DOCSLIB.ORG

Dynamic Modeling, Simulation and Control Design of a Parafoil-Payload

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Dynamic Modeling, Simulation and Control Design of a Parafoil-Payload Michigan Technological University Digital Commons @ Michigan Tech Dissertations, Master's Theses and Master's Dissertations, Master's Theses and Master's Reports - Open Reports 2011 Dynamic modeling, simulation and control design of a parafoil- payload system for ship launched aerial delivery system (SLADS) Anand S. Puranik Michigan Technological University Follow this and additional works at: https://digitalcommons.mtu.edu/etds Part of the Mechanical Engineering Commons Copyright 2011 Anand S. Puranik Recommended Citation Puranik, Anand S., "Dynamic modeling, simulation and control design of a parafoil-payload system for ship launched aerial delivery system (SLADS)", Dissertation, Michigan Technological University, 2011. https://digitalcommons.mtu.edu/etds/401 Follow this and additional works at: https://digitalcommons.mtu.edu/etds Part of the Mechanical Engineering Commons DYNAMIC MODELING, SIMULATION AND CONTROL DESIGN OF A PARAFOIL-PAYLOAD SYSTEM FOR SHIP LAUNCHED AERIAL DELIVERY SYSTEM (SLADS) By Anand S Puranik A DISSERTATION Submitted in partial fulfillment of the requirements for the degree of DOCTOR OF PHILOSOPHY (Mechanical Engineering – Engineering Mechanics) MICHIGAN TECHNOLOGICAL UNIVERSITY 2011 Copyright © 2011 Anand S Puranik This dissertation, “Dynamic Modeling, Simulation And Control Design Of A Parafoil- Payload System For Ship Launched Aerial Delivery System (SLADS),” is hereby approved in partial fulfillment for the requirements for the Degree of DOCTOR OF PHILOSOPHY IN Mechanical Engineering – Engineering Mechanics. Department of Mechanical Engineering – Engineering Mechanics Advisor: Dr. Gordon Parker Committee Member: Dr. Chris Paserrello Committee Member: Dr. Jason Blough Committee Member: Dr. Allan Struthers Department Chair: Professor William W. Predebon Date: Contents List of Figures :::::::::::::::::::::::::::::::::: x List of Tables ::::::::::::::::::::::::::::::::::: xii Acknowledgments :::::::::::::::::::::::::::::::: xiii Nomenclature :::::::::::::::::::::::::::::::::: xiv Abstract ::::::::::::::::::::::::::::::::::::: xxi 1. Introduction ::::::::::::::::::::::::::::::::::: 1 1.1 Background .................................. 2 1.2 Aerodynamic Decelerators .......................... 4 1.2.1 Parachute ............................... 4 1.2.2 Parasail ................................ 4 1.2.3 Paraglider ............................... 6 1.2.3.1 Parafoil Canopy ...................... 7 1.2.3.2 Leading Edge ....................... 7 1.2.3.3 Trailing Edge ....................... 7 1.2.3.4 Suspension Lines ..................... 7 iv 1.2.3.5 Control Lines ....................... 7 1.2.3.6 Risers ........................... 8 1.3 Ship Launched Aerial Delivery System (SLADS) .............. 8 1.4 Research Contributions ............................ 9 1.5 Dissertation Outline .............................. 10 2. Literature Review :::::::::::::::::::::::::::::::: 11 2.1 Parafoil Evolution ............................... 11 2.2 Hang gliders and Paragliders ......................... 13 2.3 Dynamic Models ............................... 13 2.4 Aerodynamic Theory ............................. 19 2.4.1 Angle Of Attack (α) ......................... 19 2.4.2 Side Slip Angle (β) .......................... 20 2.4.3 Aerodynamic Forces ......................... 20 2.4.3.1 Drag ............................ 20 2.4.3.2 Lift ............................. 21 2.4.3.3 Side Force ......................... 21 2.4.4 Aerodynamic Moments ........................ 22 2.4.4.1 Pitching Moment ..................... 22 2.4.4.2 Rolling Moment ...................... 22 2.4.4.3 Yawing Moment ...................... 23 2.5 Stability Analysis ............................... 23 2.6 Control Input ................................. 30 2.7 Apparent Mass Effects ............................ 31 v 3. Modeling Of Towed Parafoil-Payload System :::::::::::::::::: 32 3.1 Model Description And Modeling Assumptions ............... 32 3.2 Equations Of Motion ............................. 34 3.2.1 Rotation Matrices ........................... 36 3.2.2 Kinematics .............................. 37 3.2.3 Lagrange Equations ......................... 38 3.2.4 Generalized Forces .......................... 39 3.2.5 Dynamic Equations .......................... 41 3.3 Aerodynamic Model ............................. 41 3.3.1 Control Inputs ............................ 46 3.4 Geometric and Inertial Properties ....................... 50 3.4.1 Inertia Calculations .......................... 52 3.5 2D Simulation Results ............................ 55 3.6 Operator-In-The-Loop Simulation ...................... 60 4. Stability Analysis ::::::::::::::::::::::::::::::::: 62 4.1 Motivation ................................... 62 4.2 Linear Model ................................. 64 4.2.1 Lyapunov’s Linearization Method .................. 64 4.2.2 Linearization of Dynamic System .................. 65 4.3 Steady State Flight .............................. 69 4.4 Linear and Nonlinear Model Comparison .................. 71 4.5 Stability Boundaries .............................. 73 4.5.1 Elevation Angle η .......................... 75 4.5.2 Symmetric Brake Deflection δs ................... 81 vi 4.5.3 Effect of Tow Point Location ..................... 82 4.6 Summary ................................... 85 5. Control System Design :::::::::::::::::::::::::::::: 86 5.1 Control Objectives .............................. 86 5.2 Controllability And Observability ...................... 87 5.2.1 Definition ............................... 89 5.2.2 Case I ................................. 90 5.2.3 Case II: ................................ 93 5.2.4 Case III: ................................ 95 5.3 Tow Up Control Strategy ........................... 97 5.3.1 Controller for Ascent Rate ...................... 99 5.4 Lateral Stability Control ........................... 104 5.4.1 Lateral State Feedback Controller .................. 104 5.4.2 Full State Feedback Controller .................... 108 5.5 Conclusions .................................. 113 6. Conclusions And Future Work :::::::::::::::::::::::::: 115 References :::::::::::::::::::::::::::::::::::: 118 A. Nonlinear Dynamic Equation Coefficients :::::::::::::::::::: 122 B. Derivation of Equations of Motion: Maple Script :::::::::::::::: 149 C. Steady State Values ::::::::::::::::::::::::::::::: 158 D. Copyrights :::::::::::::::::::::::::::::::::::: 166 List of Figures 1.1 An American paratrooper using a MC1-1C series parachute (1). (See Ap- pendix D for the documentation that this material is in public domain.) ... 5 1.2 Parasail is a towed parachute (2). (See Appendix D for the documentation that this material is in public domain.) .................... 5 1.3 Significant parts of a paraglider or ram-air parachute (3). (See Appendix D for the documentation of the permission to republish this image). ...... 6 1.4 Stages of operation of SLADS. ........................ 9 2.1 Francis Rogallo with his parawing in the wind tunnel. (Photo credit: NASA/courtesy of nasaimages.org. See Appendix D for the documentation that this image is in the public domain.) ........................... 12 2.2 NASA X-38 re-entry vehicle (4). Photo credit: NASA/courtesy of nasaim- ages.org. (See Appendix D for the documentation that this image is in the public domain.) ................................ 16 2.3 Nine DOF dynamic model of parafoil-payload system used by Slegers and Costello (5). (See Appendix D for the documentation of permssion to re- publish this figure from (5).) ......................... 17 viii 2.4 Panel discretization used by Slegers and Costello (5). (See Appendix D for the documentation of permssion to republish this figure from (5).) ..... 18 2.5 Angle of attack α ............................... 19 2.6 Side slip angle β ............................... 20 2.7 Longitudinal static analysis (6). (See Appendix D for the documentation of permssion to reprint this figure from (6).) .................. 25 3.1 Significant points of the model. ........................ 33 3.2 Schematic diagram of the states and reference frames of the model. ..... 35 3.3 Aerodynamic forces .............................. 42 3.4 Modeling control input or parafoil brake deflection ............. 48 3.5 Steady state roll angle ϕ20 for various control inputs ............. 48 3.6 Steady state yaw angle 20 for various control inputs ............ 49 3.7 Steady state off plane tow angle 10 for various control inputs ....... 49 3.8 Parafoil used for testing. (courtesy: Flight Concepts Int’l, Inc. See Ap- pendix D for the documentation of the permission to republish this image) . 50 3.9 Payload dimensions .............................. 51 3.10 Side view of a parafoil payload system for net CG calculation ....... 54 3.11 Steady state values of in-plane tow angle θ1 and pitch angle θ2 ....... 56 3.12 Steady state values of in-plane tow angle θ1 for various symmetric brake inputs ..................................... 57 3.13 Steady state values of pitch angle θ2 for various symmetric brake inputs .. 58 3.14 Inertial X component of the relative vector between point of attachment at ship and the parafoil-payload system ..................... 59 ix 3.15 Inertial Z component of the relative vector between point of attachment at ship and the parafoil-payload system ..................... 59 3.16 Operator-In-Loop simulation setup ...................... 60 4.1 Steady state flight condition for symmetric brake input δs0 = 0:2 and asym- metric brake input δa0 = 0:1 ......................... 70
Load more

Recommended publications
  • Soft Kites—George Webster
    Page 6 The Kiteflier, Issue 102 Soft Kites—George Webster Section 1 years for lifting loads such as timber in isolated The first article I wrote about kites dealt with sites. Jalbert developed it as a response to the Deltas, which were identified as —one of the kites bending of the spars of large kites which affected which have come to us from 1948/63, that their performance. The Kytoon is a snub-nosed amazingly fertile period for kites in America.“ The gas-inflated balloon with two horizontal and two others are sled kites (my second article) and now vertical planes at the rear. The horizontals pro- soft kites (or inflatable kites). I left soft kites un- vide additional lift which helps to reduce a teth- til last largely because I know least about them ered balloon‘s tendency to be blown down in and don‘t fly them all that often. I‘ve never anything above a medium wind. The vertical made one and know far less about the practical fins give directional stability (see Pelham, p87). problems of making and flying large soft kites– It is worth nothing that in 1909 the airship even though I spend several weekends a year —Baby“ which was designed and constructed at near to some of the leading designers, fliers and Farnborough has horizontal fins and a single ver- their kites. tical fin. Overall it was a broadly similar shape although the fins were proportionately smaller. —Soft Kites“ as a kite type are different to deal It used hydrogen to inflate bag and fins–unlike with, compared to say Deltas, as we are consid- the Kytoon‘s single skinned fin.
    [Show full text]
  • Deformation and Aerodynamic Performance of a Ram-Air Wing
    Deformation and Aerodynamic Performance of a Ram-Air Wing Master thesis by Aart de Wachter Graduation committee: Prof.Dr. W.J. Ockels September 30 th , 2008 Ir. L.M.M. Boermans Ir. J. Breukels Delft University of Technology Dr. R. Ruiterkamp Faculty of Aerospace Engineering Copyright Attention is drawn to the fact that copyright of this disseration rests with the author. This copy of the dissertation has been supplied on condition that anyone who consults it is understood to recognise that its copyright rests with its author and that no quotation from this dissertation and no information derived from it may be published without the prior written consent of the author. Please contact [email protected] for written permission to quote or publish any of the contents of this dissertation. Aart de Wachter 2008 v vi Preface Before I wrote the project proposal for my master thesis in November 2007 first I wrote down all the things that I wanted to learn and do before I would leave the University. Then I tried to cast all these things into one project. With a few minor changes and additions the project was accepted. It became a project that was even more exciting than winning 3 rd price in the AIAA aircraft design competition in 2003. Because this is a very multidisciplinairy report it won’t go into all the underlying theory of the treated subjects. But to make reading easier there is a basic introduction into the most important aspects of this report. The reader should at least be familiar with the basics of aerodynamics.
    [Show full text]
  • Powered Paraglider Longitudinal Dynamic Modeling and Experimentation
    POWERED PARAGLIDER LONGITUDINAL DYNAMIC MODELING AND EXPERIMENTATION By COLIN P. GIBSON Bachelor of Science in Mechanical and Aerospace Engineering Oklahoma State University Stillwater, OK 2014 Submitted to the Faculty of the Graduate College of the Oklahoma State University in partial fulfillment of the requirements for the Degree of MASTER OF SCIENCE December, 2016 POWERED PARAGLIDER LONGITUDINAL DYNAMIC MODELING AND EXPERIMENTATION Thesis Approved: Dr. Andrew S. Arena Thesis Adviser Dr. Joseph P. Conner Dr. Jamey D. Jacob ii Name: COLIN P. GIBSON Date of Degree: DECEMBER, 2016 Title of Study: POWERED PARAGLIDER LONGITUDINAL DYNAMIC MODELING AND EXPERIMENTATION Major Field: MECHANICAL AND AEROSPACE ENGINEERING Abstract: Paragliders and similar controllable decelerators provide the benefits of a compact packable parachute with the improved glide performance and steering of a conventional wing, making them ideally suited for precise high offset payload recovery and airdrop missions. This advantage over uncontrollable conventional parachutes sparked interest from Oklahoma State University for implementation into its Atmospheric and Space Threshold Research Oklahoma (ASTRO) program, where payloads often descend into wooded areas. However, due to complications while building a powered paraglider to evaluate the concept, more research into its design parameters was deemed necessary. Focus shifted to an investigation of the effects of these parameters on the flight behavior of a powered system. A longitudinal dynamic model, based on Lagrange’s equation for adaptability when adding free-hanging masses, was developed to evaluate trim conditions and analyze system response. With the simulation, the effects of rigging angle, fuselage weight, center of gravity (cg), and apparent mass were calculated through step thrust input cases.
    [Show full text]
  • Hang Gliding / Paragliding Association of Canada Towing Procedures Manual
    Hang Gliding / Paragliding Association of Canada Towing Procedures Manual v4-preview, Jan. 29, 2005 compiled: 2/10/2009 8:10:19 PM CAUTION This manual lays out procedures, standards and guidelines under which the towing of hang gliders and paragliders in Canada is endorsed by the HPAC/ACVL. The information contained in this manual is a compilation of knowledge from many highly experienced sources, and is intended as a reference for pilots to use as they see fit in the interests of their own safety. A pilot's safety has always and will always be his own responsibility, regardless of the contents of this manual. The authors and contributors have no responsibility or liability for the actions or results of the actions of any person following the guidelines in this manual, since the person is performing those actions of his own free will. Pilots are not bound in any way to follow the guidelines in this manual, decisions involving their safety are always theirs to make, regardless of the wording used in this manual. If a pilot does choose to follow different procedures than those described here in the interests of making his activities safer, the authors would appreciate being apprised of these procedures so that we may improve this manual. Under no circumstances should the reader, or anyone directly or indirectly associated with the reader, use this manual as a sole reference on which to base towing operations of any kind. This manual is not an instructional course, it is a reference and compilation of information intended to be used to increase the safety of this portion of our sport.
    [Show full text]
  • Kite Lines Is the Comprehensive International ...J Journal of Kiting, Uniquely Serving to Unify the ::> Broadest Range of Kiting Interests
    QUARTERLY JOURNAL OF THE WORLDWIDE KITE COMMUNITY BEAUTIFUL MAKE'rHE Is PIN SKYGALLERY: BERCK­ EURO-BALENO! COLLECTING MICHAEL SUR-MER DEAD? GODDARD'S MAKE THE COLOR FOLD BLACK! , ETUDES Put Yourself in the Picture Our Free 80 page Catalog has hundreds of Kites. Get into the sky with the latest kite designs from Into The Wnd, America's leading mail order kite company for 16 years. We specialize in unmatched selection and fast service, and we guarantee your complete satisfaction with everything you buy. Call, write, FAX or e-mail us for your Catalog today. Into the Wind 1408-AG Pearl St., Boulder, CO 80302 . (800) 541-0314 (303) 449-5356 . FAX (303) 449-7315 • [email protected] -you're looking for a line that F[ You're looking for a flyline that is DISTINCTIVELY DIFFERENT. You're looking for a flyline that offers such STUNNING CONTROL that you can positively FEEL THE DIFFERENCE! You're looking for FLY LIKE YOU MEAN IT!TM You'll find competitors flying LaserPro ™ lines at most festivals. Ask them about the LaserPro ™ difference! ••••••••••••• • • • •••• •• RETAIL DEALERS! Get your LaserPro out of the back room and into your prospects' hands with a custom Point-of-Purchase Display, Highlight the convenience of LaserPro ready-to­ fly line sets and let them FEEL THE LASERPRO DIFFERENCE with a nifty line sampler. A great way to get your kite sales soaring! 970-242-3002 http://www.innotex.com FLyTnG CII ~nes o C') ISSN 0192-3439 Printed in U.S.A. o co Copyright © 1996 tEolus Press, Inc Reproduction in any form, in whole or in part, u Is strictly prohibited without prIor written per­ a: mission of the publisher.
    [Show full text]
  • Kitesurfing a - Z
    Kitesurfing A - Z A Airfoil (aerofoil): a wing, kite, or sail used to generate lift or propulsion. Airtime: the amount of time spent in the air while jumping. AOA, Angle of Attack: also known as the angle of incidence (AOI) is the angle with which the kite flies in relation to the wind. Increasing AOA generally gives more lift. AOI, Angle of Incidence: angle which the kite takes compared to the wind direction Apparent wind, AW: The wind felt by the kite or rider as they pass through the air. For instance, if the true wind is blowing North at 10 knots and the kite is moving West at 10 knots, the apparent wind on the kite is NW at about 14 knots. The apparent wind direction shifts towards the direction of travel as speed increases. Aspect Ratio, AR: the ratio of a kites width to height (span to chord). Kites can range between a high aspect ratio of about 5.0 or a low aspect ratio of about 3.0. AR5: The legendary first 4 line inflatable kite manufactured by Naish. ARC: a foil kite manufactured by Peter Lynn B Back Loop: a kitesurfing trick where the kiter rotates backward (begins by turning their back toward the kite) while throwing his/her feet above the level of his/her head. Back Roll: same as a back loop but without getting their feet up high. Batten: a length of carbon or plastic which adds stiffness or shape to the kite or sail. Bear Away / Bear Off: change your direction of travel to a more downwind direction.
    [Show full text]
  • Tandem Document
    Tandem – How it works General Instructions for a Tandem Passenger You will need to follow the instructions of the Tandem Pilot. Do not grab the tow bridle at any time or any of the lines or webbing above your shoulders and head unless the Pilot is guiding you in flight lessons. Make sure you are clear on the instructions for how to transition from the launch position to the flying position and back to landing position for landing. How a Paraglider Launches and Lands: A Paraglider is a parafoil wing which requires acceleration through the air to achieve lift. It launches similar to how a kite is launched. In light winds, Pilots normally do a “Forward Launch”, and in strong winds, pilots do a “Reverse Launch”. In either launch technique, the pilot and passenger accelerate together to reach a good flying speed for take-off. Forward Launch : Forward launches are preferred in very light or no wind conditions. With the wing laid out behind them in a horseshoe shape, the Pilot and Passenger are centered in the wing and facing forward. When the wind is right and the Tandem Pilot decides to launch, both the Pilot and Passenger must run forward together in a coordinated fashion. At first, as the wing climbs overhead, the wing will not allow much forward progress. But, as the wing gets fully overhead, the Pilot and Passenger will be able to accelerate together. They must run efficiently together until the glider is well clear of the ground. Sometimes the wind can gust during the run and then calm slightly causing the Pilot and Passenger to settle back to the ground.
    [Show full text]
  • Stephen E. Hobbs a Quantitative Study of Kite Performance in Natural Wind
    CRANFIELD INSTITUTE OF TECHNOLOGY STEPHEN E. HOBBS A QUANTITATIVE STUDY OF KITE PERFORMANCE IN NATURAL WIND WITH APPLICATION TO KITE ANEMOMETRY Ecological Physics Research Group PhD THESIS CRANFIELD INSTITUTE OF TECHNOLOGY ECOLOGICAL PHYSICS RESEARCH GROUP PhD THESIS Academic Year 1985-86 STEPHEN E. HOBBS A Quantitative Study of Kite Performance in Natural Wind with application to Kite Anemometry Supervisor: Professor G.W. Schaefer April 1986 (Digital version: August 2005) This thesis is submitted in ful¯llment of the requirements for the degree of Doctor of Philosophy °c Cran¯eld University 2005. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright owner. i Abstract Although kites have been around for hundreds of years and put to many uses, there has so far been no systematic study of their performance. This research attempts to ¯ll this need, and considers particularly the performance of kite anemometers. An instrumented kite tether was designed and built to study kite performance. It measures line tension, inclination and azimuth at the ground, :sampling each variable at 5 or 10 Hz. The results are transmitted as a digital code and stored by microcomputer. Accurate anemometers are used simultaneously to measure the wind local to the kite, and the results are stored parallel with the tether data. As a necessary background to the experiments and analysis, existing kite information is collated, and simple models of the kite system are presented, along with a more detailed study of the kiteline and its influence on the kite system. A representative selection of single line kites has been flown from the tether in a variety of wind conditions.
    [Show full text]
  • • 206-547-1100 Why Fly?
    © 2011 Prism Designs Inc. 4214 24th Ave. West, Seattle Washington 98199 [email protected] WWW.PRISMKITES.COM • 206-547-1100 WHY FLY? redefined a pastime for the fanatical few who shared our passion. As the sport grew, so did we, and today Prism is recognized worldwide as the gold standard in kite design and technology. While stunt kites will always remain close to our hearts and provide us with our most Flight is the ultimate escape. There are technical design challenges, these days times when we welcome the pull of gravity we work to bring flight to the more casual anchoring our feet to the earth. But take user as well. Whether you’re looking for a kite in your hands, send it skyward to the perfect single line for a family outing, feel the connection with the wind’s subtle seeking the challenge of ripping up the sky, currents and you become a different or craving the exhilaration and power of person. Stress, deadlines and the work- the wind, we have the kite for you. a-day world melt away, leaving you with peace and perspective you can only find in Prism is dedicated to putting the magic the sky. of flight at your fingertips wherever you go. Pick up a kite and let your spirit soar. Prism was founded in 1992 by a couple of guys who fell in love with the wind. We started off making high-tech, dual-line stunt kites when the sport was young. We brought space age materials such as graphite composites, Spectra and Kevlar to an ancient art - and along the way we 4 WHERE DESIGN TAKES FLIGHT Our passion for flight is matched only by our fascination with the technology that makes it possible.
    [Show full text]
  • Download Alongside Other Britloo Pictures
    Success! BritlOO Special Inside a discussion of the aad’s affect on our sport handy hints from a national champion NORTH POLE ADVENTURE August 99 on your own but not alone Photo: Hans Berggren AIRTEC Mittelstrasse 69 Tel. +49 2953 9899 D-33181 Wunnenberg Fax +49 2953 1293 Do not solely rely upon the CYPRES as a life-saving device. Stay current and practice your emergency procedures. PARA E D IT O R IA L: S T Lesley Gale THE JOURNAL OF THE BRITISH PARACHUTE ASSOCIATION Managing Editor S kyd ive 3 Burton Street Peterborough PE1 5HA Tel/Fax: 01733 755860 E-mail: [email protected] editorial the magazine of www.skydivemag.com This issue we bring you an extra eight pages of your all-singing, all­ ADVERTISING: dancing magazine. The fir s t ever 68 page Mag (just one short!). Jackie Green How can we do this? Our new print/advertising company Warners Warners Group Publications Pic have sold more advertising, this revenue goes to improve quality. O f West Street Bourne, Lines PE10 9PH the usual 60 pages, 8 have been paid fo r as an extra and will always Tel: 01778 393313 be used for editorial (as I promised you at the '98 ASM). Of the Fax: 01778 394748 remaining 52 pages, if the number of ad pages goes over 40% (ie, The British E-mail: [email protected] 21 pages), we will increase the size of the Mag to accommodate Parachute this. This is a great issue to add pages to, see page 28 onwards fo r Design and layout: Association Julie Gray and Trish Jones a special BritlOO report of the new British record achieved at Patron: His Royal Highness CCP Ltd, Brookfield Park The Prince of Wales Lincoln Road Langar during July.
    [Show full text]
  • Preview of “Microsoft Word
    com AdrenalineNation.a state without borders ! ! SNAKE!RIVER!CANYON!JUMP! September!8th,!2014! City!of!Twin!Falls!RFQ!Response!! ! Adrenaline)Nation)is)making)plans)to)jump)over)the)Snake)River)Canyon)on)September) 8th,)2014,)marking)the)40th)anniversary)of)Knievel’s)famous)(or)infamous))attempt.)) With)the)worldwide)interest)in)Evel)Knievel)that)spans)generations,)we)will)be)looking)to) reach)out)to)as)wide)an)audience)as)possible)to)share)in)this)event.) In)order)to)do)accomplish)this)we)have)partnered)with)two)major)production) companies,)Kinetic)Content)out)of)Los)Angeles)and)Nerd)TV)out)of)London.))Both)these) companies)are)part)of)the)Red)Arrow)Entertainment)Group)which)is)owned)by) ProSiebenSat.1)one)of)Germany’s)largest)broadcasters.) We)are)not)trying)to)duplicate)Knievel’s)failed)plan.))Our)approach)is)to)do)the)same) stunt,)only)to)do)it)the)way)Knievel)would)have)done)it)today,)with)more)advanced) rocket)motors)and)technology,)steerable)ramSair)parachutes,)and)advanced)composite) materials.) PO Box 241, Perris, CA 92572 (310) 686-0778 [email protected] www.AdrenalineNation.com October 18, 2013 Page 2 When)Evel)Knievel)undertook)this)project)over)40)years)ago)he)assembled)the)best) engineers)and)technology)available)(and)affordable))at)the)time.))After)realizing)the) technical)and)physiological)problems)with)actually)trying)to)do)the)jump)on)a) motorcycle,)he)hired)Robert)Truax,)one)of)the)best)and)brightest)rocket)designers)of)his) day,)and)built)the)XS2)Skycyle.) A)lot)has)changed)since)1974.))HighSpowered)model)rocketeers)have)access)to)the)same)
    [Show full text]
  • Adaptive Glide Slope Control for Parafoil and Payload Aircraft
    ADAPTIVE GLIDE SLOPE CONTROL FOR PARAFOIL AND PAYLOAD AIRCRAFT A Dissertation Presented to The Academic Faculty by Michael Ward In Partial Fulfillment of the Requirements for the Degree Doctor of Philosophy in the School of Aerospace Engineering Georgia Institute of Technology May 2012 ADAPTIVE GLIDE SLOPE CONTROL FOR PARAFOIL AND PAYLOAD AIRCRAFT Approved by: Dr. Mark Costello, Advisor Dr. Eric Feron School of Aerospace Engineering School of Aerospace Engineering Georgia Institute of Technology Georgia Institute of Technology Dr. Eric Johnson Dr. Nathan Slegers School of Aerospace Engineering Department of Mechanical and Georgia Institute of Technology Aerospace Engineering University of Alabama, Huntsville Mr. Steve Tavan Natick Soldier Research, Development and Engineering Center U.S. Army Date Approved: April 27, 2012 ii ACKNOWLEDGEMENTS I wish to thank Mark Costello for his advice and support for these past 4 years. I would especially like to thank him for funding my paragliding lessons. They were absolutely crucial to the success of this research, I swear. I wish to thank Steven Tavan and the Natick Soldier Research, Development and Engineering Center for supporting this exciting, fascinating, frustrating, and extremely rewarding research. I wish to thank Alek Gavrilovski, my partner for the majority of this research. Without his fabrication and especially his outstanding piloting skills, this research would literally never have gotten off the ground. I would like to thank Keith Bergeron for his practical insight and advice as an expert in extreme landing accuracy. Finally, I would like to thank my parents for their love, support, and interest. iii TABLE OF CONTENTS CHAPTER 1 INTRODUCTION .......................................................................................
    [Show full text]