AHS -- Future of Vertical Flight
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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. -
Future Battlefield Rotorcraft Capability (FBRC) – Anno 2035 and Beyond
November 2018 Future Battle eld Rotorcraft Capability Anno 2035 and Beyond Joint Air Power Competence Centre Cover picture © Airbus © This work is copyrighted. No part may be reproduced by any process without prior written permission. Inquiries should be made to: The Editor, Joint Air Power Competence Centre (JAPCC), [email protected] Disclaimer This document is a product of the Joint Air Power Competence Centre (JAPCC). It does not represent the opinions or policies of the North Atlantic Treaty Organization (NATO) and is designed to provide an independent overview, analysis and food for thought regarding possible ways ahead on this subject. Comments and queries on this document should be directed to the Air Operations Support Branch, JAPCC, von-Seydlitz-Kaserne, Römerstraße 140, D-47546 Kalkar. Please visit our website www.japcc.org for the latest information on JAPCC, or e-mail us at [email protected]. Author Cdr Maurizio Modesto (ITA Navy) Release This paper is releasable to the Public. Portions of the document may be quoted without permission, provided a standard source credit is included. Published and distributed by The Joint Air Power Competence Centre von-Seydlitz-Kaserne Römerstraße 140 47546 Kalkar Germany Telephone: +49 (0) 2824 90 2201 Facsimile: +49 (0) 2824 90 2208 E-Mail: [email protected] Website: www.japcc.org Denotes images digitally manipulated JAPCC |Future BattlefieldRotorcraft Capability and – AnnoBeyond 2035 | November 2018 Executive Director, JAPCC Director, Executive DEUAF General, Lieutenant Klaus Habersetzer port Branchviae-mail [email protected]. AirOperationsSup contact to theJAPCC’s free feel thisdocument.Please to withregard have you may comments welcome any We thisstudy. -
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. -
Abstract Effect of Interactional
ABSTRACT Title of thesis: EFFECT OF INTERACTIONAL AERODYNAMICS ON COMPUTATIONAL AEROACOUSTICS OF SIKORSKY'S NOTIONAL X2 PLATFORM Ian Kevin Bahr Master of Science in Aerospace Engineering, 2020 Thesis directed by: Professor James Baeder A. James Clark School of Engineering Department of Aerospace Engineering An in-house acoustics code, ACUM, was used in conjunction with full vehicle CFD/CSD coupling to create a computational aeroacoustic framework to investigate the effect of aerodynamic interactions on the acoustic prediction of a compound coaxial helicopter. The full vehicle CFD/CSD was accomplished by using a high- fidelity computational fluid dynamics framework, HPCMP CREATETM-AV Helios, combined with an in-house computational structural dynamics solver to simulate the helicopter in steady forward flight. A notional X2TD helicopter consisting of a coaxial rotor, airframe and pusher propeller was used and split into three simulation cases: isolated coaxial and propeller, airframe and full helicopter configuration to investigate each component's affect on the others noise as well as the total noise. The primary impact on the acoustic prediction was the inclusion of the airframe in the CFD simulation as it affected both coaxial rotors as well as the propeller. It was found that the propeller and coaxial rotors had negligible impact on each other. EFFECT OF INTERACTIONAL AERODYNAMICS ON COMPUTATIONAL AEROACOUSTICS OF SIKORSKY'S NOTIONAL X2 PLATFORM by Ian Kevin Bahr Thesis submitted to the Faculty of the Graduate School of the University of Maryland, College Park in partial fulfillment of the requirements for the degree of Master of Science 2020 Advisory Committee: Dr. James Baeder, Chair/Advisor Dr. -
AHS -- Future of Vertical Flight
The Future of Vertical Flight www.tinyurl.com/VFS-Heli-Expo-2020 Mike Hirschberg, Executive Director The Vertical Flight Society www.vtol.org • [email protected] © Vertical Flight Society: CC-BY-SA 4.0 www.vtol.org ▪ The international professional society for those working to advance vertical flight – Founded in 1943 as the American Helicopter Society (AHS) – Everything from VTOL MAVs/UAS to helicopters, eVTOL, etc. ▪ Expands knowledge about vertical flight technology and promotes its application around the world CFD of Joby S4, Aug 2015 ▪ Advances safety and acceptability ▪ Advocates for vertical flight R&D funding ▪ Helps educate and support today’s and tomorrow’s vertical flight engineers and leaders ▪ Brings together the community — industry, academia and government agencies — to tackle the toughest challenges Join us today: www.vtol.org VFF Scholarship Winners at Forum 71, May 2015 © Vertical Flight Society: CC-BY-SA 4.0 2 www.vtol.org ▪ VFS has a long history of advocacy and leadership – Helped establish NASA-Army Joint Office, Nat’l Rotorcraft Technology Center (NRTC), Centers of Excellence, RITA/VLC – Worked with NASA and DoD to save the NFAC wind tunnel ▪ Provided major support to transformative initiatives NFAC 40 ft x 80 ft wind tunnel Courtesy of NASA – Joint Strike Fighter/F-35B STOVL Lightning II – V-22 Osprey tiltrotor ▪ Providing major foundational support to new transformative initiatives – Future Vertical Lift (FVL)/Joint Multi-Role (JMR) – Electric and hybrid-electric VTOL (eVTOL) Future Vertical Lift (FVL) VFS Works -
Federal Register/Vol. 85, No. 207/Monday, October 26, 2020
67692 Federal Register / Vol. 85, No. 207 / Monday, October 26, 2020 / Proposed Rules DEPARTMENT OF TRANSPORTATION Fort Worth, TX 76177. For information as ‘‘PROPIN.’’ The FAA will treat such on the availability of this material at the marked submissions as confidential Federal Aviation Administration FAA, call 817–222–5110. under the FOIA, and they will not be placed in the public docket of this Examining the AD Docket 14 CFR Part 39 NPRM. Submissions containing CBI You may examine the AD docket on should be sent to Neil Doh, Aerospace [Docket No. FAA–2020–0920; Project the internet at https:// Identifier AD–2020–00662–R] Engineer, Boston ACO Branch, FAA, www.regulations.gov by searching for 1200 District Avenue, Burlington, MA RIN 2120–AA64 and locating Docket No. FAA–2020– 01803. Any commentary that the FAA 0920; or in person at Docket Operations receives which is not specifically Airworthiness Directives; Sikorsky between 9 a.m. and 5 p.m., Monday Aircraft and Sikorsky Aircraft designated as CBI will be placed in the through Friday, except Federal holidays. public docket for this rulemaking. Corporation Helicopters The AD docket contains this NPRM, any Background AGENCY: Federal Aviation comments received, and other Administration (FAA), DOT. information. The street address for The FAA proposes to adopt a new AD Docket Operations is listed above. ACTION: Notice of proposed rulemaking for Sikorsky Aircraft Model S–61L, S– FOR FURTHER INFORMATION CONTACT: (NPRM). Neil 61N, S–61NM, and S–61R helicopters Doh, Aerospace Engineer, Boston ACO and Sikorsky Aircraft Corporation SUMMARY: The FAA proposes to adopt a Branch, FAA, 1200 District Avenue, Model S–61A, S–61D, S–61E, and S– new airworthiness directive (AD) for all Burlington, MA 01803; phone: 781– 61V restricted category helicopters, with Sikorsky Aircraft Model S–61L, S–61N, 238–7757; fax: 781–238–7199; email: an arm assembly, part number S6140– S–61NM, and S–61R helicopters and [email protected]. -
Sikorsky Multi-Mission Helicopter
SIKORSKY ® MULTI-MISSION S-92 HELICOPTER This Page Does Not Contain Export Controlled Technical Data COMFort AND CONVenience This Page Does Not Contain Export Controlled Technical Data REVolutionAry The Sikorsky S-92® helicopter is truly revolutionary. From enhanced safety features that meet the latest and most stringent FAA and JAA regulations to its various multi-mission capabilities, the S-92 helicopter’s versatility and dependability are unmatched. The S-92 is an aircraft capable of flying virtually any mission, anywhere, including offshore oil transport, search and rescue and airliner point-to-point service. In addition to the range of mission configurations the S-92 helicopter offers, it is also designed to be cost-effective to operate and easy to maintain. Whatever your mission requires you need an aircraft that’s up to the challenge. Safe, comfortable, reliable – the S-92 is all that and more. Ideal for passengers, pilots and operators alike, the S-92 helicopter is truly a revolutionary way to fly. S-92® is a registered trademark of Sikorsky Aircraft Corporation. All rights reserved. This Page Does Not Contain Export Controlled Technical Data A GenerAtion AheAD Improving Safety and Reliability Building on Sikorsky’s fifty year legacy of exceptional civil helicopters, the S-92 helicopter was the first in it’s class to meet the newest, most stringent FAA/JAA Part 29 requirements, and remains the only medium weight helicopter to meet those requirements without exception or waiver. The S-92 incorporates state-of-the-art technology such as active vibration control, composite blades, and a long list of advanced safety features that are a generation ahead of competitive helicopters. -
Aerospace Facts and Figures 1983/84
Aerospace Facts and Figures 1983/84 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC. 1725 DeSales Street, N.W., Washington, D.C. 20036 Published by Aviation Week & Space Technology A MCGRAW-HILL PUBLICATION 1221 Avenue of the Americas New York, N.Y. 10020 (212) 997-3289 $9.95 Per Copy Copyright, July 1983 by Aerospace Industries Association o' \merica, Inc. · Library of Congress Catalog No. 46-25007 2 Compiled by Economic Data Service Aerospace Research Center Aerospace Industries Association of America, Inc. 1725 DeSales Street, N.W., Washington, D.C. 20036 (202) 429-4600 Director Research Center Virginia C. Lopez Manager Economic Data Service Janet Martinusen Editorial Consultant James J. Haggerty 3 ,- Acknowledgments Air Transport Association of America Battelle Memorial Institute Civil Aeronautics Board Council of Economic Advisers Export-Import Bank of the United States Exxon International Company Federal Trade Commission General Aviation Manufacturers Association International Civil Aviation Organization McGraw-Hill Publications Company National Aer~mautics and Space Administration National Science Foundation Office of Management and Budget U.S. Departments of Commerce (Bureau of the Census, Bureau of Economic Analysis, Bureau of Industrial Economics) Defense (Comptroller; Directorate for Information, Operations and Reports; Army, Navy, Air Force) Labor (Bureau of Labor Statistics) Transportation (Federal Aviation Administration The cover and chapter art throughout this edition of Aerospace Facts and Figures feature computer-inspired graphics-hot an original theme in the contemporary business environment, but one particularly relevant to the aerospace industry, which spawned the large-scale development and application of computers, and conti.nues to incorpora~e computer advances in all aspects of its design and manufacture of aircraft, mis siles, and space products. -
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. -
Identification of Random Loads Impinging on the RAH-66 Comanche Helicopter Empennage Using Spectral Analysis
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 1998-06 Identification of random loads impinging on the RAH-66 Comanche Helicopter empennage using spectral analysis Mason, Patrick H. Monterey, California. Naval Postgraduate School http://hdl.handle.net/10945/8486 DUDLEY KNOX LIBRARY STGRADUATE SCHOOi MONTEgEY^Y^ C/ 5 1 q 1 NAVAL POSTGRADUATE SCHOOL Monterey, California THESIS IDENTIFICATION OF RANDOM LOADS IMPINGING ON THE RAH-66 COMANCHE HELICOPTER EMPENNAGE USING SPECTRAL ANALYSIS by Patrick H. Mason June 1998 Thesis Co-Advisors: E. Roberts Wood Donald A. Danielson Joshua H. Gordis Approved for public release; distribution is unlimited. REPORT DOCUMENTATION PAGE Form Approved OMB No 0704-01 i Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1 204, Arlington, VA 22202^302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-01 88) Washington DC 20503 1 . AGENCY USE ONLY (Leave blank) REPORT DATE REPORT TYPE AND DATES COVERED June 1998 Master's Thesis IDENTIFICATION OF RANDOM LOADS IMPrNGING ON THE RAH-66 FUNDING NUMBERS COMANCHE HELICOPTER EMPENNAGE USING SPECTRAL ANALYSIS AUTHOR(S) Mason, Patrick H. 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) PERFORMING Naval Postgraduate School ORGANIZATION Monterey CA 93943-5000 REPORT NUMBER 9. -
Design and Performance of Lift-Offset Rotorcraft for Short-Haul Missions
Design and Performance of Lift-Offset Rotorcraft for Short-Haul Missions Wayne Johnson Aeromechanics Branch National Aeronautics and Space Administration Ames Research Center, Moffett Field, California [email protected] Alex M. Moodie and Hyeonsoo Yeo Aeroflightdynamics Directorate (AMRDEC) U.S. Army Research, Development, and Engineering Command Ames Research Center, Moffett Field, California [email protected], [email protected] ABSTRACT The design and performance of compound helicopters utilizing lift-offset rotors are examined, in the context of short-haul, medium-size civil and military missions. The analysis tools used are the comprehensive analysis CAMRAD II and the sizing code NDARC. Following correlation of the comprehensive analysis with existing lift-offset aircraft flight test data, the rotor performance model for the sizing code was developed, and an initial estimate was made of the rotor size and key hover and cruise flight conditions. The rotor planform and twist were optimized for those conditions, and the sizing code rotor performance model updated. Two models for estimating the blade and hub weight of lift-offset rotors are discussed. The civil and military missions are described, along with the aircraft design assumptions. The aircraft are sized for 30 passengers or 6600 lb payload, with a range of 300 nm. Civil and military aircraft designs are described for each of the rotor weight models. Disk loading and blade loading were varied to optimize the designs, based on gross weight and fuel burn. The influence of technology is shown, in terms of rotor hub drag and rotor weight. and the rotor efficiency and lift capability steadily INTRODUCTION. -
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).