This document is a project report on the design and fabrication of a quadcopter. It was submitted by two students in partial fulfillment of their Bachelor of Technology degree in Mechanical Engineering. The report covers modeling the quadcopter in Pro-E software, selecting hardware components, developing control software, assembly, and flight testing. While hardware issues prevented full testing, the students were able to complete a hands-free hover demonstration and other tests showing the quadcopter's stability and potential 6-8 minute flight time.
This document discusses the development of a fixed-wing vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV). It begins with an introduction comparing multi-rotor and fixed-wing UAVs and proposing a hybrid VTOL design. It then details the conceptual design process including weight estimation, airfoil selection, and preliminary sizing calculations. Next, it describes the preliminary and detailed design stages in Solidworks and validation of the design through computational fluid dynamics analysis in ANSYS Fluent. Finally, it summarizes that the methodology allows for the design of a fixed-wing VTOL UAV and concludes the design is ready for prototyping and flight testing.
This document discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
This document summarizes the design and testing of an unmanned aerial vehicle (UAV) built by students to survey farmland by taking aerial images and recording GPS coordinates. The students followed an engineering design process, beginning with brainstorming how to survey large areas of rough terrain. They researched UAV types and flight principles and designed a flying wing platform suited for autonomous flight, first-person viewing, and ease of use. A quality function deployment analysis supported this design. The UAV was constructed of expanded polypropylene foam and tested through several flights. High definition video and images captured during test flights over a banana crop provided a valuable aerial view for monitoring the farm.
Design and Finite Element Analysis of Aircraft Wing using Ribs and SparsIRJET Journal
This document describes the design and finite element analysis of an aircraft wing structure using ribs and spars. The wing structure was modeled in PRO-ENGINEER and then analyzed in ANSYS. Static, fatigue, and modal analyses were performed to determine stresses, life, damage, and deformation under different loads and speeds. The analyses showed that a carbon epoxy composite material performed better than aluminum or glass materials, with lower stresses and higher safety factors. In conclusion, the carbon epoxy material was determined to be better suited for aircraft wings.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
A Review on Longitudinal Control Law Design for a Small Fixed-Wing UAVIRJET Journal
This document reviews various techniques for designing longitudinal control laws for small fixed-wing unmanned aerial vehicles (UAVs). It discusses techniques such as integral sliding mode control, linear quadratic regulator (LQR), Apriltags recognition algorithm with PID control, observer Kalman identification with PID control, root locus method, nonlinear model simulation, and multi-model techniques. These techniques have been applied to problems such as longitudinal guidance, stability augmentation, autonomous landing, and modeling fixed-wing UAV dynamics. The document analyzes the effectiveness and robustness of different proposed control schemes through simulations and comparisons of various techniques.
This document is a project report on the design and fabrication of a quadcopter. It was submitted by two students in partial fulfillment of their Bachelor of Technology degree in Mechanical Engineering. The report covers modeling the quadcopter in Pro-E software, selecting hardware components, developing control software, assembly, and flight testing. While hardware issues prevented full testing, the students were able to complete a hands-free hover demonstration and other tests showing the quadcopter's stability and potential 6-8 minute flight time.
This document discusses the development of a fixed-wing vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV). It begins with an introduction comparing multi-rotor and fixed-wing UAVs and proposing a hybrid VTOL design. It then details the conceptual design process including weight estimation, airfoil selection, and preliminary sizing calculations. Next, it describes the preliminary and detailed design stages in Solidworks and validation of the design through computational fluid dynamics analysis in ANSYS Fluent. Finally, it summarizes that the methodology allows for the design of a fixed-wing VTOL UAV and concludes the design is ready for prototyping and flight testing.
This document discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
This document summarizes the design and testing of an unmanned aerial vehicle (UAV) built by students to survey farmland by taking aerial images and recording GPS coordinates. The students followed an engineering design process, beginning with brainstorming how to survey large areas of rough terrain. They researched UAV types and flight principles and designed a flying wing platform suited for autonomous flight, first-person viewing, and ease of use. A quality function deployment analysis supported this design. The UAV was constructed of expanded polypropylene foam and tested through several flights. High definition video and images captured during test flights over a banana crop provided a valuable aerial view for monitoring the farm.
Design and Finite Element Analysis of Aircraft Wing using Ribs and SparsIRJET Journal
This document describes the design and finite element analysis of an aircraft wing structure using ribs and spars. The wing structure was modeled in PRO-ENGINEER and then analyzed in ANSYS. Static, fatigue, and modal analyses were performed to determine stresses, life, damage, and deformation under different loads and speeds. The analyses showed that a carbon epoxy composite material performed better than aluminum or glass materials, with lower stresses and higher safety factors. In conclusion, the carbon epoxy material was determined to be better suited for aircraft wings.
Structural Weight Optimization of Aircraft Wing Component Using FEM Approach.IJERA Editor
One of the main challenges for the civil aviation industry is the reduction of its environmental impact by better fuel efficiency by virtue of Structural optimization. Over the past years, improvements in performance and fuel efficiency have been achieved by simplifying the design of the structural components and usage of composite materials to reduce the overall weight of the structure. This paper deals with the weight optimization of transport aircraft with low wing configuration. The Linear static and Normal Mode analysis were carried out using MSc Nastran & Msc Patran under different pressure conditions and the results were verified with the help of classical approach. The Stress and displacement results were found and verified and hence arrived to the conclusion about the optimization of the wing structure.
A Review on Longitudinal Control Law Design for a Small Fixed-Wing UAVIRJET Journal
This document reviews various techniques for designing longitudinal control laws for small fixed-wing unmanned aerial vehicles (UAVs). It discusses techniques such as integral sliding mode control, linear quadratic regulator (LQR), Apriltags recognition algorithm with PID control, observer Kalman identification with PID control, root locus method, nonlinear model simulation, and multi-model techniques. These techniques have been applied to problems such as longitudinal guidance, stability augmentation, autonomous landing, and modeling fixed-wing UAV dynamics. The document analyzes the effectiveness and robustness of different proposed control schemes through simulations and comparisons of various techniques.
This document describes the design and development of an unmanned aerial surveillance vehicle (UASV). It discusses:
1. The methodology used which included calculating dimensions based on theoretical formulas, constructing prototypes, testing them, modifying dimensions, and building a final structure.
2. Details of the design process including wing, airfoil, and control surface specifications as well as fuselage, avionics, and performance calculations.
3. Validation of the design through analytical calculations showing the aircraft can generate enough lift to support its weight at various speeds.
Design and Computational Fluid Dynamic Analysis of Spiroid Winglet to Study i...IRJET Journal
This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
Technical Development of Design & Fabrication of an Unmanned Aerial VehicleIOSR Journals
: UAV (Unmanned Aerial Vehicle) is an air vehicle which is largely used for surveillance, monitoring,
reconnaissance, data relay, and data collection or to enter the area which is not safe for human i.e. flood
affected or virus affected area. This paper represents the unique design of such an UAV which designed at
MILITARY INSTITUTE OF SCIENCE & TECHNOLOGY to participate in an international competition SAE
Aero Design West-2013. As per competition requirement empty weight of the UAV must be less than 2 lb and
must fly with payload as heavy as possible for good scoring. Initially, the model of the UAV was tested in wind
tunnel and the test data showed that the model aircraft performance was capable enough for flying and covering
an area specified in the competition. Subsequently, an actual aircraft was fabricated of that model and flight
tested which proved the match with theoretical, statistical and experimental data that was obtained from wind
tunnel test, wing tip test, tensile test of manufacturing material and CFD (Computational Fluid Dynamics) flow
simulation over the aerofoil.
Modeling and analysis of naca 66 206 aerofoil propellereSAT Journals
Abstract
NACA aerofoil shapes have been successfully used over the years as wing and tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors. The aircraft performance is highly affected by induced drag caused by wingtip vortices to improve fuel efficiency. In this research work, the analysis of NACA 66-206 aerofoil propellers was investigated for high-speed aircraft propulsion.CFD analysis is performed on the NACA aerofoil to verify the aerodynamic characteristics and enhancing the lift of the aircraft by changing the orientation of angle of attack 00, 100 and 200 and to determine the drag and lift coefficients by applying inlet velocities. An auxiliary part, winglets are added on propeller blade tip in order to improve the performance of propeller. By adding this auxiliary equipment the weight of propeller are significantly increased. To decrease the weight without compromising the performance of the propeller the fiber reinforced composite materials are used. The effects of stacking sequence layers of composite materials, which were fabricated from Kevlar, carbon, glass fibres, and epoxy resin have been used to increase the strength to weight ratio. To validate the strength of the propeller, Structural and buckling analysis is performed.
Keywords: Aerofoil, Propeller, fiber reinforcement and strength etc…
This document describes the development of a vision-based autopilot system for unmanned aerial vehicles (UAVs). The system uses a modular design with three main components: an autopilot to control low-level functions, a single-board computer for image processing, and a switching module to toggle between manual and autonomous control. Hardware tests show the switching module can reliably switch inputs and return control to the operator if needed. The system aims to provide an affordable, standardized platform for developing and testing vision-based control algorithms for UAVs.
This document describes the design of a vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) for intelligence, surveillance, and reconnaissance missions. The goals are to develop a fixed-wing UAV with VTOL capability, high speed, stealth, and autonomous payload delivery. An additive manufactured airframe and commercial off-the-shelf components are selected to allow for low cost and reconfiguration. Electronics including batteries, motors, flight controller, and Android device are designed to fit within the airframe. A transition rig is built and tested to demonstrate VTOL capability using simpler autopilot software prior to integrating the design onto the full-scale aircraft.
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 - Design and Computational Fluid Dynamic Simulation of Micro Air Ve...IRJET Journal
This document describes the design and computational fluid dynamic (CFD) simulation of a micro air vehicle (MAV) propeller. It begins with introductions to unmanned aerial vehicles (UAVs) and MAVs. It then discusses propellers for MAVs and the importance of thrust. The document outlines the design of the MAV propeller, including the selection of the Clark-Y airfoil section based on its aerodynamic properties. It also provides the coordinates of the Clark-Y airfoil. Finally, it describes the CFD simulation process using ANSYS Fluent software to analyze thrust performance and validate the analytical results.
This document summarizes the design and results of a test rig to measure lift force generated by flapping wings. Numerical modeling was used to predict lift values based on wing geometry and motion parameters like frequency and angle of attack. An experimental test rig was designed and built with servo motors in the wings to control twisting instead of relying on flexibility. Force measurements from the rig were taken using a load cell as frequency and angle of attack were varied. Results showed that increasing frequency and angle of attack both increased lift force as expected based on the numerical predictions. The document provides context on bio-inspired flight and reviews other flapping wing projects to inform the design of the test rig.
This document describes a project report for a quadcopter that uses an ATmega 328 microcontroller. It includes a title page, certificate of authenticity signed by the student and advisor, acknowledgements, abstract, list of figures, and table of contents. The project aims to design and build a stable quadcopter capable of autonomous flight and GPS data logging. Various components of the quadcopter are discussed including the frame, motors, electronic speed controllers, batteries, and remote control system. The control and programming of the flight controller is also outlined.
The document describes the design and fabrication of a V-tail unmanned aerial vehicle (UAV). It aims to study the stability, design parameters, and operation of a V-tail configuration. The project involves designing all parts of the RC aircraft using CATIA software, performing calculations to determine dimensions, and assembling the final prototype. The design process considers various factors like material selection, component orientation, weight estimation, and control surface sizing. The report outlines the various stages of completing the project, from initial conceptualization to fabrication and testing of the final V-tail UAV model.
The document is a seminar report on aircraft drone technology submitted by Ganesh Kanherkar to the Mechanical Engineering department. It contains an abstract, introduction, types of drones, technical specifications, block diagram, components of drones, advantages, disadvantages, discussion on Indian drone technology, and conclusion with references. The main components of drones discussed are frames, rotors/motors, batteries, and electronic speed controllers. Drones have various applications but also disadvantages that need to be addressed.
IRJET- Analysing the Performance of Solar Powered Wing (UAV)IRJET Journal
This document analyzes the performance of a solar-powered wing for an unmanned aerial vehicle (UAV) consisting of two different airfoil sections. Computational fluid dynamics (CFD) software is used to model and analyze wings with the Eppler 421 and Selig 1223 airfoils individually and as a combined wing. Results show that the combined wing profile has lift and drag characteristics between the individual airfoils. Specifically, the Selig 1223 airfoil produces higher lift but also higher drag. The combined wing design and CFD analysis indicate that a solar-powered wing could provide long endurance flights for UAVs.
DESIGN AND ANALYSIS OF AN ACTIVE TWIST ROTOR BLADES WITH D-SPAR MODEL USING C...AM Publications
Today’s helicopters are the result of collaborative work in mechanical engineering and aeronautics. A helicopter main rotor or rotor system is the combination of a rotary wing and a control system that generates the aerodynamic lift force that supports the weight of the helicopter, and the thrust that counteracts aerodynamic drag in forward flight. In the field of rotorcraft, the research in this project is currently focusing on active blade systems to adapt the aerodynamic properties of the blade to the local aerodynamic conditions. Fuel-efficiency, reduction of vibration and noise and increase of the helicopter maximum speed are the benefits expected from these new technologies. A helicopter's rotor is generally made of two or more rotor blades. Rotor blades are made out of various materials, including aluminum, composite structure, and steel or titanium, with abrasion shields along the leading edge. The blade pitch is typically controlled by a swash plate connected to the helicopter flight controls. An Active Twist Rotor (ATR) is developed for future implementation of the individual blade control for vibration and noise reduction in helicopters. The rotor blade is integrally twisted by direct strain actuation using active fiber composites (AFC). In this thesis, the model of rotor blade is designed and analyzed. 3D models are done in CATIA. Analysis is done in Ansys. The materials used for original model are steel and Aluminum alloy, The modified model is analyzed by specifying aluminum alloy using solid element and also the shell element. The optimization results have been obtained for design solutions, connected with the application of active materials.
: The main objective of this paper is the systematic description of the current research and
development of small or miniature unmanned aerial vehicles and micro aerial vehicles, with a focus on
rotary wing vehicles. In recent times, unmanned/Micro aerial vehicles have been operated across the
world; they have also been the subject of considerable research. In particular, UAVs/MAVs with rotary
wings have been expected to perform various tasks such as monitoring at fixed points and surveillance
from the sky since they can perform not only perform static flights by hovering but also achieve vertical
takeoffs and landing. Helicopters have been used for personnel transport, carrying goods, spreading
information, and performing monitoring duties for long periods. A manned helicopter has to be used for
all these duties. On the other hand, unmanned helicopters that can be operated by radio control have
been developed as a hobby. Since unmanned helicopters are often superior to manned helicopters in
terms of cost and safety, in recent years, accomplishing tasks using unmanned helicopters has become
popular. Considerable expertise is required to operate unmanned helicopters by radio control, and
hence, vast labor resources are employed to train operators. Moreover, it is impossible to operate
unmanned helicopters outside visual areas because of lack of radio control, and the working area is
hence limited remarkably. For solving the above problems, it is necessary to realize autonomous
control of unmanned helicopters. However, no general method for designing the small unmanned
helicopters has been developed yet – today, various design techniques by different study groups using
different helicopters exist. In this paper the conceptual design process is explained.
This document analyzes bungee cord launching devices (LDs) for unmanned aerial vehicles (UAVs). It provides four analyses: 1) an analysis of LD systems against critical design requirements and customer needs, 2) an analysis of the motion of the UAV-cradle subsystem on the launch rail, 3) an analysis of cord selection and the cord's energetic capabilities based on design requirements, and 4) an analysis of how aerodynamic lift and drag forces influence mathematical and physical models, with results compared. The analyses recommend bungee cord LDs for early design phases. Mathematical models of the UAV-cradle motion on the launch rail are developed based on various assumptions about forces like gravity
Design,Construction And Structure Analysis Of Twinrotor UAVijics
There have been many advancements in the field of aerospace and avionics. Scientists have increasingly
started to focus on VTOL (vertical take - off and landing) aircrafts. We have built a miniature VTOL
twinrotor UAV. UAVs have begun to grab a lot of attention these days due to its numerous applications
such as surveillance and relief. Twinrotor is a kind of a helicopter having two main propellers instead of
one and no tail fin. All three important motion of the aircraft i.e. roll, pitch, yaw are controlled by thrust
vectoring using servo motors and changing the magnitude of thrust using electronics speed controllers. The
paper deals with the design of a basic UAV based on application and the construction keeping in mind the
different concepts that govern its motion.
Detail Solidworks Design and Simulation of an Unmanned Air VehicleIOSR Journals
Unmanned Air Vehicles (UAVs) are a new type of aircraft maturing day by day and have reached
unprecedented levels of growth recently. Unmanned Air Vehicles (UAVs) have enormous potential in
applications. They are deployed predominantly for military and special operation applications, but also used in
a small but growing number of civil applications, such as policing and firefighting, and nonmilitary security
work, such as surveillance of pipelines. UAVs are often preferred for missions that are too "dull, dirty, and
dangerous" for manned aircraft. This article mainly describes the design process of an unmanned air vehicle in
solidworks and shows the results of solidworks simulation analysis
This document summarizes the design and components of a small-scale unmanned aerial vehicle (UAV). It describes the required hardware including a brushless motor, electronic speed controller, transmitter and receiver, servos, and battery. It provides block diagrams of the system design and discusses the materials used to build the airframe. Applications of UAVs include aerial surveillance, scientific research, search and rescue operations, and more. Future developments may allow UAVs to perform combat missions and aerial resupply.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
This document describes the design and development of an unmanned aerial surveillance vehicle (UASV). It discusses:
1. The methodology used which included calculating dimensions based on theoretical formulas, constructing prototypes, testing them, modifying dimensions, and building a final structure.
2. Details of the design process including wing, airfoil, and control surface specifications as well as fuselage, avionics, and performance calculations.
3. Validation of the design through analytical calculations showing the aircraft can generate enough lift to support its weight at various speeds.
Design and Computational Fluid Dynamic Analysis of Spiroid Winglet to Study i...IRJET Journal
This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
Technical Development of Design & Fabrication of an Unmanned Aerial VehicleIOSR Journals
: UAV (Unmanned Aerial Vehicle) is an air vehicle which is largely used for surveillance, monitoring,
reconnaissance, data relay, and data collection or to enter the area which is not safe for human i.e. flood
affected or virus affected area. This paper represents the unique design of such an UAV which designed at
MILITARY INSTITUTE OF SCIENCE & TECHNOLOGY to participate in an international competition SAE
Aero Design West-2013. As per competition requirement empty weight of the UAV must be less than 2 lb and
must fly with payload as heavy as possible for good scoring. Initially, the model of the UAV was tested in wind
tunnel and the test data showed that the model aircraft performance was capable enough for flying and covering
an area specified in the competition. Subsequently, an actual aircraft was fabricated of that model and flight
tested which proved the match with theoretical, statistical and experimental data that was obtained from wind
tunnel test, wing tip test, tensile test of manufacturing material and CFD (Computational Fluid Dynamics) flow
simulation over the aerofoil.
Modeling and analysis of naca 66 206 aerofoil propellereSAT Journals
Abstract
NACA aerofoil shapes have been successfully used over the years as wing and tail sections for general aviation and military aircraft, as well as propellers and helicopter rotors. The aircraft performance is highly affected by induced drag caused by wingtip vortices to improve fuel efficiency. In this research work, the analysis of NACA 66-206 aerofoil propellers was investigated for high-speed aircraft propulsion.CFD analysis is performed on the NACA aerofoil to verify the aerodynamic characteristics and enhancing the lift of the aircraft by changing the orientation of angle of attack 00, 100 and 200 and to determine the drag and lift coefficients by applying inlet velocities. An auxiliary part, winglets are added on propeller blade tip in order to improve the performance of propeller. By adding this auxiliary equipment the weight of propeller are significantly increased. To decrease the weight without compromising the performance of the propeller the fiber reinforced composite materials are used. The effects of stacking sequence layers of composite materials, which were fabricated from Kevlar, carbon, glass fibres, and epoxy resin have been used to increase the strength to weight ratio. To validate the strength of the propeller, Structural and buckling analysis is performed.
Keywords: Aerofoil, Propeller, fiber reinforcement and strength etc…
This document describes the development of a vision-based autopilot system for unmanned aerial vehicles (UAVs). The system uses a modular design with three main components: an autopilot to control low-level functions, a single-board computer for image processing, and a switching module to toggle between manual and autonomous control. Hardware tests show the switching module can reliably switch inputs and return control to the operator if needed. The system aims to provide an affordable, standardized platform for developing and testing vision-based control algorithms for UAVs.
This document describes the design of a vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) for intelligence, surveillance, and reconnaissance missions. The goals are to develop a fixed-wing UAV with VTOL capability, high speed, stealth, and autonomous payload delivery. An additive manufactured airframe and commercial off-the-shelf components are selected to allow for low cost and reconfiguration. Electronics including batteries, motors, flight controller, and Android device are designed to fit within the airframe. A transition rig is built and tested to demonstrate VTOL capability using simpler autopilot software prior to integrating the design onto the full-scale aircraft.
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 - Design and Computational Fluid Dynamic Simulation of Micro Air Ve...IRJET Journal
This document describes the design and computational fluid dynamic (CFD) simulation of a micro air vehicle (MAV) propeller. It begins with introductions to unmanned aerial vehicles (UAVs) and MAVs. It then discusses propellers for MAVs and the importance of thrust. The document outlines the design of the MAV propeller, including the selection of the Clark-Y airfoil section based on its aerodynamic properties. It also provides the coordinates of the Clark-Y airfoil. Finally, it describes the CFD simulation process using ANSYS Fluent software to analyze thrust performance and validate the analytical results.
This document summarizes the design and results of a test rig to measure lift force generated by flapping wings. Numerical modeling was used to predict lift values based on wing geometry and motion parameters like frequency and angle of attack. An experimental test rig was designed and built with servo motors in the wings to control twisting instead of relying on flexibility. Force measurements from the rig were taken using a load cell as frequency and angle of attack were varied. Results showed that increasing frequency and angle of attack both increased lift force as expected based on the numerical predictions. The document provides context on bio-inspired flight and reviews other flapping wing projects to inform the design of the test rig.
This document describes a project report for a quadcopter that uses an ATmega 328 microcontroller. It includes a title page, certificate of authenticity signed by the student and advisor, acknowledgements, abstract, list of figures, and table of contents. The project aims to design and build a stable quadcopter capable of autonomous flight and GPS data logging. Various components of the quadcopter are discussed including the frame, motors, electronic speed controllers, batteries, and remote control system. The control and programming of the flight controller is also outlined.
The document describes the design and fabrication of a V-tail unmanned aerial vehicle (UAV). It aims to study the stability, design parameters, and operation of a V-tail configuration. The project involves designing all parts of the RC aircraft using CATIA software, performing calculations to determine dimensions, and assembling the final prototype. The design process considers various factors like material selection, component orientation, weight estimation, and control surface sizing. The report outlines the various stages of completing the project, from initial conceptualization to fabrication and testing of the final V-tail UAV model.
The document is a seminar report on aircraft drone technology submitted by Ganesh Kanherkar to the Mechanical Engineering department. It contains an abstract, introduction, types of drones, technical specifications, block diagram, components of drones, advantages, disadvantages, discussion on Indian drone technology, and conclusion with references. The main components of drones discussed are frames, rotors/motors, batteries, and electronic speed controllers. Drones have various applications but also disadvantages that need to be addressed.
IRJET- Analysing the Performance of Solar Powered Wing (UAV)IRJET Journal
This document analyzes the performance of a solar-powered wing for an unmanned aerial vehicle (UAV) consisting of two different airfoil sections. Computational fluid dynamics (CFD) software is used to model and analyze wings with the Eppler 421 and Selig 1223 airfoils individually and as a combined wing. Results show that the combined wing profile has lift and drag characteristics between the individual airfoils. Specifically, the Selig 1223 airfoil produces higher lift but also higher drag. The combined wing design and CFD analysis indicate that a solar-powered wing could provide long endurance flights for UAVs.
DESIGN AND ANALYSIS OF AN ACTIVE TWIST ROTOR BLADES WITH D-SPAR MODEL USING C...AM Publications
Today’s helicopters are the result of collaborative work in mechanical engineering and aeronautics. A helicopter main rotor or rotor system is the combination of a rotary wing and a control system that generates the aerodynamic lift force that supports the weight of the helicopter, and the thrust that counteracts aerodynamic drag in forward flight. In the field of rotorcraft, the research in this project is currently focusing on active blade systems to adapt the aerodynamic properties of the blade to the local aerodynamic conditions. Fuel-efficiency, reduction of vibration and noise and increase of the helicopter maximum speed are the benefits expected from these new technologies. A helicopter's rotor is generally made of two or more rotor blades. Rotor blades are made out of various materials, including aluminum, composite structure, and steel or titanium, with abrasion shields along the leading edge. The blade pitch is typically controlled by a swash plate connected to the helicopter flight controls. An Active Twist Rotor (ATR) is developed for future implementation of the individual blade control for vibration and noise reduction in helicopters. The rotor blade is integrally twisted by direct strain actuation using active fiber composites (AFC). In this thesis, the model of rotor blade is designed and analyzed. 3D models are done in CATIA. Analysis is done in Ansys. The materials used for original model are steel and Aluminum alloy, The modified model is analyzed by specifying aluminum alloy using solid element and also the shell element. The optimization results have been obtained for design solutions, connected with the application of active materials.
: The main objective of this paper is the systematic description of the current research and
development of small or miniature unmanned aerial vehicles and micro aerial vehicles, with a focus on
rotary wing vehicles. In recent times, unmanned/Micro aerial vehicles have been operated across the
world; they have also been the subject of considerable research. In particular, UAVs/MAVs with rotary
wings have been expected to perform various tasks such as monitoring at fixed points and surveillance
from the sky since they can perform not only perform static flights by hovering but also achieve vertical
takeoffs and landing. Helicopters have been used for personnel transport, carrying goods, spreading
information, and performing monitoring duties for long periods. A manned helicopter has to be used for
all these duties. On the other hand, unmanned helicopters that can be operated by radio control have
been developed as a hobby. Since unmanned helicopters are often superior to manned helicopters in
terms of cost and safety, in recent years, accomplishing tasks using unmanned helicopters has become
popular. Considerable expertise is required to operate unmanned helicopters by radio control, and
hence, vast labor resources are employed to train operators. Moreover, it is impossible to operate
unmanned helicopters outside visual areas because of lack of radio control, and the working area is
hence limited remarkably. For solving the above problems, it is necessary to realize autonomous
control of unmanned helicopters. However, no general method for designing the small unmanned
helicopters has been developed yet – today, various design techniques by different study groups using
different helicopters exist. In this paper the conceptual design process is explained.
This document analyzes bungee cord launching devices (LDs) for unmanned aerial vehicles (UAVs). It provides four analyses: 1) an analysis of LD systems against critical design requirements and customer needs, 2) an analysis of the motion of the UAV-cradle subsystem on the launch rail, 3) an analysis of cord selection and the cord's energetic capabilities based on design requirements, and 4) an analysis of how aerodynamic lift and drag forces influence mathematical and physical models, with results compared. The analyses recommend bungee cord LDs for early design phases. Mathematical models of the UAV-cradle motion on the launch rail are developed based on various assumptions about forces like gravity
Design,Construction And Structure Analysis Of Twinrotor UAVijics
There have been many advancements in the field of aerospace and avionics. Scientists have increasingly
started to focus on VTOL (vertical take - off and landing) aircrafts. We have built a miniature VTOL
twinrotor UAV. UAVs have begun to grab a lot of attention these days due to its numerous applications
such as surveillance and relief. Twinrotor is a kind of a helicopter having two main propellers instead of
one and no tail fin. All three important motion of the aircraft i.e. roll, pitch, yaw are controlled by thrust
vectoring using servo motors and changing the magnitude of thrust using electronics speed controllers. The
paper deals with the design of a basic UAV based on application and the construction keeping in mind the
different concepts that govern its motion.
Detail Solidworks Design and Simulation of an Unmanned Air VehicleIOSR Journals
Unmanned Air Vehicles (UAVs) are a new type of aircraft maturing day by day and have reached
unprecedented levels of growth recently. Unmanned Air Vehicles (UAVs) have enormous potential in
applications. They are deployed predominantly for military and special operation applications, but also used in
a small but growing number of civil applications, such as policing and firefighting, and nonmilitary security
work, such as surveillance of pipelines. UAVs are often preferred for missions that are too "dull, dirty, and
dangerous" for manned aircraft. This article mainly describes the design process of an unmanned air vehicle in
solidworks and shows the results of solidworks simulation analysis
This document summarizes the design and components of a small-scale unmanned aerial vehicle (UAV). It describes the required hardware including a brushless motor, electronic speed controller, transmitter and receiver, servos, and battery. It provides block diagrams of the system design and discusses the materials used to build the airframe. Applications of UAVs include aerial surveillance, scientific research, search and rescue operations, and more. Future developments may allow UAVs to perform combat missions and aerial resupply.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
Similar to UAV PROJECT FINAL..Design and analysis of unmanned aerial vehicle (20)
Electric vehicle and photovoltaic advanced roles in enhancing the financial p...IJECEIAES
Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
Embedded machine learning-based road conditions and driving behavior monitoringIJECEIAES
Car accident rates have increased in recent years, resulting in losses in human lives, properties, and other financial costs. An embedded machine learning-based system is developed to address this critical issue. The system can monitor road conditions, detect driving patterns, and identify aggressive driving behaviors. The system is based on neural networks trained on a comprehensive dataset of driving events, driving styles, and road conditions. The system effectively detects potential risks and helps mitigate the frequency and impact of accidents. The primary goal is to ensure the safety of drivers and vehicles. Collecting data involved gathering information on three key road events: normal street and normal drive, speed bumps, circular yellow speed bumps, and three aggressive driving actions: sudden start, sudden stop, and sudden entry. The gathered data is processed and analyzed using a machine learning system designed for limited power and memory devices. The developed system resulted in 91.9% accuracy, 93.6% precision, and 92% recall. The achieved inference time on an Arduino Nano 33 BLE Sense with a 32-bit CPU running at 64 MHz is 34 ms and requires 2.6 kB peak RAM and 139.9 kB program flash memory, making it suitable for resource-constrained embedded systems.
Software Engineering and Project Management - Introduction, Modeling Concepts...Prakhyath Rai
Introduction, Modeling Concepts and Class Modeling: What is Object orientation? What is OO development? OO Themes; Evidence for usefulness of OO development; OO modeling history. Modeling
as Design technique: Modeling, abstraction, The Three models. Class Modeling: Object and Class Concept, Link and associations concepts, Generalization and Inheritance, A sample class model, Navigation of class models, and UML diagrams
Building the Analysis Models: Requirement Analysis, Analysis Model Approaches, Data modeling Concepts, Object Oriented Analysis, Scenario-Based Modeling, Flow-Oriented Modeling, class Based Modeling, Creating a Behavioral Model.
KuberTENes Birthday Bash Guadalajara - K8sGPT first impressionsVictor Morales
K8sGPT is a tool that analyzes and diagnoses Kubernetes clusters. This presentation was used to share the requirements and dependencies to deploy K8sGPT in a local environment.
Optimizing Gradle Builds - Gradle DPE Tour Berlin 2024Sinan KOZAK
Sinan from the Delivery Hero mobile infrastructure engineering team shares a deep dive into performance acceleration with Gradle build cache optimizations. Sinan shares their journey into solving complex build-cache problems that affect Gradle builds. By understanding the challenges and solutions found in our journey, we aim to demonstrate the possibilities for faster builds. The case study reveals how overlapping outputs and cache misconfigurations led to significant increases in build times, especially as the project scaled up with numerous modules using Paparazzi tests. The journey from diagnosing to defeating cache issues offers invaluable lessons on maintaining cache integrity without sacrificing functionality.
cnn.pptx Convolutional neural network used for image classication
UAV PROJECT FINAL..Design and analysis of unmanned aerial vehicle
1. DESIGN AND ANALYSIS OF UNMANNED AERIAL VEHICLE
PRESENTED BY
JAY JAIN
AKARSH DEVADIGA
ABHAY BHUTKAR
NIRAJ GUPTA
UNDER THE GUIDANCE OF
PROF. DR. FAUZIA SIDDIQUI
Department of Mechanical Engineering
Saraswati College Of Engineering
2. INTRODUCTION
• Multi-purpose, compact unmanned aerial vehicles are important
due to their abilities to replace manned aircrafts in many routine
and dangerous missions.
• These aerial robots can be utilized in a variety of civilian
missions such as surveillance in disasters, traffic
monitoring, military purposes and power line maintenance.
3. OBJECTIVES
1.To design an UAV with ease of Assembly and Disassembly.
2.UAV with minimum aerodynamic instability.
3.To design an aircraft with minimum drag.
4.UAV for surveillance purpose.
4. LITERATURE REVIEW
SR
NO.
TOPIC, AUTHOR & YEAR
OF PUBLICATION
ABSTRACT METHODOLOGY USED CONCLUSION
1. Design and construction
of a novel quad tilt-wing
UAV
By
E. Cetinsoy et al [1]
2012
This paper presents
aerodynamic and mechanical
design, prototyping and flight
control system design of
a new unmanned aerial
vehicle SUAVI
4 motors are mounted on
the mid span of wings so
that UAV takes flight as a
helicopter and for
horizontal flight, wings are
gradually tilted to
appropriate angles.
They presented aerodynamic
& mechanical design,
prototyping & flight control
system design that can take
off & land like a quad rotor
helicopter & horizontal flight
like a airplane.
2. Crop Area Estimation
from UAV Transect and
MSR Image
Data Using Spatial
Sampling Method: a
Simulation
Experiment.
By Yaozhong Pan et al [2]
2011
In this paper they choose
area-scale index as
auxiliary variable, using
simulated MSR image for
crop area estimation.
Spatial sampling method
was used for crop area
estimation purposes.
This method helped in
improving crop are estimation
accuracy over a large area.
5. 3. Control System Design of a
Vertical Take-off and Landing
(VTOL)
Fixed-Wing UAV
By M. Kemal LEBLEBİCİOĞLU
et al [3]
2016
In this paper study, design
and implementation of
control system of a vertical
take-off and landing (VTOL)
unmanned aerial vehicle
(UAV) with level flight
capability is considered.
Vertical take off &
vertical landing is made
possible by adding 4
motors to it (like that of
drone)
5th motor is added to
provide forward thrust.
Linear analysis is done by
examining stability &
controllability.
VTOL-FW UAV is
expected to find usage
areas in mission
requiring VTOL and
efficient level flight
without the need for a
runway and launch
recovery equipment.
4. Design, performance
evaluation and optimization of
a UAV
By Spyridon G. Kontogiannis
et al [4]
2013
In this paper a small size
light UAV was designed,
constructed and tested in
flight.
In this the methodology
used is computational
fluid dynamics (CFD).
The result of several
CFD simulations that
clearly demonstrated
that aerodynamic
characteristics of
airplane could be
improved after certain
modification.
6. 5. UAVs for coastal surveying
By Ian L. Turner et al [5]
2015
. In this paper
particular, survey-
grade UAVs that
incorporate internal
RTK-GPS for high
accuracy positioning
and requiring a single
operator only to safely
deploy in the field
Sampling once every
second, which is
enhanced by density
of UAV point cloud
data
Survey-grade UAV
equipment, data
processing and
analysis tools are now
readily available to
practicing coastal
engineers, managers
and researchers.
Within the regulatory
constraints that
determine their use
7. METHODOLOGY
1.The design of the UAV will be done on CATIA.
2.The structural analysis will be done through Ansys.
3.For Aerodynamic analysis , we will be using XFLR5.
4.Balsa wood will be used for manufacturing of body ,wings and tail.
5.Kevlar Rod and Medium Density Fibre(MDF) for mounting purpose.
6. Radio Controller 2.4Ghz for controlling the UAV.
7.Autopilot/Flight-Back/Arduino/Razbeery-Pi as a software for surveillance
purpose.
8.Super glue for assembling and fibre glass for mounting tail.
10. REFERENCES
[1] E. Cetinsoy, S. Dikyar, C. Hancer, K.T. Oner, E. Sirimoglu, M. Unel ,
M.F. Aksit ‘’Design and construction of a novel quad tilt- wing UAV’’
12th March 2012.
[2] Yaozhong Pana, Jinshui Zhanga, Kejian Shena ‘’Crop Area Estimation
from UAV Transect using Spatial Sampling method’’ Procedia
Environment Sciences 7(2011) 110-115.
[3]Ferit CAKICI, M.Kemal ‘’Control System Design of a vertical take-off
and Landing using UAV’’IFAC Paper 49-3(2016) page:267-272.
[4]Spyridon G.Kontogiaisi, JohnA. Ektateriris’’Design Performance
Evaluation and Optimization of a UAV ‘’16th April 2013.
[5]Lan l turner , Mitchell DHarley, Christopher D Drummond ‘’UAVs for
coastal Surveying’’ 14th December 2015