Design of an Unmanned Aerial Vehicle for Emergency Situations (original) (raw)

Technical Development of Design & Fabrication of an Unmanned Aerial Vehicle

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.

Design and Analysis of Unmanned Aerial Vehicle

2016

UAV is a most rapidly growing sector today with its application ranging from Defense, Surveillance to personal hobbies. A UAV is a radio-controlled Aircraft which will have flying range of 500 meters‘ radius. It can be equipped with a camera which will be useful for surveillance purpose. The UAV can also be used in rescue mission to provide food, medicines and other utility products in areas affected by natural calamities, where it is out of human reach. The UAV‘s are also used by Army and Air force for short missions (e.g. dropping a bomb) in enemy dormitories. The advantage of the same is safety as no human is involved and because of its low cost. Our UAV will be controlled using a radio frequency of 2.4 GHz. The control surfaces will be controlled through servo motors and the engine will be a brushless DC motor connected with an electric speed control and the power source will be Lithium Polymer battery. The key components that will be designed are the Wings, Control Surfaces and...

DESIGNING AND DEVELOPMENT OF UNMANNED AERIAL VEHICLE

2002

With the advancement in science and technology, the aviation industry is increasingly concentrating on the development of Remotely Piloted Vehicles (RPVs), Unmanned Aerial Vehicles (UAVs) and Unmanned Combat Aerial Vehicles (UCAVs). The Unmanned Aerial Vehicle (UAV) are being used for many years for a variety of different tasks like reconnaissance, bomb damage assessment (BDA), scientific research, escort EW, decoying guiding SAMs and AAMs, and target practice. These UAVs will replace the conventional aircraft in several roles and even perform novel assignments. The hostile battlefield environments and difficult access areas can be monitored without endangering human life. This paper elaborate the designing of UAV that can be used as interceptor and can perform reconnaissance/survillance missions as well.

Conceptual design , Structural and Flow analysis of an UAV wing Abdus

2016

Unmanned Aerial Vehicles (UAVs) are considered as the largest integration of modern technology which have enormous potential for both military special operations & civil applications. UAVs are often preferred for missions that are too "dull, dirty, and dangerous". Its efficiency & success depends on factors such as performance, maintenance costs, design etc. This Paper aims to optimize the design of the wing of a medium size surveillance type UAV, by carrying out both analytical and computational analysis of aerodynamic and structural loads & also to study various materials and techniques for the fabrication of the designed wing. During the study, an attempt was made to familiarize with the theoretical aerodynamics, aircraft structural design methodologies and historical trends in wing design. The preliminary design dimensions as well as relevant loads of the wing structure were calculated based on the design lift and loading requirement for the UAV. The wing design was fu...

Design Development and Fabrication of Unmanned Aerial Vehicle

International Journal For Research In Applied Science & Engineering Technology, 2020

UAV or an unmanned aerial vehicle is a remote-controlled aircraft. It can be operated remotely in real-time or pre-programmed to fly autonomously on the pre-defined routes. These aircraft help police, fire and other first responders save lives in the event of natural disasters, locate missing children and help fight wildfires. They assist the Coast Guard in rescue missions and help the Border Patrol keep our nation secure. They boost agricultural production and allow us to better protect the environment. Moreover, UAS have virtually no limitations, with the ability carry out such work in hazardous conditions, darkness, extreme heat and a host of other conditions that may pose significant risks to manned aircraft. I. INTRODUCTION Airplane, also called aero plane or plane, any of a class of fixed-wing aircraft that is heavier than air, propelled by a screw propeller or a high-velocity jet, and supported by the dynamic reaction of the air against its wings.Aerodynamics and the loads are derived from aerodynamic considerations. Usage and analysis of airfoil shapes for determination of lift and moment coefficients, pressure distributions. Structural design, analysis, and testing of our model is made. Solid modeling of the plane, electronics and radio control. Work delegation and time budgeting are the main aspect in this project. The goal of this undertaking is to gather engineering knowledge and skill, master new techniques and information and apply these to produce a successful design and fabrication of a radio-controlled aircraft.The aircraft should be able to perform such that it is capable of earning points at each level of the event. That is, it should be capable of lifting as much weight as possible while at the same time maintaining a very less weight of itself. Aerobatic performance is of no concern; rather, good lifting qualities at low speed and stable configuration are primary factors to be considered.

Design and implementation of an unmanned aerial vehicle for autonomous firefighting missions

2016 12th IEEE International Conference on Control and Automation (ICCA), 2016

The article aims to prove the effectiveness of the proposed unmanned air vehicle design (The Propulsive Wing) through numerical and experimental means. The propulsive wing unmanned air vehicle is a completely new class of unmanned air vehicle, making disruptive changes in the aircraft industry. It is based on a distributed cross-flow electric fan propulsion system. When the fan starts to operate, the flow is drawn from the suction surface, provided by energy through the fan and expelled out of the airfoil trailing edge (TE). This causes a significant lift increase and drag reduction with respect to ordinary aircrafts, making it perfect for applications requiring low cruise speed such as firefighting, agriculture, and aerial photography. In this early stage of the investigation, our main aim is to prove that this design is applicable and the expected aerodynamic and propulsion improvements are achievable. This is done through a two-dimensional computational fluid dynamics investigation of the flow around an airfoil with an embedded cross-flow fan near its TE. A scaled wind tunnel model of the same geometry used in the computational fluid dynamics investigation was manufactured and used to perform wind tunnel testing. The computational fluid dynamics and wind tunnel results are compared for validation. Furthermore, an unmanned air vehicle model was designed and manufactured to prove that the propulsive wing concept is flyable. The article shows that the aerodynamic forces developed on the cross-flow fan airfoil are not only functions of Reynolds number and angle of attack as for standard airfoils but also function of the fan rotational speed. The results show the great effect of the rotational speed of fan on lift augmentation and thrust generation through the high momentum flow getting out of the fan nozzle. Wind tunnel tests show that the suction effect of the fan provides stall free operation up to very high angles of attack (40 degrees) leading to unprecedented values of lift coefficient up to 5.8. The flight test conducted showed the great potential of the new aircraft to perform the expected low cruise speed and high angles of attack flight.

Evaluation of Novel Wing Design for UAV

Viable design alternative for the existing and fast growing UAVs, which are optimized for unmanned flight, is of great demand. Designing of a small scale UAV alternative to the AAI Aerosonde UAV has been considered changing the wing tail configuration of the vehicle analyzing both structural and aerodynamic performance improvements using COMSOL Multiphysics. Various Non-Planar design alternatives have been considered and box wing configuration has been proven to be the best suited for the application. Variations in the design with box wing configuration have been analyzed by using Tornado scrip in Matlab and the important configurations have been analyzed using the CFD module for aerodynamics and Multiphysics for structural performance. The NACA 0012, Ahmed body models have been very much helpful in learning COMSOL and applying it to the present situation for reducing the solving time and increasing the accuracy of solving the problem

Design and performance analysis of unmanned aerial vehicle (UAV) to deliver aid to the remote area

International Conference on Mechanical, Industrial and Material Engineering, 2017

The Small Unmanned Aerial Vehicle is playing an increasingly significant role in modern military and civil arena. The list of potential uses is now rapidly expanding to encompass a broad range of other activities, including aerial photography, surveying land and crops, communications and broadcast, monitoring forest fires and environmental conditions, and protecting critical infrastructures. An Unmanned Aerial Vehicle named 'Mohapotongo' has been designed with the capability of carrying medical aid to remote areas. The Mohapotongo is an advanced, durable, lightweight aircraft designed to carry 700gm of payload covering a range of 20km.Via the autonomous system in Mohapotongo, it can gain information about the environment, work for an extended period without human intervention, move either all or part of itself throughout its operating environment without human assistance and its building structure enable it to carry easily. The Mohapotongo is a canard configured aircraft with the capability of hand-launch or pod launch and is incorporated into the battery powered the electric motor. The overall design process has been done using system engineering process. This paper presents the design methodology, performance analysis, and manufacturing process of the UAV Mohapotongo.

AIR AMBULANCE DRONE -A MODERN CONCEPTUAL AERIAL VEHICLE FOR SURVEILLANCE AND CASUALTY EVACUATION

Transstellar Journals, 2019

The present works discuss the design of an Air Ambulance Drone (AAD), anuncrewed aerial vehicle or UAV has the ability to perform an operation to handle numerous activities like vigilance, saving people, any unpleasant circumstancesand evacuation of wounded. The computations of Preliminary design of the present AAD had been summarized in detail, which includes the structural, propulsive, aerodynamic and performance aspects. The innovative AAD employs the numerous techniques that identify the survivor, final design and so on, had been deliberated in these researches. The design has been made in Fusion 360 software and is presented. The peculiarities, significance and applications of present AAD have been discussed.