It describes generating monitors for components, sensors for input ports, and converting monitoring properties into policies. The document also outlines the monitoring library generator, generic and CITADEL APIs, supported SLIM types and operators, and examples of initialization and monitoring loops.
Optimal and pid controller for controlling camera’s position in unmanned aeri...Zac Darcy
This paper describes two controllers designed specifically for adjusting camera’s position in a small unmanned aerial vehicle (UAV). The optimal controller was designed and first simulated by using MATLAB technique and the results displayed graphically, also PID controller was designedand simulatedby using MATLAB technique .The goal of this paper is to connect the tow controllers in cascade mode to obtain the desired performance and correction in camera’s position in both roll and pitch.
Modern Tools for the Small-Signal Stability Analysis and Design of FACTS Assi...Power System Operation
There has recently been an intense development of eigenanalysis tools for power systems dynamics and control. This paper provides an up-to-date review of the major algorithms available. Comments on other relevant but yet unpublished algorithms are also made.
The conventional state-space description is obtained through the elimination of the algebraic variables of the mathematical model. In many applications, the power system case included, the algebraic variables in the model are usually more numerous than the state variables.
The problem of multiple, decentralized controller synthesis in large, FACTS assisted power systems is addressed.
A report in CIGRE [1] recognized the large benefits of working with the unreduced set of differential-algebraic equations linearized at an operating point. The resulting power system Jacobian is large and highly sparse, allowing efficient use of sparsity oriented programming. The computation of all system eigenvalues, not practical for large power systems, was since then replaced by the computation of only the eigenvalues of interest.
A good part of the paper is dedicated to showing the high productivity gains achieved when using a well designed package for graphical display and animation of results.
The pressing needs for better utilization of existing transmission and generation equipment will eventually dictate a wider use of FACTS devices. The higher complexity and stricter requirements on power system controls, under both steady-state and dynamic conditions, calls for the immediate development and use of more sophisticated computer tools. The material in this paper may help the further development of one of these tools.
Many important developments occurred in the last fifteen
This document describes U PPAAL PORT, a new tool for component-based design and analysis of embedded systems. U PPAAL PORT uses partial-order reduction techniques to efficiently model check hierarchical component models specified in the SaveCCM modeling language. It is implemented as an extension of the U PPAAL model checking engine and can interface with the SAVE-IDE modeling environment. Case studies demonstrate the tool's ability to analyze component models of systems like an adaptive cruise controller and a turntable production unit.
This document discusses automata-based programming and control. It proposes representing programs as systems of automated control objects, with behavior described using interacting finite state machines. Advantages include formal verification and generation of code directly from automata specifications. The approach aims to improve software quality by specifying programs visually with automata instead of traditional text-based coding. Several examples of industrial information control systems developed using this approach are also mentioned.
On an LAS-integrated soft PLC system based on WorldFIP fieldbusISA Interchange
Communication efficiency is lowered and real-time performance is not good enough in discrete control based on traditional WorldFIP field intelligent nodes in case that the scale of control in field is large. A soft PLC system based on WorldFIP fieldbus was designed and implemented. Link Activity Scheduler (LAS) was integrated into the system and field intelligent I/O modules acted as networked basic nodes. Discrete control logic was implemented with the LAS-integrated soft PLC system. The proposed system was composed of configuration and supervisory sub-systems and running sub-systems. The configuration and supervisory sub-system was implemented with a personal computer or an industrial personal computer; running subsystems were designed and implemented based on embedded hardware and software systems. Communication and schedule in the running subsystem was implemented with an embedded sub-module; discrete control and system self-diagnosis were implemented with another embedded sub-module. Structure of the proposed system was presented. Methodology for the design of the sub-systems was expounded. Experiments were carried out to evaluate the performance of the proposed system both in discrete and process control by investigating the effect of network data transmission delay induced by the soft PLC in WorldFIP network and CPU workload on resulting control performances. The experimental observations indicated that the proposed system is practically applicable.
This material provides guidelines in form of a presentation of the Context Awareness - component of the Adaptation Plane.
The Context Awareness is a component which implements a mechanism to identify the current context under which the CITADEL framework as well as an application is used/operated.
To identify the current context, the Context Awareness will use run-time data provided by the Monitoring Plane as input on one hand and a pre-defined context model on the other hand.
Tracking and control problem of an aircraftANSUMAN MISHRA
Here our main focus is to monitor and maneuver the flight for a particular distance in a time-scale with absolute control. For this a rigorous formulation of flight mechanics and theories associated with advanced control systems are simplified and analyzed to obtain a feasible & optimized solution.
It is also important to remember that this idea basically involves handling problems of maneuvering control and other pilot-issues of an inner-loop flight-control system and does not dwell on outer loop control systems .
The operational significance of this maneuver is that it allows the pilot to slew quickly without increasing the normal acceleration and turning.
This document discusses the configuration of a state monitoring module. It describes generating monitors for components, sensors for input ports, and converting monitoring properties into policies. The document also outlines the monitoring library generator, generic and CITADEL APIs, supported SLIM types and operators, and examples of initialization and monitoring loops.
Optimal and pid controller for controlling camera’s position in unmanned aeri...Zac Darcy
This paper describes two controllers designed specifically for adjusting camera’s position in a small unmanned aerial vehicle (UAV). The optimal controller was designed and first simulated by using MATLAB technique and the results displayed graphically, also PID controller was designedand simulatedby using MATLAB technique .The goal of this paper is to connect the tow controllers in cascade mode to obtain the desired performance and correction in camera’s position in both roll and pitch.
Modern Tools for the Small-Signal Stability Analysis and Design of FACTS Assi...Power System Operation
There has recently been an intense development of eigenanalysis tools for power systems dynamics and control. This paper provides an up-to-date review of the major algorithms available. Comments on other relevant but yet unpublished algorithms are also made.
The conventional state-space description is obtained through the elimination of the algebraic variables of the mathematical model. In many applications, the power system case included, the algebraic variables in the model are usually more numerous than the state variables.
The problem of multiple, decentralized controller synthesis in large, FACTS assisted power systems is addressed.
A report in CIGRE [1] recognized the large benefits of working with the unreduced set of differential-algebraic equations linearized at an operating point. The resulting power system Jacobian is large and highly sparse, allowing efficient use of sparsity oriented programming. The computation of all system eigenvalues, not practical for large power systems, was since then replaced by the computation of only the eigenvalues of interest.
A good part of the paper is dedicated to showing the high productivity gains achieved when using a well designed package for graphical display and animation of results.
The pressing needs for better utilization of existing transmission and generation equipment will eventually dictate a wider use of FACTS devices. The higher complexity and stricter requirements on power system controls, under both steady-state and dynamic conditions, calls for the immediate development and use of more sophisticated computer tools. The material in this paper may help the further development of one of these tools.
Many important developments occurred in the last fifteen
A WORKSPACE SIMULATION FOR TAL TR-2 ARTICULATED ROBOT IAEME Publication
This paper discusses about simulation. Simulation is optimizing system performance. It is an unobtrusive scientific method of enquiry involving experiments rather than with the portion of reality that the model represents. Simulation is nothing but a result generation of system performance data.Simulation is often used to identify the better of the two alternatives.
IRJET - Airplane Crash Analysis and Prediction using Machine LearningIRJET Journal
This document discusses research on analyzing and predicting airplane crashes using machine learning techniques. The researchers conducted an analysis of airplane crash data, correlating it with accident factors. They used supervised machine learning algorithms like SVM, K-NN, AdaBoost and XGBoost for classification and prediction. Feature selection was used to choose the most relevant features for improving accuracy. The algorithms were trained and tested on datasets, with the most accurate one used for prediction to determine if a flight was "safe" or at "crash" risk based on input specifications. The goal was to help the aviation industry improve safety by better understanding factors that contribute to crashes.
Design of a Controller for Systems with Simultaneously Variable Parametersijtsrd
The contribution of this paper is in suggesting an analysis and design of a control system with variable parameters By applying the recommended by the author method of the Advanced D-partitioning the system's stability can be analyzed in details The method defines regions of stability in the space of the system's parameters The designed controller is enforcing desired system performance The suggested technique for analysis and design is essential and beneficial for the further development of control theory in this area Prof. Kamen Yanev "Design of a Controller for Systems with Simultaneously Variable Parameters" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-2 | Issue-6 , October 2018, URL: http://www.ijtsrd.com/papers/ijtsrd18440.pdf
This document discusses configuring communications monitoring by implementing features and signatures from network traffic and learning a white-box model. It describes extracting feature values from packet fields using Python expressions and gathering them in a feature file. Signatures are defined as Python boolean expressions mapped to alert IDs. A white-box model is learned from a training set and stored in a histograms file, which can be tuned by adjusting likelihood values and bins. The steps are demonstrated on a bottle filling plant use case monitoring Modbus traffic.
DEVELOPMENT OF FUZZY LOGIC LQR CONTROL INTEGRATION FOR AERIAL REFUELING AUTOP...Ahmed Momtaz Hosny, PhD
This document summarizes research on integrating fuzzy logic control with linear quadratic regulator (LQR) control for an aerial refueling autopilot. It describes modeling an aircraft, applying LQR control alone and with fuzzy logic control integrated. The integrated LQR fuzzy control is shown to more effectively suppress uncertainties and minimize mission time compared to LQR alone. Key aspects covered include aircraft modeling, optimal LQR flight control, applying fuzzy inference systems, deriving fuzzy rules, and the integrated LQR fuzzy control structure applied to pitch and lateral control for aerial refueling simulations.
STATE OBSERVER DESIGNS FOR QUARTER-CAR PASSIVE SUSPENSIONijccmsjournal
This paper presents state observer designs for quarter-car passive suspension. Proposed designs correspond to two theories, full-order state observer and observer on closed-loop system. Those observers are used for states and estimation errors observation. Simulation is done using MATLAB and SIMULINK. MATLAB is used to calculate both feedback gain matrix and observer gain matrix whereas SIMULINK is applied to build state space block. Results show that those observers work effectively and fit observer theories. This work may motivate to continue to other steps of observer designs, observer designs for halfcar and full car passive suspension.
muhammad zahid is the verry nice engineer in indus university...zawalbaloch75
This document describes the design of a flight stabilization system for an unmanned aerial vehicle (UAV) using hardware-in-the-loop (HIL) testing. Controllers were designed separately for longitudinal and lateral flight axes using simulations. The controllers successfully stabilized straight and level flight in HIL tests. The document discusses the aircraft dynamics, controller designs for elevators and ailerons, multivariable control system design, and HIL test platform used to validate the controllers.
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.
Design and Implementation of Model Reference Adaptive Controller using Coeffi...IOSR Journals
This document describes the design and implementation of a model reference adaptive controller (MRAC) using the coefficient diagram method (CDM) for a nonlinear process. It begins by introducing MRAC for single-input single-output plants, developing the MRAC design and control law. It then provides basics of the CDM design approach. The document applies the CDM-MRAC to a spherical tank level process in simulation, comparing its performance to a linear PI controller. Simulation results show the CDM-MRAC has faster rise time and settling time than the PI controller.
Model predictive control (MPC) is an advanced contr
ol algorithm that has been very successful in the
control industries due to its capability of handlin
g multi input multi output (MIMO) systems with phys
ical
constraints. In MPC, the control action are obtaine
d by solving a constrained optimization problem at
every sample interval to minimize the difference be
tween the predicted outputs and the reference value
through the using of minimum control energy and sat
isfying the constraints of the physical system.
Quadratic programing (QP) problem is solved using Q
PKWIK method which improves the active set
method. The system architecture and design for the
implementation of online MPC on the FPGA is taken
into consideration in this paper to control a DC mo
tor. This implementation is completed using Spartan
6
Nexys3 FPGA chip using simulation environment (EDK
tool) and the comparison between MPC and PID
controller is also established.
A Comparison of Closed-Loop Performance of MULTIROTOR Configurations using No...IRJET Journal
This document presents a comparison of the closed-loop performance of different multirotor configurations (quadrotor, hexacopter, octocopter) using nonlinear dynamic control. It first describes the common properties and differences between the configurations. It then presents the nonlinear dynamic model of the multirotors derived using Newton-Euler equations. Three control algorithms are analyzed - backstepping, sliding mode, and a hybrid backstepping/Frenet-Serret Theory controller. Simulation experiments show the performance of the control techniques in terms of dynamic performance, stability, and disturbance rejection. The conclusion proposes hybrid control systems that combine advantages of multiple control philosophies.
IRJET- Quadrotor Modeling and Control using PID TechniqueIRJET Journal
The document describes modeling and PID control of a quadrotor unmanned aerial vehicle. It presents the quadrotor model and equations of motion. PID controllers are designed and tuned for roll, pitch, yaw, and altitude control. Simulation results show the PID controllers provide stable response for the system with good rise times and minimal overshoot and steady state error for attitude angles. The altitude response has longer rise time and some overshoot and steady state error. Overall, the PID control strategy successfully stabilized the quadrotor model.
This document presents research on developing real-time adaptive feedforward control for an XY table system. The researchers identified mathematical models of the XY table plant using system identification techniques. They obtained both minimum phase and non-minimum phase models by varying the sampling time during data collection. They then developed and tested two types of feedforward zero phase error tracking controllers on the system models. Experimental results showed that the modified controller improved tracking performance for both minimum and non-minimum phase systems.
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.
The document discusses the generation of sequential state vectors over time. It notes that the functional description can be found in a referenced paper, that an Excel operationalization will be released online after publication, and that a simplified animation visualizes the movement of an aspect of the state vector through a system space.
ROBOT HYBRID AND FORCE CONTROL IN MULTI-MICROPROCESSOR SYSTEM AnuShka Yadav
This document discusses a multi-microprocessor system for controlling the position and force of a walking robot in real time. It presents the implementation of an open architecture system that uses forward and inverse kinematics to control the robot's position in Cartesian coordinates. Experimental results showed that the open architecture control system ensured flexibility, short execution time, precision targeting and repeatability of movement programs compared to a single microprocessor system.
The document provides an introduction to control systems engineering, defining key terms like controlled variable, manipulated variable, and feedback control. It describes the basic components and configurations of control systems, including open-loop and closed-loop designs. The introduction also covers analysis and design objectives for control systems, like transient response, steady-state response, and stability. It outlines the typical design process and gives examples of control system applications in various fields like aerospace, manufacturing, and power generation.
Design the implementation of CDEx Robust DC Motor.Ankita Tiwari
This document describes an experiment using LabVIEW to design and implement a robust DC motor controller. It discusses:
1. The apparatus used, including the LabVIEW software and computer specifications.
2. An overview of LabVIEW, describing it as a visual programming language where programs are created by connecting functional nodes with wires to control data flow.
3. The procedure for the experiment, which involves modeling the DC motor and controller, discretizing the controller, and performing time and frequency response simulations to analyze robustness.
Study of model predictive control using ni lab viewIAEME Publication
This document discusses the implementation of model predictive control (MPC) using National Instruments LabVIEW software. It begins with introductions to MPC and LabVIEW. It then covers constructing state space and transfer function models in LabVIEW. Simulation results are presented for MPC applied to first order systems with and without time delay. MPC performance is compared to PID control, showing MPC can handle constraints and optimize process operation while PID cannot. The document concludes MPC simulation using LabVIEW is successful and simulation results are useful for control system design.
Study of model predictive control using ni lab viewiaemedu
This document discusses the implementation of model predictive control (MPC) using National Instruments LabVIEW software. It begins with introductions to MPC and LabVIEW. It then covers constructing state space and transfer function models in LabVIEW. Simulation results are presented for MPC applied to first order systems with and without time delay. MPC performance is compared to PID control, showing MPC can handle constraints and optimize process operation while PID cannot. The document concludes MPC simulation using LabVIEW is successful and simulation results are useful for control system design.
Study of model predictive control using ni lab viewiaemedu
This document discusses the implementation of model predictive control (MPC) using National Instruments LabVIEW software. It begins with introductions to MPC and LabVIEW. It then covers constructing state space and transfer function models in LabVIEW. Simulation results are presented for MPC applied to first order systems with and without time delay. MPC performance is compared to PID control, showing MPC can handle constraints and optimize process operation while PID cannot. The document concludes MPC simulation using LabVIEW is successful and simulation results are useful for control system design.
An Unmanned Rotorcraft System with Embedded DesignIOSR Journals
This document describes the design and implementation of an embedded control system for an unmanned rotorcraft. It uses a backstepping control law with state estimation provided by an extended Kalman filter using data from a marker-based vision system and inertial measurement unit. A self-organizing map is used to select local operating regimes for modeling the nonlinear dynamics. The control algorithm was tested in a hardware-in-the-loop simulation and able to track spiral paths in 3D space with the embedded controller implemented on a Freescale MPC555 processor.
A WORKSPACE SIMULATION FOR TAL TR-2 ARTICULATED ROBOT IAEME Publication
This paper discusses about simulation. Simulation is optimizing system performance. It is an unobtrusive scientific method of enquiry involving experiments rather than with the portion of reality that the model represents. Simulation is nothing but a result generation of system performance data.Simulation is often used to identify the better of the two alternatives.
IRJET - Airplane Crash Analysis and Prediction using Machine LearningIRJET Journal
This document discusses research on analyzing and predicting airplane crashes using machine learning techniques. The researchers conducted an analysis of airplane crash data, correlating it with accident factors. They used supervised machine learning algorithms like SVM, K-NN, AdaBoost and XGBoost for classification and prediction. Feature selection was used to choose the most relevant features for improving accuracy. The algorithms were trained and tested on datasets, with the most accurate one used for prediction to determine if a flight was "safe" or at "crash" risk based on input specifications. The goal was to help the aviation industry improve safety by better understanding factors that contribute to crashes.
Design of a Controller for Systems with Simultaneously Variable Parametersijtsrd
The contribution of this paper is in suggesting an analysis and design of a control system with variable parameters By applying the recommended by the author method of the Advanced D-partitioning the system's stability can be analyzed in details The method defines regions of stability in the space of the system's parameters The designed controller is enforcing desired system performance The suggested technique for analysis and design is essential and beneficial for the further development of control theory in this area Prof. Kamen Yanev "Design of a Controller for Systems with Simultaneously Variable Parameters" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-2 | Issue-6 , October 2018, URL: http://www.ijtsrd.com/papers/ijtsrd18440.pdf
This document discusses configuring communications monitoring by implementing features and signatures from network traffic and learning a white-box model. It describes extracting feature values from packet fields using Python expressions and gathering them in a feature file. Signatures are defined as Python boolean expressions mapped to alert IDs. A white-box model is learned from a training set and stored in a histograms file, which can be tuned by adjusting likelihood values and bins. The steps are demonstrated on a bottle filling plant use case monitoring Modbus traffic.
DEVELOPMENT OF FUZZY LOGIC LQR CONTROL INTEGRATION FOR AERIAL REFUELING AUTOP...Ahmed Momtaz Hosny, PhD
This document summarizes research on integrating fuzzy logic control with linear quadratic regulator (LQR) control for an aerial refueling autopilot. It describes modeling an aircraft, applying LQR control alone and with fuzzy logic control integrated. The integrated LQR fuzzy control is shown to more effectively suppress uncertainties and minimize mission time compared to LQR alone. Key aspects covered include aircraft modeling, optimal LQR flight control, applying fuzzy inference systems, deriving fuzzy rules, and the integrated LQR fuzzy control structure applied to pitch and lateral control for aerial refueling simulations.
STATE OBSERVER DESIGNS FOR QUARTER-CAR PASSIVE SUSPENSIONijccmsjournal
This paper presents state observer designs for quarter-car passive suspension. Proposed designs correspond to two theories, full-order state observer and observer on closed-loop system. Those observers are used for states and estimation errors observation. Simulation is done using MATLAB and SIMULINK. MATLAB is used to calculate both feedback gain matrix and observer gain matrix whereas SIMULINK is applied to build state space block. Results show that those observers work effectively and fit observer theories. This work may motivate to continue to other steps of observer designs, observer designs for halfcar and full car passive suspension.
muhammad zahid is the verry nice engineer in indus university...zawalbaloch75
This document describes the design of a flight stabilization system for an unmanned aerial vehicle (UAV) using hardware-in-the-loop (HIL) testing. Controllers were designed separately for longitudinal and lateral flight axes using simulations. The controllers successfully stabilized straight and level flight in HIL tests. The document discusses the aircraft dynamics, controller designs for elevators and ailerons, multivariable control system design, and HIL test platform used to validate the controllers.
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.
Design and Implementation of Model Reference Adaptive Controller using Coeffi...IOSR Journals
This document describes the design and implementation of a model reference adaptive controller (MRAC) using the coefficient diagram method (CDM) for a nonlinear process. It begins by introducing MRAC for single-input single-output plants, developing the MRAC design and control law. It then provides basics of the CDM design approach. The document applies the CDM-MRAC to a spherical tank level process in simulation, comparing its performance to a linear PI controller. Simulation results show the CDM-MRAC has faster rise time and settling time than the PI controller.
Model predictive control (MPC) is an advanced contr
ol algorithm that has been very successful in the
control industries due to its capability of handlin
g multi input multi output (MIMO) systems with phys
ical
constraints. In MPC, the control action are obtaine
d by solving a constrained optimization problem at
every sample interval to minimize the difference be
tween the predicted outputs and the reference value
through the using of minimum control energy and sat
isfying the constraints of the physical system.
Quadratic programing (QP) problem is solved using Q
PKWIK method which improves the active set
method. The system architecture and design for the
implementation of online MPC on the FPGA is taken
into consideration in this paper to control a DC mo
tor. This implementation is completed using Spartan
6
Nexys3 FPGA chip using simulation environment (EDK
tool) and the comparison between MPC and PID
controller is also established.
A Comparison of Closed-Loop Performance of MULTIROTOR Configurations using No...IRJET Journal
This document presents a comparison of the closed-loop performance of different multirotor configurations (quadrotor, hexacopter, octocopter) using nonlinear dynamic control. It first describes the common properties and differences between the configurations. It then presents the nonlinear dynamic model of the multirotors derived using Newton-Euler equations. Three control algorithms are analyzed - backstepping, sliding mode, and a hybrid backstepping/Frenet-Serret Theory controller. Simulation experiments show the performance of the control techniques in terms of dynamic performance, stability, and disturbance rejection. The conclusion proposes hybrid control systems that combine advantages of multiple control philosophies.
IRJET- Quadrotor Modeling and Control using PID TechniqueIRJET Journal
The document describes modeling and PID control of a quadrotor unmanned aerial vehicle. It presents the quadrotor model and equations of motion. PID controllers are designed and tuned for roll, pitch, yaw, and altitude control. Simulation results show the PID controllers provide stable response for the system with good rise times and minimal overshoot and steady state error for attitude angles. The altitude response has longer rise time and some overshoot and steady state error. Overall, the PID control strategy successfully stabilized the quadrotor model.
This document presents research on developing real-time adaptive feedforward control for an XY table system. The researchers identified mathematical models of the XY table plant using system identification techniques. They obtained both minimum phase and non-minimum phase models by varying the sampling time during data collection. They then developed and tested two types of feedforward zero phase error tracking controllers on the system models. Experimental results showed that the modified controller improved tracking performance for both minimum and non-minimum phase systems.
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.
The document discusses the generation of sequential state vectors over time. It notes that the functional description can be found in a referenced paper, that an Excel operationalization will be released online after publication, and that a simplified animation visualizes the movement of an aspect of the state vector through a system space.
ROBOT HYBRID AND FORCE CONTROL IN MULTI-MICROPROCESSOR SYSTEM AnuShka Yadav
This document discusses a multi-microprocessor system for controlling the position and force of a walking robot in real time. It presents the implementation of an open architecture system that uses forward and inverse kinematics to control the robot's position in Cartesian coordinates. Experimental results showed that the open architecture control system ensured flexibility, short execution time, precision targeting and repeatability of movement programs compared to a single microprocessor system.
The document provides an introduction to control systems engineering, defining key terms like controlled variable, manipulated variable, and feedback control. It describes the basic components and configurations of control systems, including open-loop and closed-loop designs. The introduction also covers analysis and design objectives for control systems, like transient response, steady-state response, and stability. It outlines the typical design process and gives examples of control system applications in various fields like aerospace, manufacturing, and power generation.
Similar to CONCEPT OF OPERATIONS TO SYSTEM DESIGN AND DEVELOPMENT-AN INTEGRATED SYSTEM FOR AIRCRAFT MISSION FEASIBILITY ANALYSIS USING STK ENGINE, MATLAB AND LABVIEW
Design the implementation of CDEx Robust DC Motor.Ankita Tiwari
This document describes an experiment using LabVIEW to design and implement a robust DC motor controller. It discusses:
1. The apparatus used, including the LabVIEW software and computer specifications.
2. An overview of LabVIEW, describing it as a visual programming language where programs are created by connecting functional nodes with wires to control data flow.
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CONCEPT OF OPERATIONS TO SYSTEM DESIGN AND DEVELOPMENT-AN INTEGRATED SYSTEM FOR AIRCRAFT MISSION FEASIBILITY ANALYSIS USING STK ENGINE, MATLAB AND LABVIEW
1. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
DOI : 10.5121/ijics.2015.5401 1
CONCEPT OF OPERATIONS TO SYSTEM DESIGN
AND DEVELOPMENT-AN INTEGRATED SYSTEM
FOR AIRCRAFT MISSION FEASIBILITY ANALYSIS
USING STK ENGINE, MATLAB AND LABVIEW
Princy Randhawa 1
and Vijay Shanthagiri 2
Assistant Professor, Department of Mechatronics Engineering, Manipal University Jaipur
Principle System Engineer, Oeuvre Software Solutions, Bangalore
ABSTRACT
In recent times, there has been a significant rise in usage of aircrafts in surveillance and reconnaissance
missions. Not all the aircrafts survive the harsh testing conditions put forth by the enemy regions. Aircraft
Survivability Analysis gives the measure of the chances of survival for different counter strategies. The
mission would be recalculated if particular sortie does not fall within the physical boundary of the
performance of an aircraft. This is required both for the success of the mission and the survivability of the
aircraft in the harsh enemy conditions.
A system is envisioned comprising of the accurate modeling of the physical world and the accurate model
of control system. An interoperable system which can work seamlessly together will provide mission
planners, System integrators, aeronautical/aerospace engineers a milieu wherein the Control System
designer who is found wanted as far as the physical world is concerned is given a system which can
simulate the real world in lab conditions. To achieve this, we combine the two most promising
environments prevalent in the industry today namely Systems tool kit for modeling the operational
environment MATLAB and LabVIEW for modeling the control system environment. Using a Math script
window of LabVIEW, we have designed the aircraft model and controlling the variables of an aircraft
using a simulation loop of a LabVIEW. The different flight conditions were arrived using Orthogonal Array
(OA) based on different Aircraft weight, Altitude, Mach number configurations. This attempts to span the
aircrafts across the regimes in aircrafts flight envelope. A system comprising of both, with seamless UDP
based connection between the two is developed to expedite the process of development of feasible control
system design and verification which allows the aircrafts to undertake complex mission. This system we
believe would answer questions of limits of the aircrafts maneuverability and survivability in terms of its
limitation concerning control system design and development of commercial fighter aircrafts, UAV's and
Quad copters.
INDEX TERMS
Aerospace control, Aircraft navigation,
KEYWORDS
Aircrafts, Control System, Navigation guidance and control, Aircraft mission planning Line-of-sight,
Systems Tool Kit, LabVIEW, Control design, Closed Loop System.
2. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
2
1. INTRODUCTION
To connect the physical world with the control system environment is to have given the designer
a debugging feature unlike never before. It is advantageous if an attempt to finalize a control
system design is supported or criticized not by heuristics or intuitive insights based on experience
but by a real system which models a system connected to a control system design environment.
While all these days, the feedback loop would ensure stability of a process or a system, it is
assured here that a feedback for verifying a systems stability, controllability, observability is
verified for different dynamically created mission paths and not just a small set of paths which are
usually available due to lack of simulating environment. In other words, this paper is about
connecting a highly accurate simulating environment such as STK with a highly accurate and user
friendly Instrument Design and Control system design environment such as LabVIEW.
2. MISSION PLANNING ON SYSTEMS TOOL KIT
Systems Tool Kit the user with the following important inputs for simulating the mission path
Scenario configuration: – Set Units; Set Epoch; Set Time Period
Way Point Creation: – Click and Create Waypoints on Aircraft mission modeler; plan
CAP mission, Refueling , Reconnaissance mission and other critical mission paths
Animation setup and control: – Animate Set-Values, Set-Time; Start Forward
Vehicle attitude initialization example:–Set-Attitude */Launch Vehicle/L1 Profile Fixed
Euler 91.1 80.9 0.0 323 "Facility/WFF_Pad_1 Body".
Aircraft simulated live data: – Get position of each simulated point and other values
pertaining to aerodynamic attributes such as Pitch, Yaw, and Roll Turn Radius in time.
Fig 1: STK's Simulation Environment concerning Aircrafts Attitude, Pitch, Roll and Yaw.
3. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
3
3. AIRCRAFT CONTROL SYSTEM DESIGN ON LABVIEW
LabVIEW is a graphical programming environment that has very powerful numeric array
and string handling capabilities, and easy numeric to string conversion.
LabVIEW has good capability to model complex control system design. It provides user
friendly virtual instrumentation environment to iterate and dynamically update control
values into it.
Building user interface is very simple.
Basic TCP functions built in – Open, Write, Read, Close Connection.
Fig 2: LabVIEW Design and Simulation Environment with Control System Block Diagram
4. INTEGRATING STK AND LABVIEW
It is envisioned that STK will connected to LabVIEW using UDP Connection. Since the
data rate is not too high TCP/IP connection can also be used.
The events leading to invocation and information exchange between STK and LabVIEW
will be delineated.
The Message structures with coded heading will be agreed between both the parties.
Fig. 3: Block Diagram of the integrated system and the information flow.
4. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
4
Fig. 4: STK's Simulation Environment concerning Waypoint Creation of Aircrafts
The mutual data flow will be though structures containing the information. A Message Structure
of TYPE1 is as follows.
[Message Struct Type 1]
{
int16 Message Header
int16 Message Type
char[50] AicraftName
double Latitude
double Longitude
double Pitch
double Roll
double Yaw
double Pitch Rate
double Roll Rate
double Yaw Rate
double Velocity
double Epoch Time
}
The message is received by LabVIEW over a preselected socket and interpreted.
5. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
5
Fig. 5: Behind the scenes of LabVIEW where the Control System Schema is rigged to receive external
inputs through instruments assigned to produce the signals.
Fig. 6: Dynamic Data Creation Panel where data is received though a socket and connected
6. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
6
The information flow between STK and LabVIEW is shown below.STK used here with its engine
and a c# based application is used to invoke the engine. This makes it easy to gain full control
over the data transfer without too much UI interaction for the user. The way points created as
shown in Fig 6 is directly converted and sent over the socket to Lab View’s port for stability
analysis of the path.
The sequential flow between STK engine and LabVIEW is shown below.
Fig. 7: Sequence Diagram of the integrated system and the information flow
5. USE CASE WITH RESULTS - CONTROL SYSTEM DESIGN OF A
COMMERCIAL AIRCRAFT USING STK AND LABVIEW
For designing a plant model through LabVIEW Simulation loop, we need a longitudinal equation.
For the dynamics of a longitudinal aircraft, we need variables which are (small) deviations from
operating point or trim conditions. These small deviations are created by first modelling the
aircraft path on Systems Took Kit and then streaming the delta change in u, α, θ ,q with respect
to time.
• u : velocity of aircraft along body axis
• α : angle of attack (the angle between the velocity vector and the x-axis of the
aircraft
• θ : Angle between body axis and horizontal (up is positive)
q =
.
θ : Angular velocity of aircraft (pitch rate)
7. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
7
INPUTS
Control or actuator inputs:
• eδ : Elevator angle ( eδ >0 is down)
If we introduce the longitudinal state variable vector
x = [u α qθ ]
and the longitudinal control vector
)(tu = [ eδ ]
These equations are equivalent to the system of first-order equations )(txIn
•
= )()( tButAx +
)()()( tDutCty +=
where: a A—State matrix (n× n)
B—Input matrix (n× m)
C—Output matrix (r × n)
a D—Direct matrix (r ×m)
x (t)—column vector of n state variables
u (t)—column vector of m input variables
y (t)—column vector of n output variables
•
x represent the time derivative of the state vector x, and the matrices appearing in this equation
are
An=
−
+
−
0100
0
sin
cos0
0
00
0
00
00
00
qu
u
MMM
u
g
u
uZ
u
Z
u
Z
gXXu
α
α θθ
θθα
Fig. 8: State Space Equation of an Aircraft plant model
8. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
8
Thus, transfer function for output variable u with respect to elevator deflection is presented in Fig
9
)(
)(
se
su
δ
0008952.0005087.02^8295.03^2388.04^
01012.05849.02^2504.03^015721.1
++++
+−−−
ssss
ssse
Thus, transfer function for output variable α with respect to elevator is presented as follows
shown in Fig 9
)(
)(
se
s
δ
α
0008952.0005087.02^8295.03^2388.04^
0009804.0001072.0_2^009529.03^003388.0
++++
−−−
ssss
sss
Thus, transfer function for output variable q with respect to elevator deflection is presented as
shown in Fig 10.
)(
)(
se
sq
δ 0008952.0005087.02^8295.03^2388.04^
019674.8007502.02^002106.03^009151.0
++++
−+−−−
ssss
esss
Thus, transfer function for output variable θ with respect to elevator deflection is presented and
shown in Fig 10
)(
)(
se
s
δ
θ
006613.3001754.02^8295.03^2388.04^
007502.0002106.02^009151.03^017551.5
−++++
−−−−−
essss
ssse
Fig 9: Longitudinal Aircraft Response for velocity (m/se) and angle of attack (deg) v/s time (sec) to 1 deg
Elevator Step Input
9. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
9
Fig 10: Longitudinal Aircraft Response for pitch rate (deg/se) and pitch attitude (deg) v/s time (sec) to 1
deg Elevator Step Input
We will begin with an analysis of how an aircraft will behave in the pitch when it is controlled
solely by the elevator. Figure 11 shows the poles are on the L.H.S determines the stability of
plant. The poles near to the origin show Phugoid mode and the poles far from the origin shows
short period mode. It infers that at very high weight with less altitude, the Mach no. should be
less (velocity). It was assumed that the control surfaces (elevator) have certain limits on the
deflection. Figure 12 shows the typical variations of elevator deflection versus aircraft speed to
maintain aircraft longitudinal trim. Figure 13 shows the response of elevator control defection of
1-deg step input for
Fig. 11: Pole Zero map of short period and Phugoid mode.
Phugoid periodShort period mode
10. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
10
Fig. 12: Typical variations of elevator deflection versus aircraft speed
Fig. 13: Elevator control deflection for 1-deg Elevator step Input
11. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
11
Fig. 14: Controllability Matrix
Figure 14 shows the controllability matrix which depends on the coefficients matrixes A and B
which states that plant can be controllable by seeing control input. if Qc≠0 (Controllable) or vice
versa.
It must be noted here that this above calculation is repeated for every input from STK to
LabVIEW. The math script which models the system is invoked repeatedly for newer values and
a feed back is sent as to whether the performance of the system is within the expected ranges of
stability and controllability. A system which can respond successfully to almost all kinds of
mission paths can then be given a go for production of prototype and field testing.
It is easy to note here that the effort to integrate STK, LabVIEW along with Math script ensures
that the mission/operations of various kinds are tested before the agency or organization invests in
real hardware development.
6. APPLICABILITY
The application of such a system spans a whole lot of applications. It is particularly valid in
following use cases
1. Design of Quad Copters with mounted Direction Finder.
2. Design of Drones with validated Survivability analysis in enemy environment.
3. Design of UAV for Intelligence Surveillance and Reconnaissance missions where
maneuvering is remotely done on a UAV which is far from the friendly territory
12. International Journal of Instrumentation and Control Systems (IJICS) Vol.5, No.4, October 2015
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7. FUTURE WORK
With this framework in place, industries can extract the best of STK and LabVIEW. In future, the
same type of set up can be used in the following areas.
1. Satellite Constellation Design
2. Satellite Swarm Design
3. Aircraft Control and Air Defense analysis and validation
4. Model validation of proposed design against uncertainties in the natural environments
8. CONCLUSION
With the above results it can be inferred that system development can be expedited by connecting
a simulation environment with Development environment to get a feed back about one's own
design. The quick results during mission planning ensure that the design which has been
approved for final construction or even a prototype construction is indeed closer to the desired
design. This helps largely in reducing development time and saves energy and repetition of work.
More importantly, it is well know that system design , structural design of aircrafts and flying
object involves large sum of money in construction. What might work in lab condition using
LabVIEW might not work in the real condition in nature due to uncertain condition and different
convoluted use cases which might show up in the real world scenario. here we have brought the
real world scenario to the laboratory so that through use cases are created to validate the design
against different mission plans, aircraft paths to test the response of the control systems against
the path it has to endure.
REFERENCES
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[3] Nilar Lwin, Hla Myo Tun, “ Implementation Of Flight Control System Based On Kalman And PID
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Feedback Attitude Stabilization of a Quadrotor UAV”, International Journal of Information
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