Download or read book Design Study of a High Altitude Morphing UAV with Analysis of Low Reynolds Number Parawing Aerodynamics written by Peter Antoine Munther and published by . This book was released on 2006 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The study of this thesis concerned the development of a high altitude (70,000ft to 100,000ft) UAV which utilized a parawing-type wing along with a gimbaled pusher prop that was used for thrust as well as longitudinal stability and control purposes. First, an initial design study was performed based on a chosen thrust available requirement of I2HP and a cruise velocity requirement of l2OftIs at an altitude of 100,000ft. Additionally, the study was based on the idea that the aircraft should not be lengthy in structure. This led to the determination of a wing area of 1 8,000ft2 given that (L/D)max was 5.5 along with a CL of 0.6, as found from historical parawing analyses. This wing area was found to have met the desired dimensions of an equal length fuselage and wing leading edge of about 5Oft. These parameters dictated a low Reynolds number of 6.6X105 for the cruise condition at 100,000ft. For the found geometry it was necessary to maintain a leading edge sweep, A, of 270. However, historical parawing tests did not provide data concerning a A below 350. This motivated low leading edge sweep parawing wind tunnel tests. A model was built and tested matching the cruising Re of 6.6X105 at leading edge sweeps of 450, 300, 150, and 00 along with flat-planform leading edge sweeps, [Lamda]0, of 380, 230, 80, and -70 respectively to allow for billow. Wind tunnel tests showed that for the case where [Lamda] was 00 (with a [Lamda]0 of -70) provided the maximum values for (L/D)max and (L312/D)max at a 4.6 and 3.9 respectively. However, results for the other cases of leading edge sweep were relatively close in value. The magnitude of the values for CMa.c. were large, ranging from -0.104 to -0.323. Additionally, the a.c. locations were found to be in-front of the leading edge of the wings for all cases, moving further out as [Lamda] decreased. Data trends were created from the wind tunnel test data along with historical data in order to study the flight capabilities of the aircraft for a range of [Lamda] from 00 to 800. It was found that the THPA was sufficient to allow for flight at both extremes of altitudes at the desired cruise velocity without consideration to longitudinal stability and control. In studying the longitudinal stability and control aspects or the aircraft, it was found that the locations of the a.c. were not favorable as a large moment about the c.g. of the aircraft was produced. This proved to be a formidable challenge for static longitudinal control purposes, where it was found that the aircraft could only reach a maximum altitude of 74,000ft, requiring a vectored thrust angle, [delta][lamda], of 600. This occurred for a [Lamda] of 120 at a velocity of 54ft/s. However, by theoretically moving the a.c. closer to the c.g. it was found that flight at the extreme case of 100,000ft at the desired cruise velocity was able to be reached while maintaining static longitudinal stability with a [delta][lamda] 90. This occurred ata [Lamda] of 410. A full-state feedback dynamic longitudinal stability analysis was performed for the case of flight at 70,000ft demonstrating that the aircraft was naturally unstable but controllable utilizing the designed control system. The state responses to a disturbance in flight angle, [theta], of 50 are shown as an example. This analysis provided the equations for the control stability derivates, which were applicable to all flight cases. Overall, the study of aircraft proved to be beneficial. The results from the wind tunnel testing proved that a parawing could operate at very low leading edge sweeps. However, because of the large aerodynamic moments due to the forward position of the a.c., the longitudinal stability and control system performed poorly. Either the a.c. would need to be changed or a new longitudinal stability and control system would need to be developed to produce a successful UAV.

Download or read book Design and Development of a High altitude In flight deployable Micro UAV written by Tony S. Tao and published by . This book was released on 2012 with total page 143 pages. Available in PDF, EPUB and Kindle. Book excerpt: A micro-UAV ([mu] UAV) system was developed to provide maximum endurance for a small atmospheric sensing payload. The system, composed of a ([mu] UAV) and protective case, folds and fits into a MJU-10/B flare cartridge (7.1" x 2.4" x 1.9") and is designed to be ejected in-flight from altitudes up to 30,000 ft at 300 G, to open and unfold in freefall, and to autonomous fly, sense, and transmit data for up to 45 minutes at maximum altitude. The[mu]UAV has a wingspan of 11.8", a length of 6.6", and a mass of 220 grains. Guided by first-principles, a series of design studies are conducted to maximize the airframe performance. The[mu]UAV is refined through computational analysis, prototyping, and a multi-phase testing program involving wind tunnel, structural shock, and deployment tests. A series of airfoils was developed for the low Reynolds numbers in which the wings operate (between 30,000 and 80,000) and for manufacturing considerations. Detailed design of aircraft components is presented with a discussion of small-scale composites manufacturing processes. Folding and control mechanisms were developed to actuate control surfaces on a swinging wing. The resulting design carefully balances low Reynolds number aerodynamic effects, small-scale composite structures, and manufacturing capabilities in a configuration that offers unprecedented endurance (for aircraft of this size and altitude) in a widely-compatible package with mission-reconfigurable payload.

Download or read book A Design for a High Altitude Flight Test System written by Kristen Erin Wahlers and published by . This book was released on 2006 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Small UAV's and flight vehicles in other atmospheres such as Mars are characterized by low Reynolds numbers. Low Reynolds number airfoil testing has been difficult to achieve and there are few centers that can accomplish this task. This study is an effort to develop a flight test system that will enable low Reynolds number tests to be performed with a simple glider design. The concept is to develop a high altitude glider that will be transported to altitudes reaching 100,000 feet or more by a helium filled balloon. At altitude, the glider will be released and will perform flight experiments as it descends. This region of Earth's atmosphere, 'near space' has the conditions desired for low Reynolds number testing as well as similar properties to the surface of Mars. With the knowledge gained from this experiment, a better understanding of accomplishing flight on Mars may be attained.

Download or read book Low Reynolds Number Aerodynamics of a UAV Wing Under Icing Condition written by Nay Lin Oo and published by . This book was released on 2020 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Small size Unmanned Aerial Vehicles (UAVs) are designed to operate in various types of weather conditions. Of these, flying under icing conditions is one of the most challenging tasks because the streamline profile of the wing is altered by ice-accretion on the leading-edge. To enhance our understanding of the impacts of ice-accretion on small UAV's, an experimental and numerical analysis of the low Reynolds number aerodynamics of an ice-accreted RG-15 aerofoil was undertaken. The RG-15 aerofoil, which is a typical form used for UAV wing profiles, was tested in a wind tunnel at three Reynolds numbers, i.e., 5Ã-10â ́,1Ã-10â μ and 2Ã-10â μ, which are based on the chord of the clean aerofoil. The aerofoil was tested with four configurations, which are clean (without ice), with an original ice shape generated in an icing wind tunnel (Ice 1), and two further ice shapes obtained by enlarging the original ice shape (Ice 2 and Ice 3). Fluctuating pressure measurements were made using a multi-channel pressure acquisition system, to help reveal the time-averaged and unsteady aerodynamic behaviour. To compensate for the frequency limitations of the pressure system, a series of microphones were embedded to measure the boundary layer instabilities for both clean and ice-accreted aerofoils. In addition to that, a hotwire anemometer was utilized for only Ice 1 configurations, to obtain the level of turbulence generated from the ice. Moreover, Large Eddy Simulations were conducted for specific cases, to achieve an in-depth understanding and visualization of the flow field around the aerofoil. From the experimental investigations, the original ice shape (Ice 1) has only a minimal effect, whereas, the largest ice shape (Ice 3) caused a decrease in maximum lift of 14.2%, and increase in drag of up to 182%. These suggest that a small amount of streamwise ice at the leading-edge is relatively safe for UAV flight. However, with larger ice accretions there is an obvious increase in drag, which is hazardous for the operation of the UAV. A detailed study of the surface pressure measurements reveals the presence of separation bubbles on both clean and iced aerofoils. On the clean aerofoil, the laminar separation bubble (LSB) moves upstream and reduces in its extent with an increase in angle of attack. Also, the presence of freestream turbulence or increase in flow Reynolds number reduces the size of the LSB. Unlike the LSB, an ice-induced separation bubble (ISB) always remains anchored around the leading-edge regardless of the Reynolds number and angle of attack, in addition, the extent of the ISB is dependent on both Reynolds number and angle of attack. Moreover, the instabilities from the ISB are similar to those observed for the conventional LSB, where the dominant frequencies are typically higher than those of vortex shedding, with a Strouhal number higher than 0.64. Furthermore, the shear layer instability frequencies were observed to have a power law dependency on Reynolds number, with an exponent between 1.24 and 1.64 on the clean aerofoil, and 1.11 to 1.14 on the ice-accreted aerofoil. While comparing the convective velocities of the shear layer instabilities, the ISB on the original ice shape (Ice 1) was found to have a faster velocity than that of the LSB. The numerical simulations, based on Large Eddy Simulations, show good agreement with the experimental results, such as in the locations and the extent of both LSB and ISB. The numerical simulation also shows the ice on the leading-edge behaves like a turbulence generator, which increases the lift coefficient on the ice-accreted RG-15 aerofoil at 0° angle of attack. Normally, an iced aerofoil only shows the formation of an ISB, but at one of the lowest Reynolds numbers,5x104, and at certain angles of attack, both an ISB and LSB were observed in the present study. While the ISB exists and remains anchored around the leading-edge of the aerofoil at all times, the level of turbulence generated by the ISB has a significant effect on the development of the secondary separation bubble (i.e. LSB), which was only observed under certain conditions.

Download or read book Small Unmanned Fixed wing Aircraft Design written by Andrew J. Keane and published by John Wiley & Sons. This book was released on 2017-08-29 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt: Small Unmanned Fixed-wing Aircraft Design is the essential guide to designing, building and testing fixed wing UAVs (or drones). It deals with aircraft from two to 150 kg in weight and is based on the first-hand experiences of the world renowned UAV team at the UK’s University of Southampton. The book covers both the practical aspects of designing, manufacturing and flight testing and outlines and the essential calculations needed to underpin successful designs. It describes the entire process of UAV design from requirements definition to configuration layout and sizing, through preliminary design and analysis using simple panel codes and spreadsheets to full CFD and FEA models and on to detailed design with parametric CAD tools. Its focus is on modest cost approaches that draw heavily on the latest digital design and manufacturing methods, including a strong emphasis on utilizing off-the-shelf components, low cost analysis, automated geometry modelling and 3D printing. It deliberately avoids a deep theoretical coverage of aerodynamics or structural mechanics; rather it provides a design team with sufficient insights and guidance to get the essentials undertaken more pragmatically. The book contains many all-colour illustrations of the dozens of aircraft built by the authors and their students over the last ten years giving much detailed information on what works best. It is predominantly aimed at under-graduate and MSc level student design and build projects, but will be of interest to anyone engaged in the practical problems of getting quite complex unmanned aircraft flying. It should also appeal to the more sophisticated aero-modeller and those engaged on research based around fixed wing UAVs.

Download or read book A Conceptual Design Methodology for Low Speed High Altitude Long Endurance Unmanned Aerial Vehicles written by and published by . This book was released on 2009 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A conceptual design methodology was produced and subsequently coded into a Visual C++ (GUI) environment to facilitate the rapid comparison of several possible configurations to satisfy High Altitude Long Endurance (FIALE) unmanned aircraft (UAV) missions in the Low Speed (propeller driven aircraft) regime. Several comparative studies were performed to verify the applicability of traditional design methods. The traditional computational design methodologies fail in several areas such as high aspect ratio wing weight estimation and design, low Reynolds number wing design, high altitude engine performance, low Reynolds number drag estimation, unmanned aircraft design, and the conceptual design of unconventional configurations. The methodology developed for this thesis was robust enough to allow not only for consideration of these areas of inadequacy in traditional methods, but also to allow for the inclusion of advancements in the relevant technologies as they become more widely available. The following configurations were evaluated for suitability to the Low Speed HALE UAV application: conventional, canard, twin boom, multiple fuselage (conventional or canard), tandem wing, multiple fuselage tandem wing or flying wing configuration. The configurations were compared on the basis of aircraft endurance for takeoff weights ranging from 2,000 to 20,000 pounds and wing loadings ranging from 5 to 25 lbs1fe. Initial drag estimates were made using traditional parabolic drag estimation techniques. A more refined drag buildup was performed using a vortex lattice drag estimation for the lift induced drag (for all lifting components) and calculated skin friction coefficients for the parasite drag. Statistically based methods were used for other components of drag having much smaller contributions. In addition, a statistical approach was taken to the weight estimation of the major aircraft components. However, this approach made comparison of alternative configurations more difficu.

Download or read book Unmanned Aircraft Design written by Mohammad Sadraey and published by Springer Nature. This book was released on 2022-05-31 with total page 193 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides fundamental principles, design procedures, and design tools for unmanned aerial vehicles (UAVs) with three sections focusing on vehicle design, autopilot design, and ground system design. The design of manned aircraft and the design of UAVs have some similarities and some differences. They include the design process, constraints (e.g., g-load, pressurization), and UAV main components (autopilot, ground station, communication, sensors, and payload). A UAV designer must be aware of the latest UAV developments; current technologies; know lessons learned from past failures; and they should appreciate the breadth of UAV design options. The contribution of unmanned aircraft continues to expand every day and over 20 countries are developing and employing UAVs for both military and scientific purposes. A UAV system is much more than a reusable air vehicle or vehicles. UAVs are air vehicles, they fly like airplanes and operate in an airplane environment. They are designed like air vehicles; they have to meet flight critical air vehicle requirements. A designer needs to know how to integrate complex, multi-disciplinary systems, and to understand the environment, the requirements and the design challenges and this book is an excellent overview of the fundamentals from an engineering perspective. This book is meant to meet the needs of newcomers into the world of UAVs. The materials are intended to provide enough information in each area and illustrate how they all play together to support the design of a complete UAV. Therefore, this book can be used both as a reference for engineers entering the field or as a supplementary text for a UAV design course to provide system-level context for each specialized topic.

Download or read book Aerodynamic Design of Long Endurance Convertible UAV written by Yuchen Leng and published by . This book was released on 2020 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The research objective is to establish a complete methodology for long endurance unmanned aerial vehicle (UAV) with vertical take-off and landing (VTOL) capability, or transitioning UAV. In the thesis, key technical challenges will be identified and simulated using reduced-order models to form a rapid engineering method in assisting aerodynamic design of such vehicles. In view of maximizing the performance of long endurance transitioning UAVs, critical technologies include: 1) propulsion/airframe integration; 2) aerodynamic effects of flight control configuration; 3) system level overall aerodynamic optimization. Calculating methods for each problem will be developed based on existing theories. The solution will be validated with campaigns of high fidelity numerical simulation such as URANS or Boltzmann Lattice Method. Component or full configuration experiments will also be conducted using low Reynolds Number wind tunnel at ISAE. Studies on the propulsion integration will be conducted within the first year. In transition flight, propeller performance at high incidence differs significantly from cruise flight, and the close presence of wings also alters lift and drag distribution. For this reason a reduced-order model for propeller at high incidence angle will be developed based on Leishman's BEMT method [1]. The skewed slipstream will be modelled by modifying conventional method such as Selig [2]. Propeller model will be combined with a propeller-wing interaction analysis based on Veldhuis [3] to study critical parameters during transition flight. The static and dynamic aerodynamic force and moments generated by control surfaces are critical for robust transition flight control, and therefore a configuration study will then be conducted comparing potential transitioning UAV configurations with different propeller arrangements and flight control surface layouts. Following the work by McCormick [4] and Phillips [5], detailed study on the longitudinal and lateral aerodynamic moment characteristics of different configurations will be carried before summer 2019 for transition flight regime. Final phase of the thesis will be devoted to integrating various reduced-order models for propulsion integration, flight control analysis and classic cruise performance analysis to form a platform for overall aerodynamic optimization to assist design long endurance transitioning UAV. The method will be demonstrated through a prototype analysis consistent with specifications from DelairTech. Through collaboration with ENAC, a prototype will be manufactured to demonstrate the developed technologies. The prototype design will incorporate flight control law implemented by Paparazzi autopilot platform, and data acquired from actual flight tests will further validate the methodology in operational environment. The final methodology of aerodynamic design will be available in the form of open source computer program as well as published manuscript. Refs: [1] Leishman, Gordon J. Principles of helicopter aerodynamics with CD extra. Cambridge university press, 2006. [2] Selig, Michael S. 'Modeling propeller aerodynamics and slipstream effects on small UAVs in realtime.' AIAA Paper 7938 (2010). [3] Veldhuis, L. M., “Review of Propeller Wing Aerodynamic Interference,” ICAS 2004, 24th international congress of the aeronautical sciences, 2004. [4] McCormick, Barnes Warnock. Aerodynamics, aeronautics, and flight mechanics. Vol. 2. New York: Wiley, 1995. [5] Phillips, Warren F. Mechanics of flight. John Wiley & Sons, 2004.

Download or read book Advanced UAV Aerodynamics Flight Stability and Control written by Pascual Marqués and published by John Wiley & Sons. This book was released on 2017-07-11 with total page 799 pages. Available in PDF, EPUB and Kindle. Book excerpt: Comprehensively covers emerging aerospace technologies Advanced UAV aerodynamics, flight stability and control: Novel concepts, theory and applications presents emerging aerospace technologies in the rapidly growing field of unmanned aircraft engineering. Leading scientists, researchers and inventors describe the findings and innovations accomplished in current research programs and industry applications throughout the world. Topics included cover a wide range of new aerodynamics concepts and their applications for real world fixed-wing (airplanes), rotary wing (helicopter) and quad-rotor aircraft. The book begins with two introductory chapters that address fundamental principles of aerodynamics and flight stability and form a knowledge base for the student of Aerospace Engineering. The book then covers aerodynamics of fixed wing, rotary wing and hybrid unmanned aircraft, before introducing aspects of aircraft flight stability and control. Key features: Sound technical level and inclusion of high-quality experimental and numerical data. Direct application of the aerodynamic technologies and flight stability and control principles described in the book in the development of real-world novel unmanned aircraft concepts. Written by world-class academics, engineers, researchers and inventors from prestigious institutions and industry. The book provides up-to-date information in the field of Aerospace Engineering for university students and lecturers, aerodynamics researchers, aerospace engineers, aircraft designers and manufacturers.

Download or read book Design and Dynamic Analysis of a Variable Sweep Variable Span Morphing UAV written by Nirmit Prabhakar and published by . This book was released on 2014 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis considers the dynamic effects of morphing for a variable-sweep, variable-span UAV. A scale model of such a morphing wing has been fabricated and tested in the low-speed wind tunnel at Embry-riddle Aeronautical University. The focus of this thesis is the development of a dynamic model for this morphing wing UAV that accounts for not only the varying dynamics resulting from different static morphing configurations, but also the transient dynamics associated with morphing wing UAV over a two-dimensional array of static configurations corresponding to varying span and sweep. In this analysis, only symmetric morphing configurations are considered (i.e., in every configuration, both wings have the same span and sweep); therefore, the analysis focuses on the longitudinal dynamic modes (i.e., the long period and short period modes). The dynamic model of the morphing wing UAV is used to develop a simulation in which it is possible to specify different morphing configurations as well as varying rates of morphing transition. As such, the simulation provides an invaluable tool for analyzing the effects of wing morphing on the longitudinal flight dynamics of a morphing UAV.

Download or read book Over 40 Publications Studies Combined UAS UAV Drone Swarm Technology Research written by and published by Jeffrey Frank Jones. This book was released on with total page 3840 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design of Unmanned Aerial Systems written by Mohammad H. Sadraey and published by John Wiley & Sons. This book was released on 2020-02-20 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt: Provides a comprehensive introduction to the design and analysis of unmanned aircraft systems with a systems perspective Written for students and engineers who are new to the field of unmanned aerial vehicle design, this book teaches the many UAV design techniques being used today and demonstrates how to apply aeronautical science concepts to their design. Design of Unmanned Aerial Systems covers the design of UAVs in three sections—vehicle design, autopilot design, and ground systems design—in a way that allows readers to fully comprehend the science behind the subject so that they can then demonstrate creativity in the application of these concepts on their own. It teaches students and engineers all about: UAV classifications, design groups, design requirements, mission planning, conceptual design, detail design, and design procedures. It provides them with in-depth knowledge of ground stations, power systems, propulsion systems, automatic flight control systems, guidance systems, navigation systems, and launch and recovery systems. Students will also learn about payloads, manufacturing considerations, design challenges, flight software, microcontroller, and design examples. In addition, the book places major emphasis on the automatic flight control systems and autopilots. Provides design steps and procedures for each major component Presents several fully solved, step-by-step examples at component level Includes numerous UAV figures/images to emphasize the application of the concepts Describes real stories that stress the significance of safety in UAV design Offers various UAV configurations, geometries, and weight data to demonstrate the real-world applications and examples Covers a variety of design techniques/processes such that the designer has freedom and flexibility to satisfy the design requirements in several ways Features many end-of-chapter problems for readers to practice Design of Unmanned Aerial Systems is an excellent text for courses in the design of unmanned aerial vehicles at both the upper division undergraduate and beginning graduate levels.

Download or read book Smart Morphing and Sensing for Aeronautical Configurations written by Marianna Braza and published by Springer Nature. This book was released on 2023-02-14 with total page 287 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book reports on advanced strategies to design, modeling and testing morphing wings for aeronautical applications. Covering the major outcomes of the multidisciplinary project “Smart Morphing & Sensing” (H2020 N° 723402 SMS), funded by the European Union between 2017 and 2020, it presents a complete set of theories and methods that have been used and developed to integrate novel electroactive actuators and sensors in wings, for the purpose of increasing their aerodynamic efficiency and attenuate vibrations and noise. Topics include: integrated aeroelastic design of morphing wings using high-fidelity computational fluid dynamics and structural mechanics, distributed sensing using a new generation of high-fidelity fiber optics sensors, and controller design by appropriate flight control commands. Further, the book reports on advanced experimental techniques to validate novel actuation and sensing systems on the built prototypes via wind tunnel tests at subsonic (take-off and landing) and transonic (cruise) speeds. All in all, this volume provides readers with extensive and timely information on research and developments of bioinspired aircraft wings.

Download or read book Unmanned Aircraft Design written by Mohammad Sadraey and published by Morgan & Claypool. This book was released on 2017-09 with total page 193 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides fundamental principles, design procedures, and design tools for unmanned aerial vehicles (UAVs) with three sections focusing on vehicle design, autopilot design, and ground system design. The design of manned aircraft and the design of UAVs have some similarities and some differences. They include the design process, constraints (e.g., g-load, pressurization), and UAV main components (autopilot, ground station, communication, sensors, and payload). A UAV designer must be aware of the latest UAV developments; current technologies; know lessons learned from past failures; and they should appreciate the breadth of UAV design options. The contribution of unmanned aircraft continues to expand every day and over 20 countries are developing and employing UAVs for both military and scientific purposes. A UAV system is much more than a reusable air vehicle or vehicles. UAVs are air vehicles, they fly like airplanes and operate in an airplane environment. They are designed like air vehicles; they have to meet flight critical air vehicle requirements. A designer needs to know how to integrate complex, multi-disciplinary systems, and to understand the environment, the requirements and the design challenges and this book is an excellent overview of the fundamentals from an engineering perspective. This book is meant to meet the needs of newcomers into the world of UAVs. The materials are intended to provide enough information in each area and illustrate how they all play together to support the design of a complete UAV. Therefore, this book can be used both as a reference for engineers entering the field or as a supplementary text for a UAV design course to provide system-level context for each specialized topic.

Download or read book Perpetual Flight written by Jiunn Wong and published by . This book was released on 2004 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Optimizing Small Multi Rotor Unmanned Aircraft written by Stephen D. Prior and published by CRC Press. This book was released on 2018-09-18 with total page 129 pages. Available in PDF, EPUB and Kindle. Book excerpt: This design guide was written to capture the author’s practical experience of designing, building and testing multi-rotor drone systems over the past decade. The lack of one single source of useful information meant that the past 10 years has been a steep learning curve, a lot of self-tuition and many trial and error tests. Lessons learnt the hard way are not always the best way to learn. This book will be useful for the amateur drone pilot who wants to build their own system from first principles, as well as the academic researcher investigating novel design concepts and future drone applications.

Download or read book Multi rotor Platform Based UAV Systems written by Franck Cazaurang and published by Elsevier. This book was released on 2020-02-28 with total page 268 pages. Available in PDF, EPUB and Kindle. Book excerpt: Multi-rotor Platform Based UAV Systems provides an excellent opportunity for experiential learning, capability augmentation and confidence-building for senior level undergraduates, entry-level graduates, engineers working in government agencies, and industry involved in UAV R&D. Topics in this book include an introduction to VTOL multi-copter UAV platforms, UAV system architecture, integration in the national airspace, including UAV classification and associated missions, regulation and safety, certification and air traffic management, integrated mission planning, including autonomous fault tolerant path planning and vision based auto landing systems, flight mechanics and stability, dynamic modeling and flight controller development. Other topics covered include sense, detect and avoid systems, flight testing, including safety assessment instrumentation and data acquisition telemetry, synchronization data fusion, the geo-location of identified targets, and much more. Provides an excellent opportunity for experiential learning, capability augmentation and confidence building for senior level undergraduates, entry-level graduates and engineers working in government, and industry involved in UAV R&D Includes MATLAB/SIMULINK computational tools and off-the-shelf hardware implementation tutorials Offers a student centered approach Provides a quick and efficient means to conceptualize, design, synthesize and analyze using modeling and simulations Offers international perspective and appeal for engineering students and professionals