Charging Forward New Evtol Concepts Advance “Look! up in the Sky! It’S a Car — It’S a Plane — No, It’S My Uberair!”
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Jay Carter, Founder &
CARTER AVIATION TECHNOLOGIES An Aerospace Research & Development Company Jay Carter, Founder & CEO CAFE Electric Aircraft Symposium www.CarterCopters.com July 23rd, 2017 Wichita©2015 CARTER AVIATIONFalls, TECHNOLOGIES,Texas LLC SR/C is a trademark of Carter Aviation Technologies, LLC1 A History of Innovation Built first gyros while still in college with father’s guidance Led to job with Bell Research & Development Steam car built by Jay and his father First car to meet original 1977 emission standards Could make a cold startup & then drive away in less than 30 seconds Founded Carter Wind Energy in 1976 Installed wind turbines from Hawaii to United Kingdom to 300 miles north of the Arctic Circle One of only two U.S. manufacturers to survive the mid ‘80s industry decline ©2015 CARTER AVIATION TECHNOLOGIES, LLC 2 SR/C™ Technology Progression 2013-2014 DARPA TERN Won contract over 5 majors 2009 License Agreement with AAI, Multiple Military Concepts 2011 2017 2nd Gen First Flight Find a Manufacturing Later Demonstrated Partner and Begin 2005 L/D of 12+ Commercial Development 1998 1 st Gen 1st Gen L/D of 7.0 First flight 1994 - 1997 Analysis & Component Testing 22 years, 22 patents + 5 pending 1994 Company 11 key technical challenges overcome founded Proven technology with real flight test ©2015 CARTER AVIATION TECHNOLOGIES, LLC 3 SR/C™ Technology Progression Quiet Jump Takeoff & Flyover at 600 ft agl Video also available on YouTube: https://www.youtube.com/watch?v=_VxOC7xtfRM ©2015 CARTER AVIATION TECHNOLOGIES, LLC 4 SR/C vs. Fixed Wing • SR/C rotor very low drag by being slowed Profile HP vs. -
THE ROADMAP to Scalable Urban Air Mobility
THE ROADMAP to scalable urban air mobility White paper 2.0 We bring urban air mobility to life. FOREWORD BY THE CEO MAKING HISTORY When I joined Volocopter in 2015, an amazing team of innovators had already made aviation history. With a dream, a yoga ball,1 and a new configuration of distributed electric vertical takeoff and landing (eVTOL) technology, Volocopter pioneered the way for electric passenger flights as early as 2011. Since then, Volocopter has relentlessly pursued its dream and continued to make great strides. I have witnessed the idea of electric flight grow into a fully-fledged initiative to bring seamless urban air mobility to cities. It’s true, we developed a revolutionary aircraft. But in fact, we launched the creation of an entire industry. The yoga ball evolved into the first certified multicopter, and Volocopter evolved to become the world’s first and only electric multicopter company with Design Organisation Approval (DOA) from the European Union Aviation Safety Agency (EASA). Five years, six very public flights, and two city commitments later, Volocopter continues to lead the pack as the “Pioneer of Urban Air Mobility” both in certification and in robust partnerships. We have set the stage for the next transformative industry. BRINGING URBAN AIR MOBILITY TO LIFE As the category-defining company, we are investing in multidimensional mobility. And as a team, we are engineering it. Volocopter has combined cutting-edge eVTOL technology with a holistic partnership approach as we build the world’s first fully electric, scalable UAM business for affordable air taxi services in cities. -
Effectiveness of the Compound Helicopter Configuration in Rotorcraft Performance Increase
transactions on aerospace research 4(261) 2020, pp.81-106 DOI: 10.2478/tar-2020-0023 eISSN 2545-2835 effectiveness of the compound helicopter configuration in rotorcraft performance increase Jarosław stanisławski Retired doctor of technical sciences [email protected] • ORCID: 0000-0003-1629-4632 abstract The article presents the results of calculations applied to compare flight envelopes of varying helicopter configurations. Performance of conventional helicopter with the main and tail rotors, in the case of compound helicopter, can be improved by applying wings and pusher propellers which generate an additional lift and horizontal thrust. The simplified model of a helicopter structure, consisting of a stiff fuselage and the main rotor treated as a stiff disk, is applied for evaluation of the rotorcraft performance and the required range of control system deflections. The more detailed model of deformable main rotor blades, applying the Galerkin method, is used to calculate rotor loads and blade deformations in defined flight states. The calculations of simulated flight states are performed considering data of a hypothetical medium class helicopter with the take-off mass of 6,000kg. In the case of both of the helicopter configurations, the articulated main rotor hub is taken under consideration. According to the Galerkin method, the elastic blade model allows to compute blade deformations as a combination of the blade bending and torsional eigen modes. Introduction of additional wing and pusher propellers allows to increase the range of operational speed over 300 km/h. Results of the simulation are presented as time- runs of rotor loads and blade deformations and in a form of disk distribution plots of rotor parameters. -
General Aviation Aircraft Propulsion: Power and Energy Requirements
UNCLASSIFIED General Aviation Aircraft Propulsion: Power and Energy Requirements • Tim Watkins • BEng MRAeS MSFTE • Instructor and Flight Test Engineer • QinetiQ – Empire Test Pilots’ School • Boscombe Down QINETIQ/EMEA/EO/CP191341 RAeS Light Aircraft Design Conference | 18 Nov 2019 | © QinetiQ UNCLASSIFIED UNCLASSIFIED Contents • Benefits of electrifying GA aircraft propulsion • A review of the underlying physics • GA Aircraft power requirements • A brief look at electrifying different GA aircraft types • Relationship between battery specific energy and range • Conclusions 2 RAeS Light Aircraft Design Conference | 18 Nov 2019 | © QinetiQ UNCLASSIFIED UNCLASSIFIED Benefits of electrifying GA aircraft propulsion • Environmental: – Greatly reduced aircraft emissions at the point of use – Reduced use of fossil fuels – Reduced noise • Cost: – Electric aircraft are forecast to be much cheaper to operate – Even with increased acquisition cost (due to batteries), whole-life cost will be reduced dramatically – Large reduction in light aircraft operating costs (e.g. for pilot training) – Potential to re-invigorate the GA sector • Opportunities: – Makes highly distributed propulsion possible – Makes hybrid propulsion possible – Key to new designs for emerging urban air mobility and eVTOL sectors 3 RAeS Light Aircraft Design Conference | 18 Nov 2019 | © QinetiQ UNCLASSIFIED UNCLASSIFIED Energy conversion efficiency Brushless electric motor and controller: • Conversion efficiency ~ 95% for motor, ~ 90% for controller • Variable pitch propeller efficiency -
Open Walsh Thesis.Pdf
The Pennsylvania State University The Graduate School College of Engineering A PRELIMINARY ACOUSTIC INVESTIGATION OF A COAXIAL HELICOPTER IN HIGH-SPEED FLIGHT A Thesis in Aerospace Engineering by Gregory Walsh c 2016 Gregory Walsh Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science August 2016 The thesis of Gregory Walsh was reviewed and approved∗ by the following: Kenneth S. Brentner Professor of Aerospace Engineering Thesis Advisor Jacob W. Langelaan Associate Professor of Aerospace Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering ∗Signatures are on file in the Graduate School. Abstract The desire for a vertical takeoff and landing (VTOL) aircraft capable of high forward flight speeds is very strong. Compound lift-offset coaxial helicopter designs have been proposed and have demonstrated the ability to fulfill this desire. However, with high forward speeds, noise is an important concern that has yet to be thoroughly addressed with this rotorcraft configuration. This work utilizes a coupling between the Rotorcraft Comprehensive Analysis System (RCAS) and PSU-WOPWOP, to computationally explore the acoustics of a lift-offset coaxial rotor sys- tem. Specifically, unique characteristics of lift-offset coaxial rotor system noise are identified, and design features and trim settings specific to a compound lift-offset coaxial helicopter are considered for noise reduction. At some observer locations, there is constructive interference of the coaxial acoustic pressure pulses, such that the two signals add completely. The locations of these constructive interferences can be altered by modifying the upper-lower rotor blade phasing, providing an overall acoustic benefit. -
Over Thirty Years After the Wright Brothers
ver thirty years after the Wright Brothers absolutely right in terms of a so-called “pure” helicop- attained powered, heavier-than-air, fixed-wing ter. However, the quest for speed in rotary-wing flight Oflight in the United States, Germany astounded drove designers to consider another option: the com- the world in 1936 with demonstrations of the vertical pound helicopter. flight capabilities of the side-by-side rotor Focke Fw 61, The definition of a “compound helicopter” is open to which eclipsed all previous attempts at controlled verti- debate (see sidebar). Although many contend that aug- cal flight. However, even its overall performance was mented forward propulsion is all that is necessary to modest, particularly with regards to forward speed. Even place a helicopter in the “compound” category, others after Igor Sikorsky perfected the now-classic configura- insist that it need only possess some form of augment- tion of a large single main rotor and a smaller anti- ed lift, or that it must have both. Focusing on what torque tail rotor a few years later, speed was still limited could be called “propulsive compounds,” the following in comparison to that of the helicopter’s fixed-wing pages provide a broad overview of the different helicop- brethren. Although Sikorsky’s basic design withstood ters that have been flown over the years with some sort the test of time and became the dominant helicopter of auxiliary propulsion unit: one or more propellers or configuration worldwide (approximately 95% today), jet engines. This survey also gives a brief look at the all helicopters currently in service suffer from one pri- ways in which different manufacturers have chosen to mary limitation: the inability to achieve forward speeds approach the problem of increased forward speed while much greater than 200 kt (230 mph). -
Urban Air Mobility | USD 90 Billion of Potential: How to Capture a Share of the Passenger Drone Market
Urban Air Mobility | USD 90 billion of potential: How to capture a share of the passenger drone market The Roland Berger Center for Smart Mobility MANAGEMENT SUMMARY Urban Air Mobility / USD 90 billion of potential: How to capture a share of the passenger drone market Our updated market analysis and Global Urban Air Mobility Radar show that the passenger Urban Air Mobility (UAM) market is set to soar. The number of UAM projects continues to rise, barriers to progress – such as regulation and public acceptance – are increasingly being overcome and the coronavirus crisis shows no sign of causing serious delays. By 2050, we estimate that the passenger UAM industry will generate revenues of almost USD 90 billion a year, with 160,000 commercial passenger drones plying the skies. This potential is driving the emergence of an integrated ecosystem in the nascent UAM industry, consisting of five major building blocks: eVTOL vehicles; maintenance, repair and overhaul services; flight operations; physical infrastructure; and digital infrastructure. First collaborations are forming across this ecosystem. Yet among the many disparate market players, no dominant passenger UAM player or business model has emerged yet. Instead, companies are tending towards four business model archetypes: system providers, who are involved across the value chain, and service providers, hardware providers and ticket brokers, who focus on distinct areas. Most players are currently positioning themselves as system providers to gain as much industry knowledge as possible, and we believe this trend will continue. A shake out and consolidation are likely in the coming years. Despite the lack of a proven business model, investors are strongly backing the passenger UAM industry. -
(12) United States Patent (10) Patent No.: US 8,991,744 B1 Khan (45) Date of Patent: Mar
USOO899.174.4B1 (12) United States Patent (10) Patent No.: US 8,991,744 B1 Khan (45) Date of Patent: Mar. 31, 2015 (54) ROTOR-MAST-TILTINGAPPARATUS AND 4,099,671 A 7, 1978 Leibach METHOD FOR OPTIMIZED CROSSING OF 35856 A : 3. Wi NATURAL FREQUENCIES 5,850,6154. W-1 A 12/1998 OSderSO ea. 6,099.254. A * 8/2000 Blaas et al. ................... 416,114 (75) Inventor: Jehan Zeb Khan, Savoy, IL (US) 6,231,005 B1* 5/2001 Costes ....................... 244f1725 6,280,141 B1 8/2001 Rampal et al. (73) Assignee: Groen Brothers Aviation, Inc., Salt 6,352,220 B1 3/2002 Banks et al. Lake City, UT (US) 6,885,917 B2 4/2005 Osder et al. s 7,137,591 B2 11/2006 Carter et al. (*) Notice: Subject to any disclaimer, the term of this 16. R 1239 sign patent is extended or adjusted under 35 2004/0232280 A1* 11/2004 Carter et al. ............... 244f1725 U.S.C. 154(b) by 494 days. OTHER PUBLICATIONS (21) Appl. No.: 13/373,412 John Ballard etal. An Investigation of a Stoppable Helicopter Rotor (22) Filed: Nov. 14, 2011 with Circulation Control NASA, Aug. 1980. Related U.S. Application Data (Continued) (60) Provisional application No. 61/575,196, filed on Aug. hR". application No. 61/575,204, Primary Examiner — Joseph W. Sanderson • Y-s (74) Attorney, Agent, or Firm — Pate Baird, PLLC (51) Int. Cl. B64C 27/52 (2006.01) B64C 27/02 (2006.01) (57) ABSTRACT ;Sp 1% 3:08: A method and apparatus for optimized crossing of natural (52) U.S. -
Apis Contest Taurus(Electro)
Welcome NASA PAV Apis contest The CAFÉ Foundation’s With the addition of Inaugural NASA PAV Apis/Bee to the product Centennial Challenge line, Pipistrel is now concluded on August 11 in the most complex small Santa Rosa, California, and aircraft producer IN THE brought forth remarkable WORLD, the ONLY AIRCRAFT performances by several PRODUCER offering both Personal Air Vehicles (PAVs). single-seat and two- This great event was made seater side-by-side self- possible by support from launching gliders, two-seat NASA and Boeing Phantom motorgliders, UL two-seat INDEX Works. Winning teams go-the-distance aircraft, Electric Powered shared cash prizes from trikes and propellers. 1 Welcome Apis NASA totaling $250,000. We are excited about Taurus (Electro) Prizes were awarded for welcoming all existing and Electric Powered Taurus Shortest Runway, Lowest new Apis/Bee family owners Nasa PAV Contest Noise, Highest Top Speed, and we are confident to In 1995, Pipistrel d.o.o. Ajdovščina glide ratio of Best Handling Qualities, provide them with the best Our Dealers around the World were the first in the World to present at least 1:40; and Most Efficient, with possible service! a two-seat ultralight aircraft with a make gliding the grand Vantage Prize of From its beginnings, Apis/ 2 Project Hydrogenus wing-span of 15 meters, aimed also at cheap; provide $100,000 going to the best Bee was developed as a glider pilots. The aircraft was the Sinus, a fully equipped aircraft, including a Pipistrel Factory: combination of performance sister-ship to the Pipistrel’s still going strong in production. -
The Power for Flight: NASA's Contributions To
The Power Power The forFlight NASA’s Contributions to Aircraft Propulsion for for Flight Jeremy R. Kinney ThePower for NASA’s Contributions to Aircraft Propulsion Flight Jeremy R. Kinney Library of Congress Cataloging-in-Publication Data Names: Kinney, Jeremy R., author. Title: The power for flight : NASA’s contributions to aircraft propulsion / Jeremy R. Kinney. Description: Washington, DC : National Aeronautics and Space Administration, [2017] | Includes bibliographical references and index. Identifiers: LCCN 2017027182 (print) | LCCN 2017028761 (ebook) | ISBN 9781626830387 (Epub) | ISBN 9781626830370 (hardcover) ) | ISBN 9781626830394 (softcover) Subjects: LCSH: United States. National Aeronautics and Space Administration– Research–History. | Airplanes–Jet propulsion–Research–United States– History. | Airplanes–Motors–Research–United States–History. Classification: LCC TL521.312 (ebook) | LCC TL521.312 .K47 2017 (print) | DDC 629.134/35072073–dc23 LC record available at https://lccn.loc.gov/2017027182 Copyright © 2017 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks National Aeronautics and Space Administration Washington, DC Table of Contents Dedication v Acknowledgments vi Foreword vii Chapter 1: The NACA and Aircraft Propulsion, 1915–1958.................................1 Chapter 2: NASA Gets to Work, 1958–1975 ..................................................... 49 Chapter 3: The Shift Toward Commercial Aviation, 1966–1975 ...................... 73 Chapter 4: The Quest for Propulsive Efficiency, 1976–1989 ......................... 103 Chapter 5: Propulsion Control Enters the Computer Era, 1976–1998 ........... 139 Chapter 6: Transiting to a New Century, 1990–2008 .................................... -
DEVELOPMENT TRENDS and PROSPECTS for Evtol
Mitsui & Co. Global Strategic Studies Institute Monthly Report June 2018 DEVELOPMENT TRENDS AND PROSPECTS FOR eVTOL: A NEW MODE OF AIR MOBILITY Hideki Kinjo Industry Innovation Dept., Technology & Innovation Studies Div. Mitsui & Co. Global Strategic Studies Institute SUMMARY Development activities are gaining momentum for “electric vertical takeoff and landing aircraft” (eVTOL), which is designed to transport several passengers over short distances by air. Technology advancements, such as batteries and motors in the automotive industry and autopilot navigation in the drone industry are the backgrounds. Many startups, as well as major aircraft manufacturers, are now entering into eVTOL aircraft development. Among the services envisioned, the US company Uber aims to launch an air taxi service in the first half of the 2020s. Challenges with respect to aircraft development have mainly to do with batteries, while on the services front, ensuring safety and securing profitability are the issues. As for eVTOL initial spread in the market, it may possibly be for first aid and other emergency response services and in emerging economies where flight regulations are less stringent. The development of electric vertical takeoff and landing aircraft (eVTOL) is gaining momentum. Three- dimensional mobility in the sky is expected to provide passengers with much shorter travel times and greater convenience. This report discusses the unique features of eVTOL, trends in aircraft development, moves in the area of services, challenges to make eVTOL travel a reality, and future prospects. eVTOL REPRESENTS A NEW MODE OF MOBILITY MADE POSSIBLE BY TRANSFERRING TECHNOLOGIES FROM OTHER INDUSTRIES The eVTOL can be described as a vehicle that fits somewhere in between a drone and a conventional airplane. -
Performance Analysis of the Slowed-Rotor Compound Helicopter Configuration
Performance Analysis of the Slowed-Rotor Compound Helicopter Configuration Matthew W. Floros Wayne Johnson Raytheon ITSS Army/NASA Rotorcraft Division Moffett Field, California NASA Ames Research Center Moffett Field, California The calculated performance of a slowed-rotor compound aircraft, particularly at high flight speeds, is exam- ined. Correlation of calculated and measured performance is presented for a NASA Langley high advance ratio test and the McDonnell XV-1 demonstrator to establish the capability to model rotors in such flight conditions. The predicted performance of a slowed-rotor vehicle model based on the CarterCopter Technology Demonstra- tor is examined in detail. An isolated rotor model and a model of a rotor and wing are considered. Three tip speeds and a range of collective pitch settings are investigated. A tip Mach number of 0.2 and zero collective pitch are found to be the optimum condition to minimize rotor drag. Performance is examined for both sea level and cruise altitude conditions. Nomenclature Much work has been focused on tilt rotor aircraft; both military and civilian tilt rotors are currently in development. But other configurations may provide comparable benefits to CT thrust coefficient tilt rotors in terms of range and speed. Two such configura- CQ torque coefficient tions are the compound helicopter and the autogyro. These CH longitudinal inplane force coefficient configurations provide STOL or VTOL capability, but are ca- D drag pable of higher speeds than a conventional helicopter because L lift the rotor does not provide the propulsive force or at high MTIP tip Mach number speed, the vehicle lift. The drawback is that redundant lift VT tip speed and/or propulsion add weight and drag which must be com- q dynamic pressure pensated for in some other way.