A Qualitative Introduction to the Vortex-Ring-State, Autorotation, and Optimal Autorotation
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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. -
Design, Modelling and Control of a Space UAV for Mars Exploration
Design, Modelling and Control of a Space UAV for Mars Exploration Akash Patel Space Engineering, master's level (120 credits) 2021 Luleå University of Technology Department of Computer Science, Electrical and Space Engineering Design, Modelling and Control of a Space UAV for Mars Exploration Akash Patel Department of Computer Science, Electrical and Space Engineering Faculty of Space Science and Technology Luleå University of Technology Submitted in partial satisfaction of the requirements for the Degree of Masters in Space Science and Technology Supervisor Dr George Nikolakopoulos January 2021 Acknowledgements I would like to take this opportunity to thank my thesis supervisor Dr. George Nikolakopoulos who has laid a concrete foundation for me to learn and apply the concepts of robotics and automation for this project. I would be forever grateful to George Nikolakopoulos for believing in me and for supporting me in making this master thesis a success through tough times. I am thankful to him for putting me in loop with different personnel from the robotics group of LTU to get guidance on various topics. I would like to thank Christoforos Kanellakis for guiding me in the control part of this thesis. I would also like to thank Björn Lindquist for providing me with additional research material and for explaining low level and high level controllers for UAV. I am grateful to have been a part of the robotics group at Luleå University of Technology and I thank the members of the robotics group for their time, support and considerations for my master thesis. I would also like to thank Professor Lars-Göran Westerberg from LTU for his guidance in develop- ment of fluid simulations for this master thesis project. -
Adventures in Low Disk Loading VTOL Design
NASA/TP—2018–219981 Adventures in Low Disk Loading VTOL Design Mike Scully Ames Research Center Moffett Field, California Click here: Press F1 key (Windows) or Help key (Mac) for help September 2018 This page is required and contains approved text that cannot be changed. NASA STI Program ... in Profile Since its founding, NASA has been dedicated • CONFERENCE PUBLICATION. to the advancement of aeronautics and space Collected papers from scientific and science. The NASA scientific and technical technical conferences, symposia, seminars, information (STI) program plays a key part in or other meetings sponsored or co- helping NASA maintain this important role. sponsored by NASA. The NASA STI program operates under the • SPECIAL PUBLICATION. Scientific, auspices of the Agency Chief Information technical, or historical information from Officer. It collects, organizes, provides for NASA programs, projects, and missions, archiving, and disseminates NASA’s STI. The often concerned with subjects having NASA STI program provides access to the NTRS substantial public interest. Registered and its public interface, the NASA Technical Reports Server, thus providing one of • TECHNICAL TRANSLATION. the largest collections of aeronautical and space English-language translations of foreign science STI in the world. Results are published in scientific and technical material pertinent to both non-NASA channels and by NASA in the NASA’s mission. NASA STI Report Series, which includes the following report types: Specialized services also include organizing and publishing research results, distributing • TECHNICAL PUBLICATION. Reports of specialized research announcements and feeds, completed research or a major significant providing information desk and personal search phase of research that present the results of support, and enabling data exchange services. -
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). -
Rotor Spring 2018
Departments Features Index of Advertisers Spring 2018 rotor.org Serving the International BY THE INDUSTRY Helicopter Community FOR THE INDUSTRY Grand Canyon Helitack The Best Job in Aviation? What’s In Your Jet Fuel? p 58 Vietnam Pilots and Crew Members Honored p 28 Make the Connection March 4–7, 2019 • Atlanta Georgia World Congress Center Exhibits Open March 5–7 Apply for exhibit space at heliexpo.rotor.org LOTTERY 1* Open to HAI HELI-EXPO 2018 Exhibitors APPLY BY June 22, 2018 WITH PAYMENT LOTTERY 2 Open to All Companies APPLY BY Aug. 10, 2018 WITH PAYMENT heliexpo.rotor.org * For information on how to upgrade within Lottery 1, contact [email protected]. EXHIBIT NOW FALCON CREST AVIATION PROUDLY SUPPLIES & MAINTAINS AVIATION’S BEST SEALED LEAD ACID BATTERY RG-380E/44 RG-355 RG-214 RG-222 RG-390E RG-427 RG-407 RG-206 Bell Long Ranger Bell 212, 412, 412EP Bell 407 RG-222 (17 Ah) or RG-224 (24 Ah) RG-380E/44 (42 Ah) RG-407A1 (27 Ah) Falcon Crest STC No. SR09069RC Falcon Crest STC No. SR09053RC Falcon Crest STC No. SR09359RC Airbus Helicopters Bell 222U Airbus Helicopters AS355 E, F, F1, F2, N RG-380E/44 (42 Ah) BK 117, A-1, A-3, A-4, B-1, B-2, C-1 RG-355 (17 Ah) Falcon Crest STC No. SR09142RC RG-390E (28 Ah) Falcon Crest STC No. SR09186RC Falcon Crest STC No. SR09034RC Sikorsky S-76 A, C, C+ Airbus Helicopters RG-380E/44 (42 Ah) Airbus Helicopters AS350B, B1, B2, BA, C, D, D1 Falcon Crest STC No. -
Helicopter Safety July-August 1991
F L I G H T S A F E T Y F O U N D A T I O N HELICOPTER SAFETY Vol. 17 No. 4 For Everyone Concerned with the Safety of Flight July/August 1991 The Philosophy and Realities of Autorotations Like the power-off glide in a fixed-wing aircraft, the autorotation in a helicopter must be used properly if it is to be a successful safety maneuver. by Michael K. Hynes Aviation Consultant In all helicopter flying, there is no single event that has a In the early years of airplane flight, the fear of engine greater impact on safety than the autorotation maneuver. failure, or that the airplane might have structural prob- The mere mention of the word “autorotation” at any lems during flight, was very strong. If either of these gathering of helicopter pilots, especially flight instruc- events took place, the pilot’s ability to get the airplane tors, will guarantee a long and lively discussion. safely on the ground quickly was important. The time it took to get the airplane on the ground was directly in There are many misconceptions about autorotations and proportion to the altitude at which the airplane was being they contribute to the accident rate when an autorotation flown. It is therefore logical that all early flights were precedes a helicopter landing accident. One approach to flown at low altitudes, often at less than 500 feet above a discussion of autorotations is to look at the subject the ground (agl). from three views: first, the philosophy of the subject; second, the reality of the circumstances that require au- At these low altitudes, the pilot did not always have the torotations; and third, the execution of the maneuver. -
DYNAMIC MODELING of AUTOROTATION for SIMULTANEOUS LIFT and WIND ENERGY EXTRACTION by SADAF MACKERTICH B.S. Rochester Institute O
DYNAMIC MODELING OF AUTOROTATION FOR SIMULTANEOUS LIFT AND WIND ENERGY EXTRACTION by SADAF MACKERTICH B.S. Rochester Institute of Technology, 2012 A thesis submitted in partial fulfilment of the requirements for the degree of Master of Science in the Department of Mechanical and Aerospace Engineering in the College of Engineering and Computer Science at the University of Central Florida Orlando, Florida Spring Term 2016 Major Professor: Tuhin Das c 2016 Sadaf Mackertich ii ABSTRACT The goal of this thesis is to develop a multi-body dynamics model of autorotation with the objective of studying its application in energy harvesting. A rotor undergoing autorotation is termed an Autogyro. In the autorotation mode, the rotor is unpowered and its interaction with the wind causes an upward thrust force. The theory of an autorotating rotorcraft was originally studied for achieving safe flight at low speeds and later used for safe descent of helicopters under engine failure. The concept can potentially be used as a means to collect high-altitude wind energy. Autorotation is inherently a dynamic process and requires detailed models for characterization. Existing models of autorotation assume steady operating conditions with constant angu- lar velocity of the rotor. The models provide spatially averaged aerodynamic forces and torques. While these steady-autorotation models are used to create a basis for the dynamic model developed in this thesis, the latter uses a Lagrangian formulation to determine the equations of motion. The aerodynamic effects on the blades that produce thrust forces, in- plane torques, and out-of-plane torques, are modeled as non-conservative forces within the Lagrangian framework. -
Development of a Helicopter Vortex Ring State Warning System Through a Moving Map Display Computer
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 1999-09 Development of a helicopter vortex ring state warning system through a moving map display computer Varnes, David J. Monterey, California. Naval Postgraduate School http://hdl.handle.net/10945/26475 DUDLEY KNOX LIBRARY NAVAL POSTGRADUATE SCHOOL MONTEREY CA 93943-5101 NAVAL POSTGRADUATE SCHOOL Monterey, California THESIS DEVELOPMENT OF A HELICOPTER VORTEX RING STATE WARNING SYSTEM THROUGH A MOVING MAP DISPLAY COMPUTER by David J. Varnes September 1999 Thesis Advisor: Russell W. Duren Approved for public release; distribution is unlimited. 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 1204, Arlington. VA 22202-4302, and to the Office of Management and Budget. Paperwork Reduction Project (0704-0188) Washington DC 20503. REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED 1. agency use only (Leave blank) September 1999 Master's Thesis 4. TITLE AND SUBTITLE 5. FUNDING NUMBERS DEVELOPMENT OF A HELICOPTER VORTEX RING STATE WARNING SYSTEM THROUGH A MOVING MAP DISPLAY COMPUTER 6. AUTHOR(S) Varnes, David, J. 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) PERFORMING ORGANIZATION Naval Postgraduate School REPORT NUMBER Monterey, CA 93943-5000 10. -
WYVER Heavy Lift VTOL Aircraft
WYVER Heavy Lift VTOL Aircraft Rensselaer Polytechnic Institute 1st June, 2005 1 ACKNOWLEDGEMENTS We would like to thank Professor Nikhil Koratkar for his help, guidance, and recommendations, both with the technical and aesthetic aspects of this proposal. 22ND ANNUAL AHS INTERNATIONAL STUDENT DESIGN COMPETITION UNDERGRADUATE CATEGORY Robin Chin Raisul Haque Rafael Irizarry Heather Maffei Trevor Tersmette 2 TABLE OF CONTENTS Executive Summary.................................................................................................................................. 4 1. Introduction........................................................................................................................................... 9 2. Design Philosophy.............................................................................................................................. 10 2.1 Mission Requirements .................................................................................................................. 11 2.2 Aircraft Configuration Trade Study.............................................................................................. 11 2.2.1 Tandem Design Evaluation.................................................................................................... 12 2.2.2 Tilt-Rotor Design Evaluation ................................................................................................ 15 2.2.3 Tri-Rotor Design Evaluation ................................................................................................ -
US 2005/0151003 A1 Churchman (43) Pub
US 2005O151003A1 (19) United States (12) Patent Application Publication (10) Pub. No.: US 2005/0151003 A1 Churchman (43) Pub. Date: Jul. 14, 2005 (54) V/STOL BIPLANE jyrodyne. The jyrodyne comprises a central fuselage with biplane-type Wings arranged in a negative Stagger arrange (76) Inventor: Charles Gilpin Churchman, Norcross, ment, a horizontal ducted fan inlet Shroud located at the GA (US) center of gravity in the top biplane wing, a rotor mounted in Correspondence Address: the Shroud, outrigger wing Support landing gear, a forward SUTHERLAND ASBILL & BRENNAN LLP mounted canard wing and passenger compartment, a mul 999 PEACHTREE STREET, N.E. tiple Vane-type air deflector System for control and Stability ATLANTA, GA 30309 (US) in VTOL mode, a Separate tractor propulsion System for forward flight, and a full-span T-tail. Wingtip extensions on (21) Appl. No.: 10/820,378 the two main wings extend aft to attach to the T-tail. The powerplants consist of two four cylinder two-stroke recip (22) Filed: Apr. 8, 2004 rocating internal combustion engines. Power from the engines is distributed between the ducted fan and tractor Related U.S. Application Data propeller through the use of a drivetrain incorporating two (63) Continuation of application No. 10/313,580, filed on pneumatic clutches, controlled by an automotive Style foot Dec. 9, 2002, now Pat. No. 6,848,649, which is a pedal to the left of the rudder pedals. When depressed, continuation-in-part of application No. 09/677,749, power is transmitted to the ducted fan for vertical lift. When filed on Oct. -
Introduction of the M-85 High-Speed Rotorcraft Concept Robert H
t NASA Technical Memorandum 102871 Introduction of the M-85 High-Speed Rotorcraft Concept Robert H. Stroub '-] ,t 0 January 1991 National Aeronautics and Space Administration NASATechnicalMemorandum102871 Introduction of the M-85 High-Speed Rotorcraft Concept Robert H. Stroub, Ames Research Center, Moffett Field, California January 1991 NationalAeronautics and Space Administration Ames Research Center Moffett Field, California 94035-1000 ABSTRACT As a result of studying possible requirements for high-speed rotorcrafl and studying many high- speed concepts, a new high-speed rotorcraft concept, designated as M-85, has been derived. The M-85 is a helicopter that is reconfigured to a fixed-wing aircraft for high-speed cruise. The concept was derived as an approach to enable smooth, stable conversion between fixed-wing and rotary-wing while retaining hover and low-speed flight characteristics of a low disk loading helicopter. The name, M-85, reflects the high-speed goal of 0.85 Mach Number at high altitude. For a high-speed rotorcraft, it is expected that a viable concept must be a cruise-efficient, fixed-wing aircraft so it may be attractive for a multiplicity of missions. It is also expected that a viable high-speed rotorcraft con- cept must be cruise efficient first and secondly, efficient in hover. What makes the M-85 unique is the large circular hub fairing that is large enough to support the aircraft during conversion between rotary-wing and fixed-wing modes. With the aircraft supported by this hub fairing, the rotor blades can be unloaded during the 100% change in rotor rpm. With the blades unloaded, the potential for vibratory loads would be lessened. -
Cash Flow Analysis in the Engineering Field, Cash Flow Analysis Is Most Commonly Used in Describing the Predicted Profitability of a Project
e - /6 - u £ / Final Report NAS3-00179/L-70884-D Personal Air Vehicle Exploration Tool and Modeling Under Contract NAS3-00179/L-70884-D Submitted To: Marie L. Smith, Contract Specialist NASA Langley Research Center PHONE (757) 864-4122 FAX (757) 864-8863 [email protected] and NASA Task Manager: Mr. Mark Moore Mail Stop 348 NASA Langley Research Center Tel. No.: 757-864-2262 Fax No.: 757-864-6306 Submitted by: Aerospace Systems Design Laboratory School of Aerospace Engineering Georgia Institute of Technology Atlanta, Georgia 30332-0150 Principal Investigators: Professor Dimitri N. Mavns Dr. Daniel DeLaurentis Director Research Engineer II Aerospace Systems Design Laboratory Aerospace Systems Design Laboratory School of Aerospace Engineering School of Aerospace Engineering Georgia Institute of Technology Georgia Institute of Technology (404) 894-1557 (404) 894-8280 dimitri. [email protected]. edu dan. [email protected]. edu DATE: October 31, 2002 Georgia Tech A SDL 1 Final Report NAS3-00179/L-70884-D Executive Summary ASDL has completed the current phase of research to "continue development of analysis tools for Personal Air Vehicle Exploration (PAVE) system studies", under NASA Langley's Revolutionary Aerospace Systems Concepts (RASC) program. ASDL has completed the current phase of the research and the results are described in this final report (fulfilling contract NAS3-00179/L-70884-D). The developed tools are intended to explore fundamental feasibility questions about doorstep to doorstep transportation solutions involving both air and ground travel. Key metrics for establishing fundamental feasibility are the reduction of personal travel time, the increase in travel mobility, and the ability to achieve a market share at an affordable cost while satisfying societal constraints.