micro air vehicle-2018-technology



MICRO AIR VEHICLE
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For the most important component, the powerplant, we first chose electric motor as we hoped to power both the motor and the radio receiver by the same battery (in this case a flat lithium-ion Motorola Startec handphone battery weighing only 24g). The motor chosen was the

The microcraft iSTARmicro air vehicle: control system design and testing
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Abstract The iSTARMicro Air Vehicle(MAV) is a unique 9-inch diameter ductedair vehicle weighing approximately 4 lb. The configuration consists of a ducted fan with control vanes at the duct exit plane. This VTOL aircraft not only hovers, but it can also fly at high forward

Update on flapping wingmicro air vehicleresearch-ongoing work to develop a flapping wing, crawling entomopter
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An electromechanical multimode (flying/crawling) insect is being developed by Robert Michelson and his design team at the Georgia Tech Research Institute. The project has received initial IRAD funding from the Georgia Institute of Technology. The mechanical

Design and development of amicro air vehicle( av) concept: Project Bidule
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This paper presents an analysis of the concept of MiniatureAirVehicles andMicro Air Vehicles (respectively mAV and AV) mainly carried out through the development of a mAV prototype called Bidule, which was first successfully flown in 1998. The final objective of

Design, fabrication, and performance test of a hovering-based flapping-wingmicro air vehiclecapable of sustained and controlled flight
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We present our insect-based hovering Flapping-WingMicro Air Vehicle(FW-MAV) capable of sustained flight and control. The proposed design combines two fixed wings and two flapping wings to take advantage of the double clap-and-ling effects at the end of each half-stroke during

Derivation and simulation of the nonlinear dynamics of a flapping wingmicro-air vehicle
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The paper presents a derivation of the equations of motion for a flapping wingmicro-air vehicle. The equations of motion are derived using DAlemberts Principle extended to rigid bodies. Themicro-air vehicleis modeled as aa system of three rigid bodies with rigidly

Flying insect inspired vision formicro-air-vehiclenavigation
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More often homeland security, disaster mitigation and military operations are performed in urban environments. Time consuming, labor intensive and possibly dangerous tasks like bomb detection, search-and-rescue and reconnaissance done with robots could save

Modeling the flight dynamics of amicro air vehicle
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Simulations of micro air vehicles are required for tasks related to mission planning such as control design and flight path optimization. The flight dynamics of these vehicles are difficult to model because of their small size and low airspeeds. This paper discusses a procedure to

A multi modal micro air vehiclefor autonomous flight in near-earth environments
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Unmanned Aerial Vehicles (UAVs) such as the Predator and Global Hawk have been used extensively in Bosnia since 1995 and more recently in Iraq and Afghanistan for intelligence, surveillance and reconnaissance (ISR) gathering (see Figure 1.1 ab). These large-scale

Development of transition control methodology for a quad rotor-biplanemicro air vehiclefrom hover to forward flight
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There is significant interest in the development of efficient and viableMicro AirVehicles (MAVs) that can perform various tasks such as surveillance, targeting, natural disaster support, chemical agent detection etc., which are nominally hazardous or inconvenient for

Lift and thrust characteristics of the flapping wingmicro air vehicle
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This paper concentrates on the effects of the maximum angle of flap and flapping frequency on the thrust and the lift characteristics of the flapping wingmicro air vehicle(MAV). A flapping mechanism powered by small DC motor was designed and fabricated for

Design, fabrication, analysis, and testing of amicro air vehiclepropeller
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icro Air Vehicles (MAVs) have been the subject of increased attention for the past decade because of their potential unique military and civilian applications. 1-3 These include surveillance, search and rescue, and remote detection. Originally, MAVs were

Robotic hummingbird: Design of a control mechanism for a hovering flapping wingmicro air vehicle
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The use of drones, also called unmanned aerial vehicles (UAVs), is increasing every day. These aircraft are piloted either remotely by a human pilot or completely autonomously by an on-board computer. UAVs are typically equipped with a video camera providing a live

Effective Analysis of Positioning System for Group ofMicro Air VehicleSwarms Based on Audio Frequency
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Robustness and efficiency are the two important parameters to judge the performance of any system or technology. Achieving these two characteristics in MovingAir Vehicle(MAV) is always a challenging task. Group of MAVs are best suitable in aerial coverage applications

Experimental studies on a propelledmicro air vehicle
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CL= lift coefficient drag coefficient CM= pitching moment coefficient CS= side force coefficient CYM= yaw moment coefficient CRM= roll moment coefficient CG= center of gravity LAR= low aspect ratio Re= Reynolds number V= velocity (m/s) = angle of attack

Parametric studies and performance analysis of a biplanemicro air vehicle
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This paper presents the experimental investigation of a biplanemicro air vehicle. The effects of geometric parameters, gap, stagger, and decalage angle are investigated at low Reynolds number (~ 150,000) in a low-speed wind tunnel. A rigid flat plate with an aspect

Performance tests of a hovering flapping wingmicro air vehiclewith double wing clap-and-fling mechanism
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Air Vehicle(FW-MAV) named Temasek Laboratories FlowerFly (TL-FlowerFly) having four wings and double clapand-fling mechanism driven by only one motor. The TL-FlowerFly with a wing span of 22 cm from wing tip-to-wing tip and weight of 16.6 grams is fully integrated an

The development of flapping wings for a hoveringmicro air vehicle
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Model update of amicro air vehicle(MAV) flexible wing frame with uncertainty quantification
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This paper describes a procedure to update parameters in the finite element model of a Micro Air Vehicle(MAV) to improve displacement predictions under aerodynamics loads. Because of fabrication, materials, and geometric uncertainties, a statistical approach

Experimental optimization and uncertainty quantification of flapping wing of amicro air vehicle
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Recently, there has been an increase in interest in flapping wingmicro airvehicles as they are capable of hover and forward flight with high maneuverability. Flapping wing flight is difficult to simulate accurately as it is a much more complex phenomena than fixed wing or

Rotary WingMicro Air VehicleEndurance
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One of the first questions to pilots of rotor based electric drivenmicro airvehicles is the possible flight time of the system. The answer is not easy sometimes. The possible flight time is influenced by a lot of important details of themicro air vehicleand the flight mission. At the

Development of the artificial wing suitable for flappingmicro air vehiclebased on dragonfly wing
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The dragonfly wing is passively deformed under flapping and has the strength to withstand high flapping frequency simultaneously. These characteristics of deformation and vibration of the wing is important for dragonfly flight. However, the effect of those on dragonfly flight

Experimental investigation of an insect-based flapping wing hoveringmicro air vehicle
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ABSTRACT A di erential-four-bar based apping mechanism was designed and built to emulate insect wing kinematics with an active pitching ability for a hovering apping-wing micro air vehicle(MAV). The apping mechanism was designed to have symmetric maximum

The University of Florida autonomousmicro air vehicle
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N recent years,Micro Air Vehicle(MAV) development at the University of Florida (UF) has garnered much interest in real-world applications. The MAV Laboratory at UF specializes in the design and creation of small mission capable aircraft under multiple contracts. In

Aerodynamic performances of amicro air vehiclebased on two coaxial counter-rotating rotors
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This study deals with the prediction of the aerodynamic performances of the Gun Launched Micro Air Vehicle(GLMAV) platform by using the ANSYS CFX code. A first step consisted of the validation of the numerical simulation on a two-bladed rotor, which has a diameter of

Control of a Quad Rotor BiplaneMicro Air Vehiclein Transition from Hover to Forward Flight
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Hybridairvehicles can be very useful to perform tasks that require hover and forward flight capability. This paper describes the control development of a quadrotor-biplane hybridair vehicleto enable transition from hover to forward flight mode. Thevehicleweighs about 230

CFD based aerodynamic modeling to study flight dynamics of a flapping wingmicro air vehicle
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The demand for small unmannedairvehicles, commonly termedmicro airvehicles or MAVs, is rapidly increasing. Driven by applications ranging from civil search-and-rescue missions to military surveillance missions, there is a rising level of interest and investment in better

The internationalmicro air vehicleflight competition as autonomy benchmark
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The development ofairvehicles with competitions has a long history . The firstMicro Air Vehiclecompetition was organized in 1997 at the University of Florida, the same year that the first RoboCup was organized in Nagoya, Japan

Axiomatic Design of a Wing Driving Mechanism forMicro Air Vehiclewith Flapping Motion
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ABSTRACT RecentlyMicro AirVehicles (MAVs) imitating the mechanism of birds or insects have been developed. As hummingbirds characteristics are regarded as an appropriate candidate for MAV model, the studies of hummingbirds aerodynamics and mechanics in

Development of a Composite Bendable-WingMicro Air Vehicle
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I. Introduction he InternationalMicro Air VehicleCompetition (IMAVC) has stretched the limits of small aircraft design. The 2006 IMAVC has introduced a new endurance challenge that rewards teams for maximizing the ratio of aircraft flight time to packed volume. TheMicro

Experimental Studies of Propeller Induced Flow over a TypicalMicro Air Vehicle
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I. Introduction he design and development ofMicro AirVehicles (MAVs) has become an important field in the aerospace community for its numerous military and civilian applications like surveillance, search and rescue, damage assessment and reconnaissance. Most of the

Development of ThinkkamanMicro air Vehicleat Rochester Institute of Technology
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This paper details the design and development process of the current RITMicro Air Vehicle over the course of the 2003-2004 academic year. The objective of the RIT MAV Team is to construct an aircraft with minimal dimension that can successfully complete a surveillance

SAM-semi autonomousmicro air vehicle
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Autonomous operating systems, often called robots, fascinate with their behaviour. Most of those systems are ground based, that means they have wheel or legs for moving. Robots cannot fly, cant they There are some experiments existing like the so called UAV

Low-cost Image-assisted Inertial Navigation System for aMicro Air Vehicle
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I. Introduction nmanned aerial robotics systems have become widely used by the military as well as private corporations, research institutions and hobbyists. As with many technologies, the components are now smaller and less expensive to manufacture. These systems often

Design and Testing of a Flapping WingMicro Air Vehicle
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The objective of this MQP is to design, test, and assess the feasibility of a flappingwing remote controlledmicro air vehicle(MAV). The group designed an MAV with a wingspan and total length of under one foot and a weight of under one ounce, similar to existing

Design, Fabrication and Testing of Flapping WingMicro Air Vehicle
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Flapping flight has the potential to revolutionizemicro airvehicles (MAVs) due to increased aerodynamic performance, improved maneuverability and hover capabilities. The purpose of this project is to design and fabrication of flapping wingmicro air vehicle. The designed

Iterative Learning Auto-tuned PID Controller forMicro-UnmannedAir Vehicle
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This paper investigated the design of a proportional-integral-derivative (PID) controller for MicroUnmannedAir Vehicle(Micro-UAV).Micro-UAV considered in this paper is a vertical takeoff and landing (VTOL) type UAV. By designing the best PID controller, the stability of the

Stability of a flapping wingmicro air vehicle
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An experimental investigation into the stabiiii of a flappiug wingmicro air vehiclewas perfomied at the University of Toronto Institute for Aerospace Studies. A thtee-degree of W om force balance was designed and constnicted to measure the forces and moments

Optimization ofmicro air vehicleairfoil
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AbstractMicro AirVehicles (MAVs) are small and undetectable, with a wing span of around 150mm and weighs 200 grams. Over the past decade, MAVs are gaining importance in research due to their unique capability. They are untraceable by humans at 100m above the

FPGA Implementation of Image Fusion Technique Using DWT forMicro Air VehicleApplications
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The vital and increasing role of unmanned autonomous vehicles (UAVs) throughout the military applications is now well appreciated. Multiple onboard sensors on UAV are used to collect data and they are fused to extract information. In recent years, significant attention






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