INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL an Opportunity for Electric Planes and Uavs

Total Page:16

File Type:pdf, Size:1020Kb

INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL an Opportunity for Electric Planes and Uavs “The future of aviation is electric” Dr Susan Ying, President of the International Council of Aeronautical Science and former Director of Boeing Research and Technology. WHITEPAPER INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL An Opportunity for Electric Planes and UAVs CONTENTS EXECUTIVE SUMMARY Executive summary ..........................1 It is well established that adding solar cells to UAVs and manned electric aircraft is beneficial – the sun is an inexpensive, renewable, and plentiful What is holding back source of energy. So if the advantage of solar is clear, why don’t we see the solar aircraft industry?..............1 solar aircraft in the market? Electric aircraft revolution ..............2 Industry opinion is that a solution is required to enable drones to fly as long as needed. That solution has not been forthcoming. The approach The limiting factor has to date has been to glue solar cells on top of aircraft wings, but this is been battery technology .................3 inefficient, adds weight, and is not particularly aerodynamic. Solar cells are fragile and so far there has been no way to integrate solar cells into Challenging the status quo .............3 wing materials that was robust, inexpensive and light. Solar cell composites - Praxis Aeronautics deduced – from its own experience in composite a solution .............................................4 and aeronautical engineering – that what the industry needed was an aerodynamic solution that would enable solar cells to be shaped and From invention to reality ..................5 integrated into the product. The solution would need to make the cells flexible and able to efficiently absorb light. Praxis Aeronautics has Conclusion ..........................................6 developed a solution that meets these criteria. About Praxis Aeronautics ...............6 WHAT IS HOLDING BACK THE SOLAR AIRCRAFT INDUSTRY? The first manned solar aircraft flew in 1974. More than 40 years later, there are many examples of experimental solar aircraft and unmanned aerial vehicles (known as UAVs or drones), but they are yet to become a commercial reality. INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL WHITEPAPER Today’s UAVs are used by individuals through to large commercial operators for increasingly diverse applications, such as aerial surveying, agriculture and law enforcement. They also play a significant role in defence operations. Electric UAVs are used primarily because of their relatively lower cost, higher safety rating and simplicity of use. However due to battery limitations, electric drones have the major disadvantage of a flying time typically limited to around 1 hour. A new technical approach is needed to enable industries such as Defence, Agribusiness, and the commercial Aerospace industry itself to push the boundaries of drone capabilities. This paper discusses the historic problem, current thinking – and provides a solution to this problem. EVOLUTION OF SOLAR AVIATION ELECTRIC AIRCRAFT REVOLUTION 1974 SUNRISE 1 First solar UAV 1975 SUNRISE 2 The use of electric power for flight vehicles propulsion is not new. The first example was the 1976 SOLARIS hydrogen-filled dirigible La France in 1884. The 1978 First manned solar flight SOLAR 1 first solar-powered UAV was the Sunrise in 1974. 1979 SOLAR RISER 1980 GOSSAMER PENGUIN Today, the advantages of electric aircraft 1981 SOLAR CHALLENGER are clearly known: the cost of building and 1983 SOLAIR 1 maintaining electric aircraft is considerably less than petrol fuelled aircraft. Electric motors are 1990 SUNSEEKER both incredibly simple and efficient; an electric 1990 SOLAR EXCEL motor runs at 80-98% efficiency compared to 25- 1994 NASA PATHFINDER 50% efficiency for an internal combustion engine. 1996 SOLAR SOLITUDE 1996 ICARE 2 1998 NASA PATHFINDER PLUS 1998 NASA CENTURION 1998 SOLITAIR 2001 NASA HELIOS 2003 QINETIQ ZEPHYR 2005 SOLONG First 24+ hour UAV flight 2009 SOLAR IMPULSE 1 First 24+ hour manned flight 2010 AIRBUS ZEPHYR 7 2015 SOLAR IMPULSE 2 First circumnavigation of the earth by a piloted fixed-wing 2016 FACEBOOK AQUILA solar aircraft 1980-1993 HALSOL 1995-1998 MIKROSOL, PICOSOL, NANOSOL INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL WHITEPAPER THE LIMITING FACTOR HAS BEEN BATTERY TECHNOLOGY By collecting energy from their environment, solar aircraft can greatly overcome the limitations of battery technology, extending range on average between 2 to 3 times longer than achieved with batteries alone. As solar cell and battery technology both improve, flight duration will increase. Aircraft that collect energy from their environment is the only way to achieve indefinite flight. Praxis created its own test environment to measure the difference in battery life with and without solar input. See graph below. PRAXIS PROOF OF CONCEPT - BATTERY VS SOLAR GROUND TEST 17 15.5 oltage Battery V 14 050 100 150 200 250 300 350 Run Time (minutes) Battery Test Solar Test - Sunny Conditions Solar Test - Cloudy Conditions CHALLENGING THE STATUS QUO Because of the fragility of silicon cells, they have been mostly deemed unsuitable for use on electric aircraft. The current approach to manufacturing has been to redesign the cells using flexible Gallium Arsenide (GaAs) – an expensive solution that only partially addresses the problem. Silicon solar cells of 24% efficiency cost approximately $3/watt. Single junction Gallium Arsenide cells of 26% efficiency cost approximately $100/watt. Multi-junction Gallium Arsenide cells of 32% efficiency cost in the order of US $200 - $300 per watt. The work to produce lighter, flexible GaAs cells is valid and beneficial to the use of solar in electric aircraft but still does not address the problem of integration. What has been holding back the development of solar aircraft and UAVs, beyond experimental stage, has been the failure to integrate the cells into the composite material. The approach to date has been to encapsulate the cells in plastic, which in itself has very little structural integrity, and then glue this to the top surface, which adds weight without any structural benefit. This resulting product is not robust or tough and while this is adequate for experimental aircraft, and to prove the validity of solar for range extension, it is not commercially viable. INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL WHITEPAPER SOLAR CELL COMPOSITES - A SOLUTION The solution to commercially viable solar electric aircraft is not purely in the development of suitable solar technology but in how the solar cells are themselves incorporated into the aircraft structure. Praxis has developed a novel process that encapsulates solar cells as a structural element of the composite material of a wing or fuselage. This process overcomes the problem of fragility in silicon cells, allowing Praxis to curve the cells without breaking them. The Praxis approach is to make the composite itself perfectly optically clear so it serves as the integration material as well as the wing structure. This adds little or no weight because the cells become a structural element of the skin, replacing some of the structure that would be there in a non-solar wing. The result is a perfect aerodynamic surface, no different from a non-solar wing. The Praxis solar wing has all the qualities of a non-solar composite wing - it is a perfect aerodynamic surface, tough, water-proof and scratch resistant, with minimal extra steps in manufacturing. The Praxis manufacturing processes are compatible with silicon and gallium arsenide and have demonstrable results, data, and quality standards. FROM INVENTION TO REALITY The robustness and increased flight duration offered by this integration technique makes it suitable for Defence applications such as intelligence, surveillance and reconnaissance (ISR). The composite can be retrofitted to current Small Unmanned Aerial Systems (SUAS), including Vertical Takeoff and Landing (VTOL) systems. Increased flight duration and robust construction also means farmers will be able to monitor vast tracks of land, monitor crops and livestock or manage soil health. Public safety, fire control, civil disobedience and surveillance all represent applications that would benefit from the flexibility of a longer flight duration. INTEGRATING SOLAR CELLS INTO COMPOSITE MATERIAL WHITEPAPER Longer flight duration would also benefit humanitarian challenges such as environmental and conservation management, deliveries of medical supplies to remote and isolated communities, and disaster relief efforts. These are just a few examples of the future of solar electric aircraft and UAVs. The solar integration process can be used for a range of non-aeronautical applications including: • equipment and cases, autonomous and manned vehicles (ground and sea) and habitat facilities such as communication and accommodation tents; • electric vehicles such as bus roofs and boats (surfaces and solid sails); • building surfaces. CONCLUSION The Praxis integration process results in a product that is robust, light and aerodynamic in surface for the toughest defence and commercial applications. Other integration techniques to date, while suitable for experimental aircraft, have not proven to be adequate for the rigours of real world applications. The Praxis approach of combining the cells within the structure of the composite is best practice in solar cell integration for electric aircraft and UAVs. The process is also cost effective as the integration process adds little manufacturing complexity to the process. ABOUT PRAXIS AERONAUTICS Praxis Aeronautics was formed in 2016 to manufacture encapsulated solar cells for electric planes and UAVs by using its novel integration process to extend flying time, reduce costs and extend the range of applications across industry. The Praxis team comprises expertise in composite manufacturing, aeronautical and structural engineering, electronic and software engineering, maths and physics. The Australian company is based in Adelaide, South Australia, and provides its solar integration services and products to customers worldwide. Contact Praxis at [email protected]. www.praxisaeronautics.com.au Copyright © 2018 Praxis Aeronautics Pty Ltd. All rights reserved. .
Recommended publications
  • 25Th Space Photovoltaic Research and Technology (SPRAT XXV) Conference
    National Aeronautics and Space Administration An Overview of The Photovoltaic and Electrochemical Systems Branch at the NASA Glenn Research Center Eric Clark/NASA GRC 25th Space Photovoltaic Research and Technology (SPRAT XXV) Conference Ohio Aerospace Institute Cleveland, Ohio September 19, 2018 www.nasa.gov 1 National Aeronautics and Space Administration Outline • Introduction/History • Current Projects – Photovoltaics – Batteries – Fuel Cells • Future Technology Needs • Conclusions www.nasa.gov 2 National Aeronautics and Space Administration Introduction • The Photovoltaic and Electrochemical Systems Branch (LEX) at the NASA Glenn Research Center (GRC) supports a wide variety of space and aeronautics missions, through research, development, evaluation, and oversight. –Solar cells, thermal energy conversion, advanced array components, and novel array concepts –Low TRL R&D to component evaluation & flight experiments –Supports NASA missions through PV expertise and facilities –Management of SBIR/STTR Topics, Subtopics, and individual efforts. • LEX works closely with other NASA organizations, academic institutions, commercial partners, and other Government entities. www.nasa.gov 3 National Aeronautics and Space Administration Examples of LEX activities Advanced Solar Arrays Solar Cells Array Blanket and Component Technology Solar Cell Measurements & Calibration Solar Array Space Environmental Effects www.nasa.gov 4 National Aeronautics and Space Administration History • 1991The Photovoltaic Branch – Multijunction Cell development, Advanced
    [Show full text]
  • Design, Development, and Initial Testing of a Computationally-Intensive, Long-Endurance Solar-Powered Unmanned Aircraft
    Design, Development, and Initial Testing of a Computationally-Intensive, Long-Endurance Solar-Powered Unmanned Aircraft Or D. Dantsker,∗ Mirco Theile,† and Marco Caccamo‡ Renato Mancuso§ University of Illinois at Urbana–Champaign, Urbana, IL 61801 Boston University, Boston, MA 02215 In recent years, we have seen an uptrend in the popularity of UAVs driven by the desire to apply these aircraft to areas such as precision farming, infrastructure and environment monitoring, surveillance, surveying and mapping, search and rescue missions, weather forecasting, and more. The traditional approach for small size UAVs is to capture data on the aircraft, stream it to the ground through a high power data-link, process it remotely (potentially off-line), perform analysis, and then relay commands back to the aircraft as needed. All the mentioned application scenarios would benefit by carrying a high performance embedded computer system to minimize the need for data transmission. A major technical hurdle to overcome is that of drastically reducing the overall power consumption of these UAVs so that they can be powered by solar arrays. This paper describes the work done to date developing the 4.0 m (157 in) wingspan, UIUC Solar Flyer, which will be a long-endurance solar-powered unmanned aircraft capable of performing computationally-intensive on-board data processing. A mixture of aircraft requirements, trade studies, development work, and initial testing will be presented. Nomenclature CG = center of gravity DOF = degree of freedom ESC = electronic speed controller GPS = global navigation satellite system IMU = inertial measurement unit IR = infrared L/D = lift-to-drag ratio PW M = pulse width modulation RC = radio control AR = aspect ratio b = wingspan c = wing mean chord g = gravitational acceleration L = aircraft length m = aircraft mass P = power p, q, r = roll, pitch and yaw rates S = wing area W = weight v = velocity ∗Graduate Research Fellow, Department of Aerospace Engineering, AIAA Student Member.
    [Show full text]
  • Self Powered Electric Airplanes
    Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 2 (2013), pp. 45-50 © Research India Publications http://www.ripublication.com/aasa.htm Self Powered Electric Airplanes Adesh Ramdas Nakashe 1and C. Lokesh2 1,2Department of Aeronautical Engineering Rajalakshmi Engineering College Chennai-602105, Tamil Nadu, India. Abstract The field of aeronautical engineering began to foresee its advancements in the future, the moment it evolved. Various new technologies and techniques were discovered and implemented almost in all branches of aviation industry. One branch where the researchers are continuously working for further more development is propulsion. Many new ideas are continuously being proposed. This paper deals with the use of renewable energy as the source of power for the aircraft. It gathers or creates the energy to move ON ITS OWN, it uses NO fuel. It is electric, having motors powered by electricity for propulsion. We are going to apply the same principle of electrical airplane and this can be operated as self powered electrical airplane. Here, starting power is provided to the engine and when engine gets maximum torque it starts generating current as per wind mill principle. As it produces electricity that will be used as the input for engine, so there is no need of any external electrical supply further. Efficiency of power produced can be increase to 100% by using electromagnetic generators. So the aircraft will be self driven and electrically powered. Keywords: Renewable energy, Self-powered, Electromagnetic generators. 1. Introduction This paper deals with the conceptual design of an electrically powered commercial aircraft that can carry 30 to 40 passengers.
    [Show full text]
  • Electrical Generation for More-Electric Aircraft Using Solid Oxide Fuel Cells
    PNNL-XXXXX Prepared for the U.S. Department of Energy under Contract DE-AC05-76RL01830 Electrical Generation for More-Electric Aircraft using Solid Oxide Fuel Cells GA Whyatt LA Chick April 2012 PNNL-XXXXX Electrical Generation for More- Electric Aircraft using Solid Oxide Fuel Cells GA Whyatt LA Chick April 2012 Prepared for the U.S. Department of Energy under Contract DE-AC05-76RL01830 Pacific Northwest National Laboratory Richland, Washington 99352 Summary This report examines the potential for Solid-Oxide Fuel Cells (SOFC) to provide electrical generation on-board commercial aircraft. Unlike a turbine-based auxiliary power unit (APU) a solid oxide fuel cell power unit (SOFCPU) would be more efficient than using the main engine generators to generate electricity and would operate continuously during flight. The focus of this study is on more-electric aircraft which minimize bleed air extraction from the engines and instead use electrical power obtained from generators driven by the main engines to satisfy all major loads. The increased electrical generation increases the potential fuel savings obtainable through more efficient electrical generation using a SOFCPU. However, the weight added to the aircraft by the SOFCPU impacts the main engine fuel consumption which reduces the potential fuel savings. To investigate these relationships the Boeing 787-8 was used as a case study. The potential performance of the SOFCPU was determined by coupling flowsheet modeling using ChemCAD software with a stack performance algorithm. For a given stack operating condition (cell voltage, anode utilization, stack pressure, target cell exit temperature), ChemCAD software was used to determine the cathode air rate to provide stack thermal balance, the heat exchanger duties, the gross power output for a given fuel rate, the parasitic power for the anode recycle blower and net power obtained from (or required by) the compressor/expander.
    [Show full text]
  • Electric Propulsion
    UNIVERSITY LEAD INITIATIVE Dr. Mike Benzakein Assistant Vice President, Aerospace and Aviation UNIVERSITY LED INITIATIVE Electric Propulsion – Challenges and Opportunities The challenges and the goals: • The team • System integration vehicle sizing • Batteries energy storage • Electric machines • Thermal management • The demonstration WHY ARE WE DOING THIS? • World population is growing 10 Billion by 2100 • Commercial airplanes will double in the next 20 years, causing increased CO2 emissions that affect health across the globe. • Goal is to have a carbon neutral environment by 2050. • National Academy of Engineering has established that a reduction of a 20% in fuel burn and CO2 could be attained with electric propulsion. Great to help the environment, but challenges remain THE TEAM System Integration Vehicle Sizing Initial Sizing Thermal Management Final Concept 1. Requirements Battery Definition Definition 2. Electric Power 1. Iterate with battery testing 1. Update Scaling Usage 2. Trade battery life against laws, and maps 3. density 2. Energy storage 4. 3. 3. July 2017 – July 2018 4. 4. Prelim. Sizing Resized vehicle Vehicle Design Frozen Vehicle Update July 2018 June 2019 June 2020 June 2021 Iterative cooperative process Vehicle Update between Universities June 2022 ULI Concept Benefits Assessment Baseline Aircraft Next Generation Distributed Hybrid (CRJ 900) Aircraft Turbo Electric 8% Distributed Propulsion 9% and typical payload and typical Use of Hybrid Propulsion 6% Fuel Burn Reduction at 600 nmi Reduction Burn Fuel 15% improvement
    [Show full text]
  • Integration of Photovoltaic Cells Into Composite Wing Skins
    INTEGRATION OF PHOTOVOLTAIC CELLS INTO COMPOSITE WING SKINS By JAMES LEONARD Bachelor of Science in Aerospace and Mechanical Engineering Oklahoma State University Stillwater, Oklahoma 2010 Submitted to the Faculty of the Graduate College of the Oklahoma State University in partial fulfillment of the requirements for the Degree of MASTER OF SCIENCE December, 2014 INTEGRATION OF PHOTOVOLTAIC CELLS INTO COMPOSITE WING SKINS Thesis Approved: Dr. Jamey Jacob Thesis Adviser Dr. Andy Arena Dr. Joe Conner ii Name: JAMES LEONARD Date of Degree: DECEMBER, 2014 Title of Study: INTEGRATION OF PHOTOVOLTAIC CELLS INTO COMPOSITE WING SKINS Major Field: MECHANICAL AND AEROSPACE ENGINEERING ABSTRACT: The integration of thin film solar cells into composite wing skins is explored by first testing and evaluating the integration of single solar cells into small composite samples with no encapsulating material, fiberglass encapsulating material and polyurethane film encapsulating material for the impacts that these processes and materials have on solar cell performance, aircraft performance and solar cell durability. Moving on from single cell samples, three encapsulation methods were chosen to be used in the construction of two wings utilizing arrays of multiple solar cells with each encapsulation method being utilized on 3 of the four wing skins comprising the 2 complete wings. The fourth wing skin was integrated with a functioning removable solar panel manufactured to the contours of the wing. Performance and weight data gathered from the development and fabrication of single cell and wing-skin specimens was used to develop a basic model of endurance for each encapsulation material evaluated in order to compare the effects of encapsulation materials and processes on the primary parameter that the integration of the photovoltaic cells into the wing skins is intended to improve.
    [Show full text]
  • Laser Power Beaming Fact Sheet I
    LASER POWER BEAMING FACT SHEET I. What is laser power beaming? Laser power beaming is the wireless transfer of energy (heat or electricity) from one location to another, using laser light. The basic concept is the same as solar power, where the sun shines on a photovoltaic cell that converts the sunlight to energy. Here, a photovoltaic cell converts the laser light to energy. The key differences are that laser light is much more intense than sunlight, it can be aimed at any desired location, and it can deliver power 24 hours per day. Power can be transmitted through air or space, or through optical fibers, as communications signals are sent today, and it can be sent potentially as far as the Moon. The benefits of wireless power beaming include The narrow beam allows greater energy concentration at long distances; The compact size of the receiver allows easy integration into small devices; Power is transmitted with zero radio frequency interference (e.g. to wi-fi/cellular systems); Electrical power can be utilized for applications where it was previously uneconomical or impractical to run wires, including aerial refueling of UAVs and other aircraft; Power beaming can use any existing power source to power the laser; and Power can be delivered through free space or over fiber optic cable. II. What are the uses for laser power beaming? Although still largely in the R&D stages, wireless power has many potential uses in the real world. These include powering air, ground, and underwater vehicles, replacing electric power wiring and transmission lines in difficult places, and even launching rockets into orbit.
    [Show full text]
  • The First Practical Zero Emission Aviation Powertrain
    The First Practical Zero Emission Aviation Powertrain Q4 2020 $1.5T Aviation Market is Flying into Sustainability Crisis Megatons 25% 5-10% Of total human Climate Impact 50% Today Useful life of a commercial aircraft In 2050 No real, truly scalable solutions today 2 Hydrogen is a Key Enabler of Future Aviation Options Primary issues (Blockers) Secondary issues 40x lower energy density compared to jet fuel; 5x+ higher kwh/kg High OPEX due to cycling costs (including recycling) - need Battery electric required to start being relevant in aviation at least 5x cycle life improvement Marginal / zero benefit on any but the shortest routes (where Turbine - electric None turbine is primarily a reserve power source) Not scalable to any meaningful % of aviation; Plants are 500x High costs; competition with food; environmental damage; Biofuel worse than solar+electrolysis at utilization of land water use problems; NOX / particulates Fundamentally higher cost of fuel than direct H2 approaches (green H2 is the required feedstock for synfuel); Synthetic fuel None Fundamentally lower efficiency than H2 electric; NOX / particulates Fundamentally lower efficiency than H2 electric = more fuel H2 turbine None required; volume of fuel storage system; NOX Hydrogen - Power density of fuel cell systems; volume and weight None electric of fuel storage system Hydrogen-electric powertrains have advantage over all other alternative propulsion types, with no blockers and fixable secondary issues 3 Why Hydrogen?* 4x+ Addtl 3x 50% 30% Range even Range by going Lower
    [Show full text]
  • July-16.Indd
    SWATI SAXENA RTICLE A EATURE F There have been many efforts to build and fl y a solar-powered aircraft that does not guzzle conventional fuels. Although some headway has been made, there is still a long way to go. batteries or fuel cells are used for this The Solar-Powered Aircraft purpose. They can be re-charged during Developments’ “Solar One” is a British the day. mid-wing, experimental, manned solar- Solar Plane History powered aircraft designed by David Solar plane history dates back to the Williams was the third solar-powered 1970s when the 27 lb (12 kg) unmanned aircraft to fl y. A motor-glider type AstroFlight Sunrise, the result of an USA aircraft originally built as a pedal- HE world’s fi rst offi cial fl ight in a ARPA (Advanced Research Projects powered airplane to attempt the Channel solar-powered, man-carrying aircraft T Agency) contract, made the world’s fi rst crossing, the airplane proved too heavy took place on 29 April 1979. Technologists solar-powered fl ight from Bicycle Lake, to be successfully powered by human have been trying since long to look for a dry lake bed on the Fort Irwin Military power and was then converted to greener ways of fl ying aircraft. And what Reservation, on 4 November 1974. solar power, using an electric motor can be greener than harnessing the energy The improved Sunrise II fl ew on driven by batteries that were charged of the sun to power aircraft. 27 September 1975 at Nellis Air Force before fl ight by a solar cell array on the A solar powered plane converts Base.
    [Show full text]
  • The Performance Economy: 2Nd Edition
    9780230_584662_01_prexxiv.pdf 1/12/10 2:41 PM Page i The Performance Economy 9780230_584662_01_prexxiv.pdf 1/12/10 2:41 PM Page ii Also by Walter Stahel COMMON UTILIZATION INSTEAD OF SINGULAR CONSUMPTION – A NEW RELATIONSHIP WITH GOODS Stahel, Walter R. and Gomringer, Eugen (editors) ECONOMIC STRATEGY OF DURABILITY Börlin, Max and Stahel, Walter R. (authors) HANDBUCH VON BEISPIELEN EINER HÖHEREN RESSOURCEN-EFFIZIENZ Stahel, Walter R. (author) JOBS FOR TOMORROW, THE POTENTIAL FOR SUBSTITUTING MANPOWER FOR ENERGY Stahel, Walter R. and Reday, Geneviève (authors) LANGLEBIGKEIT UND MATERIALRECYCLING Stahel, Walter R. (author) RESSOURCENPRODUKTIVITÄT DURCH NUTZUNGSINTENSIVIERUNG UND LEBENSDAUERVERLÄNGERUNG Stahel, Walter R. (author) THE LIMITS TO CERTAINTY, FACING RISKS IN THE NEW SERVICE ECONOMY Giarini, Orio and Stahel, Walter R. (authors) Translated into French, Italian, Rumanian, Japanese and German 9780230_584662_01_prexxiv.pdf 1/12/10 2:41 PM Page iii The Performance Economy 2nd Edition Walter R. Stahel 9780230_584662_01_prexxiv.pdf 1/12/10 2:41 PM Page iv © Walter R. Stahel 2006, 2010 All rights reserved. No reproduction, copy or transmission of this publication may be made without written permission. No portion of this publication may be reproduced, copied or transmitted save with written permission or in accordance with the provisions of the Copyright, Designs and Patents Act 1988, or under the terms of any licence permitting limited copying issued by the Copyright Licensing Agency, Saffron House, 6–10 Kirby Street, London EC1N 8TS. Any person who does any unauthorized act in relation to this publication may be liable to criminal prosecution and civil claims for damages. The author has asserted his right to be identified as the author of this work in accordance with the Copyright, Designs and Patents Act 1988.
    [Show full text]
  • Electric Power Systems and Components for Electric Aircraft
    University of Kentucky UKnowledge Theses and Dissertations--Electrical and Computer Engineering Electrical and Computer Engineering 2021 Electric Power Systems and Components for Electric Aircraft Damien Lawhorn University of Kentucky, [email protected] Author ORCID Identifier: https://orcid.org/0000-0002-3642-3983 Digital Object Identifier: https://doi.org/10.13023/etd.2021.134 Right click to open a feedback form in a new tab to let us know how this document benefits ou.y Recommended Citation Lawhorn, Damien, "Electric Power Systems and Components for Electric Aircraft" (2021). Theses and Dissertations--Electrical and Computer Engineering. 163. https://uknowledge.uky.edu/ece_etds/163 This Doctoral Dissertation is brought to you for free and open access by the Electrical and Computer Engineering at UKnowledge. It has been accepted for inclusion in Theses and Dissertations--Electrical and Computer Engineering by an authorized administrator of UKnowledge. For more information, please contact [email protected]. STUDENT AGREEMENT: I represent that my thesis or dissertation and abstract are my original work. Proper attribution has been given to all outside sources. I understand that I am solely responsible for obtaining any needed copyright permissions. I have obtained needed written permission statement(s) from the owner(s) of each third-party copyrighted matter to be included in my work, allowing electronic distribution (if such use is not permitted by the fair use doctrine) which will be submitted to UKnowledge as Additional File. I hereby grant to The University of Kentucky and its agents the irrevocable, non-exclusive, and royalty-free license to archive and make accessible my work in whole or in part in all forms of media, now or hereafter known.
    [Show full text]
  • Hybrid Propulsion System of a Long Endurance Electric UAV
    Hybrid Propulsion System of a Long Endurance Electric UAV Tiago Miguel Moreira Ferreira Thesis to obtain the Master of Science Degree in Mechanical Engineering Supervisor(s): Prof. André Calado Marta Prof. Virginia Isabel Monteiro Nabais Infante Examination Committee Chairperson: Prof. Luís Manuel Varejão Oliveira Faria Supervisor: Prof. André Calado Marta Member of the Committee: Prof. António Manuel Relógio Ribeiro November 2014 ii Acknowledgments I would like to thank my parents, Gracinda Ferreira and Mario´ Ferreira, for supporting me along my academic path. I would also like to thank Daniela Carvalho for always being there to help me along the way. Thanks to the professors, Dr. Andre´ Marta and Dr. Virginia Infante, that guided me and helped me during the making of this thesis. And also thanks Diogo Rechena for the help in spell checking and proof reading. iii iv Resumo A procura de fontes energeticas´ alternativas tem crescido nos ultimos´ anos. A mudanc¸a para energia electrica´ ja´ pode ser vista na industria´ automovel,´ e a industria aeronautica´ esta´ lentamente a seguir os mesmo caminho. O uso de paineis´ solares e´ uma boa fonte energetica´ alternativa, sendo que e´ limpa e abundantemente dispon´ıvel. Esta tese foca-se num sistema que combina a gerac¸ao˜ electrica´ solar com uma propulsao˜ electrica´ numa aeronave nao˜ tripulada com 4.5 m de envergadura para missoes˜ civis de vigilanciaˆ durante longos per´ıodos de tempo. Um h´ıbrido solar-bateria e´ uma boa soluc¸ao˜ para ve´ıculos aereos´ de longa durac¸ao,˜ devido a` grande area´ dispon´ıvel nas asas para montar um painel solar capaz de fornecer energia suficiente para manter o aviao˜ no ar.
    [Show full text]