Stability Analysis of the Slowed-Rotor Compound Helicopter Configuration
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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. -
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. -
NASA Mars Helicopter Team Striving for a “Kitty Hawk” Moment
NASA Mars Helicopter Team Striving for a “Kitty Hawk” Moment NASA’s next Mars exploration ground vehicle, Mars 2020 Rover, will carry along what could become the first aircraft to fly on another planet. By Richard Whittle he world altitude record for a helicopter was set on June 12, 1972, when Aérospatiale chief test pilot Jean Boulet coaxed T his company’s first SA 315 Lama to a hair-raising 12,442 m (40,820 ft) above sea level at Aérodrome d’Istres, northwest of Marseille, France. Roughly a year from now, NASA hopes to fly an electric helicopter at altitudes equivalent to two and a half times Boulet’s enduring record. But NASA’s small, unmanned machine actually will fly only about five meters above the surface where it is to take off and land — the planet Mars. Members of NASA’s Mars Helicopter team prepare the flight model (the actual vehicle going to Mars) for a test in the JPL The NASA Mars Helicopter is to make a seven-month trip to its Space Simulator on Jan. 18, 2019. (NASA photo) destination folded up and attached to the underbelly of the Mars 2020 Rover, “Perseverance,” a 10-foot-long (3 m), 9-foot-wide (2.7 The atmosphere of Mars — 95% carbon dioxide — is about one m), 7-foot-tall (2.13 m), 2,260-lb (1,025-kg) ground exploration percent as dense as the atmosphere of Earth. That makes flying at vehicle. The Rover is scheduled for launch from Cape Canaveral five meters on Mars “equal to about 100,000 feet [30,480 m] above this July on a United Launch Alliance Atlas V rocket and targeted sea level here on Earth,” noted Balaram. -
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. -
Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks
Purdue University Purdue e-Pubs Department of Electrical and Computer Department of Electrical and Computer Engineering Technical Reports Engineering August 1991 Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks Tobias J. Pallett Purdue University School of Electrical Engineering Shaheen Ahmad Purdue University School of Electrical Engineering Follow this and additional works at: https://docs.lib.purdue.edu/ecetr Pallett, Tobias J. and Ahmad, Shaheen, "Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks" (1991). Department of Electrical and Computer Engineering Technical Reports. Paper 317. https://docs.lib.purdue.edu/ecetr/317 This document has been made available through Purdue e-Pubs, a service of the Purdue University Libraries. Please contact [email protected] for additional information. Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks Tobias J. Pallett Shaheen Ahmad TR-EE 91-35 August 1991 Real-Time Helicopter Flight Control: Modelling and Control by Lineal-ization and Neural Networks Tobias J. Pallett and Shaheen Ahmad Real-Time Robot Control Laboratory, School of Electrical Engineering, Purdue University West Lafayette, IN 47907 USA ABSTRACT In this report we determine the dynamic model of a miniature helicopter in hovering flight. Identification procedures for the nonlinear terms are also described. The model is then used to design several linearized control laws and a neural network controller. The controllers were then flight tested on a miniature helicopter flight control test bed the details of which are also presented in this report. Experimental performance of the linearized and neural network controllers are discussed. -
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. -
Micro Coaxial Helicopter Controller Design
Micro Coaxial Helicopter Controller Design A Thesis Submitted to the Faculty of Drexel University by Zelimir Husnic in partial fulfillment of the requirements for the degree of Doctor of Philosophy December 2014 c Copyright 2014 Zelimir Husnic. All Rights Reserved. ii Dedications To my parents and family. iii Acknowledgments There are many people who need to be acknowledged for their involvement in this research and their support for many years. I would like to dedicate my thankfulness to Dr. Bor-Chin Chang, without whom this work would not have started. As an excellent academic advisor, he has always been a helpful and inspiring mentor. Dr. B. C. Chang provided me with guidance and direction. Special thanks goes to Dr. Mishah Salman and Dr. Humayun Kabir for their mentorship and help. I would like to convey thanks to my entire thesis committee: Dr. Chang, Dr. Kwatny, Dr. Yousuff, Dr. Zhou and Dr. Kabir. Above all, I express my sincere thanks to my family for their unconditional love and support. iv v Table of Contents List of Tables ........................................... viii List of Figures .......................................... ix Abstract .............................................. xiii 1. Introduction .......................................... 1 1.1 Vehicles to be Discussed................................... 1 1.2 Coaxial Benefits ....................................... 2 1.3 Motivation .......................................... 3 2. Helicopter Flight Dynamics ................................ 4 2.1 Introduction ........................................ -
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). -
(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. -
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. -
Session a – Tuesday Morning, May 5 – 8:00 A.M. – 12 Noon Aerodynamics I Aircraft Design I Crash Safety I Dynamics I Paper # 1 – 8:00 – 8:30 A.M
Session A – Tuesday Morning, May 5 – 8:00 a.m. – 12 noon Aerodynamics I Aircraft Design I Crash Safety I Dynamics I Paper # 1 – 8:00 – 8:30 a.m. Paper # 1 – 8:00 – 8:30 a.m. Paper # 1 – 8:00 – 8:30 a.m. Paper # 1 – 8:00 – 8:30 a.m. Navier-Stokes Assessment of Systematic Analysis of Rotor Evaluation of the Second Investigation of Whirl Flutter Test Facility Effects on Hover Blade Effective Twist Due to Transport Rotorcraft Airframe Stabilization using Active Performance (48) Planform Variation (76) Crash Testbed (TRACT 2) Full Trailing Edge Flaps (62) Neal Chaderjian and Jasim Fu-Shang (John) Wei, Central Scale Crash Test (73) Tobias Richter, Tobias Rath and Ahmad, NASA Ames Research Connecticut State U. and David Martin Annett, NASA Langley Walter Fichter, University of Center A. Peters, Washington Research Center Stuttgart; Oliver Oberinger, Paper # 2– 8:30 – 9:00 a.m. University, St Louis Paper # 2– 8:30 – 9:00 a.m. Technical University of Munich Comparing Numerical and Paper # 2– 8:30 – 9:00 a.m. Rotocraft Troop Seat with Paper # 2– 8:30 – 9:00 a.m. Experimental Results for Drag Development of Rotor Selectable Energy Absorber Effects of 2/rev Trailing Edge Reduction by Active Flow Structural Design Optimization System – Design & Test (145) Flap Input on Helicopter Control Applied to a Generic Framework for Compound Stanley Desjardins and Leda Vibrations for Modular Multi- Rotorcraft Fuselage (59) Rotorcraft with a Lift Offset (53) Belden, Safe Inc.; Lance Labun, Objective Active Rotor Control Caroline Lienard and Arnaud Le SangJoon Shin and YooJin Kang, Labun, LLC; Jin Woodhouse, US (56) Pape, ONERA; Norman W.