NASA Mars Helicopter Team Striving for a “Kitty Hawk” Moment
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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 ........................................ -
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). -
Planetary Exploration Using Biomimetics an Entomopter for Flight on Mars Phase II Project NAS5-98051
Planetary Exploration Using Biomimetics An Entomopter for Flight On Mars Phase II Project NAS5-98051 NIAC Fellows Conference June 11-12, 2002 Lunar and Planetary Institute Houston Texas Anthony Colozza Northland Scientific / Ohio Aerospace Institute Cleveland, Ohio Planetary Exploration Using Biomimetics Team Members • Mr. Anthony Colozza / Northland Scientific Inc. • Prof. Robert Michelson / Georgia Tech Research Institute • Mr. Teryn Dalbello / University of Toledo ICOMP • Dr.Carol Kory / Northland Scientific Inc. • Dr. K.M. Isaac / University of Missouri-Rolla • Mr. Frank Porath / OAI • Mr. Curtis Smith / OAI Mars Exploration Mars has been the primary object of planetary exploration for the past 25 years To date all exploration vehicles have been landers orbiters and a rover The next method of exploration that makes sense for mars is a flight vehicle Mars Exploration Odyssey Orbiter Viking I & II Lander & Orbiter Global Surveyor Pathfinder Lander & Rover Mars Environment Mars Earth Temp Range -143°C to 27°C -62°C to 50°C & Mean -43°C 15°C Surface 650 Pa 103300 Pa Pressure Gravity 3.75 m/s2 9.81 m/s2 Day Length 24.6 hrs 23.94 hrs Year Length 686 days 365.26 days Diameter 6794 km 12756 km Atmosphere CO2 N2, O2 Composition History of Mars Aircraft Concepts Inflatable Solar Aircraft Concept Hydrazine Power Aircraft Concept MiniSniffer Aircraft Long Endurance Solar Aircraft Concept Key Challenges to Flight On Mars • Atmospheric Conditions (Aerodynamics) • Deployment • Communications • Mission Duration Environment: Atmosphere • Very low atmospheric -
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. -
HELICOPTER SAFETY Vol
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. 16 No. 6 For Everyone Concerned with the Safety of Flight November/December 1990 Inflight Icing and the Helicopter Results of a U.S. Army investigation into the unique hazards facing rotary wing operations in the winter environment offers timely tips for all helicopter flight crews. Traditionally, helicopter operating manuals have addressed of fixed-wing flight. Typically, we have characterized the issue of inflight icing and its effect on helicopter icing problems by their effect on lift, drag, weight and performance with a caution or a warning to the pilot to thrust. It is readily accepted that inflight icing reduces avoid an icing environment. Such restrictions and limita- thrust and lift, and increases drag and weight, all to the tions were acceptable when helicopters were viewed as detriment of aircraft performance. aircraft operating primarily in visual meteorological con- ditions (VMC). Since early helicopters lacked the equip- Rotary-wing aircraft also suffer from these effects when ment and sophisticated systems normally employed for exposed to icing conditions and, in addition, are suscep- flight in instrument meteorological conditions (IMC), there tible to various complications that are not common to was little justification for expending valuable time and fixed-wing aircraft. Although many questions remain resources on helicopter icing research and development. regarding helicopter icing and its impact on aircraft per- formance and mission effectiveness, researchers are un- However, modern helicopters have a greatly expanded covering significant insights into this facet of helicopter concept of operations and today they routinely perform a development. -
The Pennsylvania State University the Graduate School Department of Aerospace Engineering an INVESTIGATION of PERFORMANCE BENEFI
The Pennsylvania State University The Graduate School Department of Aerospace Engineering AN INVESTIGATION OF PERFORMANCE BENEFITS AND TRIM REQUIREMENTS OF A VARIABLE SPEED HELICOPTER ROTOR A Thesis in Aerospace Engineering by Jason H. Steiner 2008 Jason H. Steiner Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science August 2008 ii The thesis of Jason Steiner was reviewed and approved* by the following: Farhan Gandhi Professor of Aerospace Engineering Thesis Advisor Robert Bill Research Associate , Department of Aerospace Engineering George Leisuietre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School iii ABSTRACT This study primarily examines the main rotor power reductions possible through variation in rotor RPM. Simulations were based on the UH-60 Blackhawk helicopter, and emphasis was placed on possible improvements when RPM variations were limited to ± 15% of the nominal rotor speed, as such limited variations are realizable through engine speed control. The studies were performed over the complete airspeed range, from sea level up to altitudes up to 12,000 ft, and for low, moderate and high vehicle gross weight. For low altitude and low to moderate gross weight, 17-18% reductions in main rotor power were observed through rotor RPM reduction. Reducing the RPM increases rotor collective and decreases the stall margin. Thus, at higher airspeeds and altitudes, the optimal reductions in rotor speed are smaller, as are the power savings. The primary method for power reduction with decreasing rotor speed is a decrease in profile power. When rotor speed is optimized based on both power and rotor torque, the optimal rotor speed increases at low speeds to decrease rotor torque without power penalties. -
The Pennsylvania State University
The Pennsylvania State University The Graduate School Department of Aerospace Engineering REAL-TIME PATH PLANNING AND AUTONOMOUS CONTROL FOR HELICOPTER AUTOROTATION A Dissertation in Aerospace Engineering by Thanan Yomchinda 2013 Thanan Yomchinda Submitted in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy May 2013 The dissertation of Thanan Yomchinda was reviewed and approved* by the following: Joseph F. Horn Associate Professor of Aerospace Engineering Dissertation Co-Advisor Co-Chair of Committee Jacob W. Langelaan Associate Professor of Aerospace Engineering Dissertation Co-Advisor Co-Chair of Committee Edward C. Smith Professor of Aerospace Engineering Christopher D. Rahn Professor of Mechanical Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School iii ABSTRACT Autorotation is a descending maneuver that can be used to recover helicopters in the event of total loss of engine power; however it is an extremely difficult and complex maneuver. The objective of this work is to develop a real-time system which provides full autonomous control for autorotation landing of helicopters. The work includes the development of an autorotation path planning method and integration of the path planner with a primary flight control system. The trajectory is divided into three parts: entry, descent and flare. Three different optimization algorithms are used to generate trajectories for each of these segments. The primary flight control is designed using a linear dynamic inversion control scheme, and a path following control law is developed to track the autorotation trajectories. Details of the path planning algorithm, trajectory following control law, and autonomous autorotation system implementation are presented. -
Moon-Miners-Manifesto-Mars.Pdf
http://www.moonsociety.org/mars/ Let’s make the right choice - Mars and the Moon! Advantages of a low profile for shielding Mars looks like Arizona but feels like Antarctica Rover Opportunity at edge of Endeavor Crater Designing railroads and trains for Mars Designing planes that can fly in Mars’ thin air Breeding plants to be “Mars-hardy” Outposts between dunes, pulling sand over them These are just a few of the Mars-related topics covered in the past 25+ years. Read on for much more! Why Mars? The lunar and Martian frontiers will thrive much better as trading partners than either could on it own. Mars has little to trade to Earth, but a lot it can trade with the Moon. Both can/will thrive together! CHRONOLOGICAL INDEX MMM THEMES: MARS MMM #6 - "M" is for Missing Volatiles: Methane and 'Mmonia; Mars, PHOBOS, Deimos; Mars as I see it; MMM #16 Frontiers Have Rough Edges MMM #18 Importance of the M.U.S.-c.l.e.Plan for the Opening of Mars; Pavonis Mons MMM #19 Seizing the Reins of the Mars Bandwagon; Mars: Option to Stay; Mars Calendar MMM #30 NIMF: Nuclear rocket using Indigenous Martian Fuel; Wanted: Split personality types for Mars Expedition; Mars Calendar Postscript; Are there Meteor Showers on Mars? MMM #41 Imagineering Mars Rovers; Rethink Mars Sample Return; Lunar Development & Mars; Temptations to Eco-carelessness; The Romantic Touch of Old Barsoom MMM #42 Igloos: Atmosphere-derived shielding for lo-rem Martian Shelters MMM #54 Mars of Lore vs. Mars of Yore; vendors wanted for wheeled and walking Mars Rovers; Transforming Mars; Xities -
Comparative Study of Aerial Platforms for Mars Exploration
Comparative Study of Aerial Platforms for Mars Exploration Thesis by Nasreen Dhanji Department of Mechanical Engineering McGill University Montreal, Canada October 2007 A Thesis submitted to McGill University in partial fulfillment of the requirements for the degree of Master of Engineering © Nasreen Dhanji, 2007 Library and Bibliotheque et 1*1 Archives Canada Archives Canada Published Heritage Direction du Branch Patrimoine de I'edition 395 Wellington Street 395, rue Wellington Ottawa ON K1A0N4 Ottawa ON K1A0N4 Canada Canada Your file Votre reference ISBN: 978-0-494-51455-9 Our file Notre reference ISBN: 978-0-494-51455-9 NOTICE: AVIS: The author has granted a non L'auteur a accorde une licence non exclusive exclusive license allowing Library permettant a la Bibliotheque et Archives and Archives Canada to reproduce, Canada de reproduire, publier, archiver, publish, archive, preserve, conserve, sauvegarder, conserver, transmettre au public communicate to the public by par telecommunication ou par Plntemet, prefer, telecommunication or on the Internet, distribuer et vendre des theses partout dans loan, distribute and sell theses le monde, a des fins commerciales ou autres, worldwide, for commercial or non sur support microforme, papier, electronique commercial purposes, in microform, et/ou autres formats. paper, electronic and/or any other formats. The author retains copyright L'auteur conserve la propriete du droit d'auteur ownership and moral rights in et des droits moraux qui protege cette these. this thesis. Neither the thesis Ni la these ni des extraits substantiels de nor substantial extracts from it celle-ci ne doivent etre imprimes ou autrement may be printed or otherwise reproduits sans son autorisation.