This presentation is about the Fly-By-Wire technology adopted in aircraft systems for greater maneuverability. The mechanical and electronics aspects of this technology is briefed in this presentation.
Smart aerosonde UAV longitudinal flight control system based on genetic algor...journalBEEI
Synthesis of a flight control system for such an aircraft that achieves stable and acceptable performance across a specified flying envelope in the presence of uncertainties represents an attractive and challenging design problem. This study uses the genetic self-tuning PID algorithm to develop an intelligent flight control system for the aerosonde UAV model. To improve the system's transient responses, the gains of the PID controller are improved using a genetic algorithm (GA). Simulink/MATLAB software is used to model and simulate the proposed system. The proposed PID controller integrated with the GA is compared with the classical one. Three simulation scenarios are carried out. In the first scenario, and at normal conditions, the proposed controller performance is better than the classical one. While in the second scenario, identical results are achieved from both controllers. Finally, in the third scenario, the PID controller with GA shows the robustness and durability of the system compared with the classical PID in presence of external wind disturbance. The simulation results prove the system parameters optimization.
This presentation is about the Fly-By-Wire technology adopted in aircraft systems for greater maneuverability. The mechanical and electronics aspects of this technology is briefed in this presentation.
Smart aerosonde UAV longitudinal flight control system based on genetic algor...journalBEEI
Synthesis of a flight control system for such an aircraft that achieves stable and acceptable performance across a specified flying envelope in the presence of uncertainties represents an attractive and challenging design problem. This study uses the genetic self-tuning PID algorithm to develop an intelligent flight control system for the aerosonde UAV model. To improve the system's transient responses, the gains of the PID controller are improved using a genetic algorithm (GA). Simulink/MATLAB software is used to model and simulate the proposed system. The proposed PID controller integrated with the GA is compared with the classical one. Three simulation scenarios are carried out. In the first scenario, and at normal conditions, the proposed controller performance is better than the classical one. While in the second scenario, identical results are achieved from both controllers. Finally, in the third scenario, the PID controller with GA shows the robustness and durability of the system compared with the classical PID in presence of external wind disturbance. The simulation results prove the system parameters optimization.
A type of flight-control system where input command signals are sent to the actuators through the medium of optical-fiber lines. The feedback from the control surfaces and other systems is routed in a similar way. The inputs from the control column, aircraft control surfaces, and other data, such as static and dynamic pressure and angle of attack, are fed into a computer connected to fiber-optic lines. The computer then provides data for movement of the aircraft control surfaces through these cables.
Improvement of Pitch Motion Control of an Aircraft SystemsTELKOMNIKA JOURNAL
The movement of the aircraft pitch is very important to ensure the passengers and crews are in
intrinsically safe and the aircraft achieves its maximum stability.The objective of this study is to provide a
solution to the control system that features particularly on the pitch angle motion of aircraft systemin order
to have a comfort boarding. Three controllers were developed in these projects which wereproportional
integral derivative (PID), fuzzy logic controller (FLC), and linear quadratic regulator (LQR) controllers.
These controllers will help improving the pitch angle and achievingthe target reference. By improving the
pitch motion angle, the flight will be stabilized and in steady cruise (no jerking effect), hence provides all
the passengers withthe comfort zone. Simulation results have been done and analyzed using Matlab
software. The simulation results demonstrated LQR and FLC were better than PID in the pitch motion
system due to the small error performance. In addition, withstrong external disturbances, a single controller
is unable to control the system, thus, the combination of PID and LQR managed to stabilize the aircraft.
Quadcopters are the rotorcraft which have become the catch of the eye in the UAVs, both for electronic hobbyists as well as various application based real time solutions.
Elevation, pitch and travel axis stabilization of 3DOF helicopter with hybrid...IJECEIAES
This research work introduces an efficient hybrid control methodology through combining the traditional proportional-integral-derivative (PID) controller and linear quadratic regulator (LQR) optimal controlher. The proposed hybrid control approach is adopted to design three degree of freedom (3DOF) stabilizing system for helicopter. The gain parameters of the classic PID controller are determined using the elements of the LQR feedback gain matrix. The dynamic behaviour of the LQR based PID controller, is modeled in state space form to enable utlizing state feedback controller technique. The performance of the proposed LQR based LQR controller is improved by using Genetic Algorithm optimization method which are adopted to obtain optimum values for LQR controller gain parameters. The LQR-PID hybrid controller is simulated using Matlab environment and its performance is evaluated based on rise time, settling time, overshoot and steady state error parameters to validate the proposed 3DOF helicopter balancing system. Based on GA tuning approach, the simulation results suggest that the hybrid LQR-PID controller can be effectively employed to stabilize the 3DOF helicopter system.
RC Quadcopters, or multirotors, were on just about everyone's Christmas list. If Santa's present has left you wanting for more (or you just want to tinker!), but you don't know where to start, this course is for you. We'll cover the basics to get you started: tools you'll need, pre-planning, components and how they all go together. I will also show a sample build that features a 3DR Pixhawk flight controller, running open-source firmware ArduPilot (http://dev.ardupilot.com/) and Mission Planner (https://github.com/diydrones/MissionPlanner)
In the past decade Unmanned Aerial Vehicles (UAVs) have become a topic of interest in many research organizations. UAVs are finding applications in various areas ranging from military applications to traffic surveillance. This paper is a survey for a certain kind of UAV called quadrotor or quadcopter. Researchers are frequently choosing quadrotors for their research because a quadrotor can accurately and efficiently perform tasks that would be of high risk for a human pilot to perform. This paper encompasses the dynamic models of a quadrotor and the different model-dependent and model-independent control techniques and their comparison. Recently, focus has shifted to designing autonomous quadrotors. A summary of the various localization and navigation techniques has been given. Lastly, the paper investigates the potential applications of quadrotors and their role in multi-agent systems.
A type of flight-control system where input command signals are sent to the actuators through the medium of optical-fiber lines. The feedback from the control surfaces and other systems is routed in a similar way. The inputs from the control column, aircraft control surfaces, and other data, such as static and dynamic pressure and angle of attack, are fed into a computer connected to fiber-optic lines. The computer then provides data for movement of the aircraft control surfaces through these cables.
Improvement of Pitch Motion Control of an Aircraft SystemsTELKOMNIKA JOURNAL
The movement of the aircraft pitch is very important to ensure the passengers and crews are in
intrinsically safe and the aircraft achieves its maximum stability.The objective of this study is to provide a
solution to the control system that features particularly on the pitch angle motion of aircraft systemin order
to have a comfort boarding. Three controllers were developed in these projects which wereproportional
integral derivative (PID), fuzzy logic controller (FLC), and linear quadratic regulator (LQR) controllers.
These controllers will help improving the pitch angle and achievingthe target reference. By improving the
pitch motion angle, the flight will be stabilized and in steady cruise (no jerking effect), hence provides all
the passengers withthe comfort zone. Simulation results have been done and analyzed using Matlab
software. The simulation results demonstrated LQR and FLC were better than PID in the pitch motion
system due to the small error performance. In addition, withstrong external disturbances, a single controller
is unable to control the system, thus, the combination of PID and LQR managed to stabilize the aircraft.
Quadcopters are the rotorcraft which have become the catch of the eye in the UAVs, both for electronic hobbyists as well as various application based real time solutions.
Elevation, pitch and travel axis stabilization of 3DOF helicopter with hybrid...IJECEIAES
This research work introduces an efficient hybrid control methodology through combining the traditional proportional-integral-derivative (PID) controller and linear quadratic regulator (LQR) optimal controlher. The proposed hybrid control approach is adopted to design three degree of freedom (3DOF) stabilizing system for helicopter. The gain parameters of the classic PID controller are determined using the elements of the LQR feedback gain matrix. The dynamic behaviour of the LQR based PID controller, is modeled in state space form to enable utlizing state feedback controller technique. The performance of the proposed LQR based LQR controller is improved by using Genetic Algorithm optimization method which are adopted to obtain optimum values for LQR controller gain parameters. The LQR-PID hybrid controller is simulated using Matlab environment and its performance is evaluated based on rise time, settling time, overshoot and steady state error parameters to validate the proposed 3DOF helicopter balancing system. Based on GA tuning approach, the simulation results suggest that the hybrid LQR-PID controller can be effectively employed to stabilize the 3DOF helicopter system.
RC Quadcopters, or multirotors, were on just about everyone's Christmas list. If Santa's present has left you wanting for more (or you just want to tinker!), but you don't know where to start, this course is for you. We'll cover the basics to get you started: tools you'll need, pre-planning, components and how they all go together. I will also show a sample build that features a 3DR Pixhawk flight controller, running open-source firmware ArduPilot (http://dev.ardupilot.com/) and Mission Planner (https://github.com/diydrones/MissionPlanner)
In the past decade Unmanned Aerial Vehicles (UAVs) have become a topic of interest in many research organizations. UAVs are finding applications in various areas ranging from military applications to traffic surveillance. This paper is a survey for a certain kind of UAV called quadrotor or quadcopter. Researchers are frequently choosing quadrotors for their research because a quadrotor can accurately and efficiently perform tasks that would be of high risk for a human pilot to perform. This paper encompasses the dynamic models of a quadrotor and the different model-dependent and model-independent control techniques and their comparison. Recently, focus has shifted to designing autonomous quadrotors. A summary of the various localization and navigation techniques has been given. Lastly, the paper investigates the potential applications of quadrotors and their role in multi-agent systems.
Christian Titze, "Hello From the Other Side: Adapting the Agile Agency to Cli...WebVisions
Many agencies have become frustrated with over-specced sequential waterfall projects. Their inflexible methodologies have too often led to outcomes that didn’t realize their full potential. In contrast, agile methods like Scrum and Kanban have proven successful ways to build and run software. But how do you apply agile methods to the reality of an agency’s project based work? There are many challenges and the most crucial question is: what if our ideal work method and our clients’ realities don’t match?
Edenspiekermann have been working agile since 2009. They’ve since achieved terrific results and have never looked back. They now employ about as many developers as designers, creating meaningful digital products and services for global clients like Red Bull, Cisco Systems, The Economist and the German and Dutch Railways.
Christian will talk about the often challenging contrast between wanting to deliver the best possible product and making sure you’re satisfying the client’s internal project needs. How to deliver excellent customer satisfaction while working as agile as possible?
. . . . . . . . . . . . . . . .
Christian is the guy designers are ambivalent about. He’s not a font guy. He’s the business guy—the one who works the odd hours creating and maintaining relationships with some of the largest companies in the world. Over the past decade, he has led business development efforts for numerous agencies on three continents.
Le virage Lean au Centre de Compétence Industriel Le Haillan de THALES AVIONICSInstitut Lean France
"Le Lean est un voyage, pas une destination" : au Lean Tour Bordeaux de novembre 2015, Ludovic Inisan, Responsable Lean Management et Jean-Philippe Boisseaux Directeur Industriel du Centre de Compétence Industrielle de THALES AVIONICS au Haillan présentent le virage Lean pris au sein de leur établissement et l’impact sur le site du Haillan.
Découvrez d'autres témoignages et retours d'expérience de Lean sur www.institut-lean-france.fr
International Journal of Engineering Research and Applications (IJERA) is a team of researchers not publication services or private publications running the journals for monetary benefits, we are association of scientists and academia who focus only on supporting authors who want to publish their work. The articles published in our journal can be accessed online, all the articles will be archived for real time access.
Our journal system primarily aims to bring out the research talent and the works done by sciaentists, academia, engineers, practitioners, scholars, post graduate students of engineering and science. This journal aims to cover the scientific research in a broader sense and not publishing a niche area of research facilitating researchers from various verticals to publish their papers. It is also aimed to provide a platform for the researchers to publish in a shorter of time, enabling them to continue further All articles published are freely available to scientific researchers in the Government agencies,educators and the general public. We are taking serious efforts to promote our journal across the globe in various ways, we are sure that our journal will act as a scientific platform for all researchers to publish their works online.
Aircraft pitch control design using LQG controller based on genetic algorithmTELKOMNIKA JOURNAL
Designing a robust aircraft control system used to achieve a good tracking performance and stable dynamic behavior against working disturbances problem has attracted attention of control engineers. In this paper, a pitch angle control system for aircraft is designed utilizing liner quadratic Gaussian (LQG) optimal controller technique with a numerical tuning algorithm method in the longitudinal plane through cruising stage. Main design approach of LQG controller includes obtaining best weighting matrices values using trial and error method that consumes effort and takes more time, in addition, there is no guarantees to obtain optimum values for weighting matrices elements. In this research, genetic algorithm (GA) is used to optimize the state and control weighting matrices and determine best values for their elements. The proposed traditional and optimized LQG pitch controller schemes are implemented utilizing Matlab simulation tool and their performance are presented and compared based on transient and steady state performance parameters. The simulation results reveal the ability of the optimized GA_LQG controller to reject the effect of the noises in the aircraft system dynamic and achieve a good and stable tracking performance compared with that of the conventional LQG pitch control system.
Taking ground effect into account a longitudinal automatic landing system is designed. Such a system will be tested and implemented on board by using the Preceptor N3 Ultrapup aircraft which is used as technological demonstrator of new control navigation and guidance algorithms in the context of the “Research Project of National Interest” (PRIN 2008) by the Universities of Bologna, Palermo, Ferrara and the Second University of Naples. A general mathematical model of the studied aircraft has been built to obtain non–linear analytical equations for aerodynamic coefficients both Out of Ground Effect and In Ground Effect. To cope with the strong variations of aerodynamic coefficients In Ground Effect a modified gain scheduling approach has been employed for the synthesis of the controller by using six State Space Models. Stability and control matrices have been evaluated by linearization of the obtained aerodynamic coefficients. To achieve a simple structure of the control system, an original landing geometry has been chosen, therefore it has been imposed to control the same state variables during both the glide path and the flare.
Stability Control Structure of Hovercraft Prototype Utilising PID ControllerjournalBEEI
Hovercraft is a method of transportation as an option for clients who remain on the waterway and swamp surface. The issue with hovercraft is when dubious climate and natural condition, e.g. wind speed and wave tallness exasperate solidness of hovercraft to jeopardise the driver. We propose an approach to keep up adjust of the hovercraft by controlling the focal point of gravity (PG) to be determined position. The controller monitors the position of load to change the position. A 6-DOF IMU Sensor MPU 6050 was utilised to create information as an examination with setpoint. PID control strategy was employed. The test outcome demonstrates that the model of air cushion vehicle could keep its adjust the axis orientation of the roll in spite of the fact that it was less compelling in the pitch pivot direction.
We will introduce a development of a mini-quad rotor system for indoor application at Keokuk University. The propulsion system consists of X-UFO blade propellers and brushless direct current (DC) motors assembled on a very stiff ai rframe made of carbon fiber composite material. The attitude control system consists of a stab ility augmentation system as the inner loop control and a modern control approach as the outer lo op. The closed-loop contro l is a PID controller,which is used for the flight test to valid ate our aerodynamic mode ling. To perform an experimental flight test,basic electronics hardware will de velop in a simple configuration. We will use an AVR microcontroller as the embe dded controller,a low-cost 100 Hz AHRS for inertial sensing,infrared (IR) sensors for horizontal ranging,and an ultrasonic sensor for ground ranging. A high performance propeller system is built on an X-UFO quad rotor airframe. The developing flying robot is shown to have an automatic hovering ability with aid of a ground control system that uses mon itoring and a fail-safe system. We will introduce a new quad rotor platform for realizing autonomous navigation in unknown indoor/outdoor environments. Au tonomous waypoint navigation,obs tacle avoidance and flight control is implemented on-board. The system does not require a special environment,artificial markers or an external reference system. We will develop a monolithic,mechanically damped perception unit which is equipped with a stereo camera pair,an Inertial Measurement Unit (IMU),two processor and an FPGA board.
Robust control of aircraft flight in conditions of disturbancesIJECEIAES
One of the most dangerous parts of the flight is the landing phase, as most accidents occur at this stage. In order to reduce the effect of the low-level wind shear on the longitudinal motion of the aircraft in the glide path landing mode (task) a robust H− control isproposed. Dynamic models of the plane and wind shear are built. 𝐻2 and 𝐻∞ synthesis methods are investigated for the task of aircraft flight control in a vertical plane during landing under conditions of undefined disturbances. Both control methods allow to reduce height deviation significantly. However, suboptimal control 𝐻∞ provides better quality of transition processes both in height and speed than optimal control 𝐻2. The results of simulation of the synthesized system confirm the effectiveness of 𝐻∞ − control for increasing robust stability to uncertainties caused by wind disturbances.
This Presentation was prepared to tell the students how to write a letter to the teacher and business type letters were discussed in this presentation.
Saudi Arabia stands as a titan in the global energy landscape, renowned for its abundant oil and gas resources. It's the largest exporter of petroleum and holds some of the world's most significant reserves. Let's delve into the top 10 oil and gas projects shaping Saudi Arabia's energy future in 2024.
Welcome to WIPAC Monthly the magazine brought to you by the LinkedIn Group Water Industry Process Automation & Control.
In this month's edition, along with this month's industry news to celebrate the 13 years since the group was created we have articles including
A case study of the used of Advanced Process Control at the Wastewater Treatment works at Lleida in Spain
A look back on an article on smart wastewater networks in order to see how the industry has measured up in the interim around the adoption of Digital Transformation in the Water Industry.
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.
Water scarcity is the lack of fresh water resources to meet the standard water demand. There are two type of water scarcity. One is physical. The other is economic water scarcity.
2. Prepared By:
Saadullah Aftab(12063122-069)
Usama Jahangir(12063122-079)
Ehtisham Hussain(12063122-091)
Research Paper By:
Buskey, Gregg and Roberts, Jonathan
and Corke, Peter and Wyeth, Gordon
Course:
Dynamic Systems Modeling(Lab)
Instructor:
Engr. Ajmal Hussain Shah
2
4. This presentation will put a light upon how to control
helicopter using low cost sensors.
Control technology is nested loops.
Speed, height and altitude is measured in house by vision and
IP system
This aircraft technology is needed to settle down and to
respond to the demands of a high level steering at all axis,
including address, height, longitudinal and lateral speed.
4
5. Introduction
This presentation gives us the solution to the problem
of automation control at low cost modules.
In Commercial aircrafts, there are many problems,
challenges and trade-offs, like.
In commercial aircrafts, there is a problem of weight
and cost.
Control of vibration is quite difficult.
5
6. Introduction (Cont…)
The challenge is to maintain the balance between size
and cost of aircraft.
There is problem of fuel and flight capacity.
Flight capacity means the flight duration with a given
fuel.
Here we shall discuss the ways to minimize all these
challenges.
6
8. Flight Vehicle
XCELL-60 RC helicopter is available in avionics.
It uses petrol as fuel instead of methanol.
Due to usage of petrol, its speed is comparatively low
but the advantage is that the vibrations are also low.
Petrol engine gives three times flight duration.
On a single tank, it gives eighteen minutes of flight.
8
9. Dimensions
Here are the major specifications of the flight vehicle:
Diameter of rotor is 1.5 meters
Weight is 8 kilograms
Length is 1.8 meters.
Flight capacity is 18 Minutes per Litre.
9
10. Avionics & Sensors
Computer for data logging and sensing is any high
processing CPU equipped by wireless Ethernet and
camera multiplexing.
Stereo vision system is used to control the velocity and
height.
The Feedback controlled by RPM sensor connected
with feed forward term from collective pitch to
improve regulation response that makes it most
effective
10
11. Altitude Control
Heading (y), roll (f) and pitch (q) is controlled by IP
modules.
Maintenance of aircraft is also conducted with the
control system of aircraft.
The second source of variation is wind magnitude and
altering the flapping characteristics of the dynamics.
This variation occurs during a flight.
11
12. Horizontal Velocity Control
Velocity is implemented by two levels nested loop
structure.
Velocity errors give roll for roll control modules
Longitudinal velocity errors for pitch control modules.
12
13. Vertical Control
Vertical control takes two forms:
One is vertical velocity regulation
Second is height regulation.
Vertical velocity controls the feedback and sends
demand to nested loop.
It also controls the height which is available in IP
modules.
13
14. Conclusion
This Presentation gives us the brief knowledge about
helicopter automation system with less cost avionics
and control systems.
Sensing is conducted by using vision modules.
Cheap sensing makes it quite efficient as compared to
expensive projects.
It gives us small size with much more flight duration
and low cost.
14