Pitch Divergence Suppression of a Subscale Wing in Ground Effect WIG Aircraft

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What is a WIG Aircraft?. A flying machine which flies over a for the most part level surface at a stature lower than half of the compass to utilize worthwhile ground impact conditions. Focal points of WIG Aircraft. Harmony Dominated

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Pitch Divergence Suppression of a Subscale Wing in Ground Effect (WIG) Aircraft 56 th Annual AIAA Southeastern Regional Student Conference April 4-5, 2005 Robert Love Auburn University

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What is a WIG Aircraft? A flying machine which flies over a generally level surface at a stature lower than half of the traverse to utilize favorable ground impact conditions

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Advantages of WIG Aircraft Chord Dominated "Slam" impact builds Lift Span Dominated Reduction of wing tip vortices drastically brings down prompted drag Therefore high L/D proportions

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History of WIG Aircraft Designs are to a great degree differed Early Designs U. S. "Spruce Goose" Russian "Erkanoplans" The KM, Lun and Orlyronk in the (1960's) PAR engines, strait wing Amphistar The Lippisch Design, single engine Airfisch 3 L-325 Flarecraft

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What is being done at this point? Australia FS-8 (with Singapore) Incat Wing (trimaran with WIG bolster) China TY-1 XTW-4 United States Boeing Pelican Aerocon Atlantis 1 Germany Hoverwing X-114

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Introduction Divergence because of ground impact is outstanding in different fields Longitudinal Stability a noteworthy issue for WIG flying machine Sudden pitch and stature changes cause uniqueness Contributors High push line, throttle cut too rapidly, absence of intrinsic solidness, wrong CG, gradualness/powerlessness to react to pitching movements Caused loss of numerous flying machine, notoriety as untrustworthy

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Previous Approaches Structural Fixes Large Tail Wing, Canards, braces, lifts, the Lippisch outline of the wing, S-molded airfoils Disadvantages incorporate a lot of drag and little adequacy Tweaking Dynamic Characteristics Movement of the focal point of pitch, focus of gravity, and streamlined focus Some achievement, however reliant on watchful adjusting

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The Aircraft Model Based off of Graham Taylor's MK5 WizzyWIG XGE arranges Materials Used Balsa wood Carbon fiber engine mounts Bonding with Cyano-Acrylate Resin and Hysol 9433 Covered with model cleaning material and blazing tape Hardware 3 Astro 020 Direct Drive Brushless engines 3 Lithium Polymer Batteries 2 servos, 1 JR DS368 and 1 Futaba FP-S-14B 1 Cirrius micropiezo MPG-10 whirligig Overall Size 2.5 lbs, 3.5 ft long, 11.5 in high, CG at 1/3 rd of harmony Main wing 17.5 in traverse by 17 in harmony

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The Aircraft Model Notable Features PAR engine mount to fill in as a lift (- 5° to 40°) Canard wing Large tail wing Upward slant of body in front and back Flat principle wing with sponsons Center of Gravity Location and association with apparatus at this area

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Experimental Procedure First sans flight on January 27, 2005 experienced dissimilarity at low speed Whirl test fix made to test the longitudinal dependability of the air ship in a steady situation Test settings With and without augmented pick up pitch rate input adjustment Full and Half Elevator Deflection Throttle setting at 2.5, 3, and 4 of 6 Digital Video broke down with ImagePro Analysis programming speed, disparity times, and body pitch dispositions

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Results Effect of Rate Stabilization on Divergence Times for Full Elevator Deflection

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Results Divergence counteractive action by pitch rate criticism framework for speed of 29.7 ft/s without gyrator and 33.0 ft/s with spinner, at throttle 3 settings

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Results Overall View of the Effectiveness of the Pitch Divergence Suppression at Half Elevator with Pitch Rate Feedback System

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Summary of Results Longitudinal flimsiness for full lift Divergence was not preventable through pitch rate adjustment with a whirligig Longitudinal precariousness for half lift Suppressed at rates lower than 26 ft/s showed by difference taking three circumstances longer than without adjustment Prevented totally at velocities higher than 30 ft/s through pitch rate adjustment

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Significance Increased push accessible to defeat "bump drag" because of higher passable lift settings Increased strength for transitioning between modes Increased mobility to maintain a strategic distance from obstructions Increased response time for pilot or control framework to avert difference as it happens Increased "pitch firmness" of air ship without considerable drag punishments from substantial tail or canard wings Increased wellbeing edge Simplified plan while giving an answer for issue

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Conclusion Divergence of a subscale wing in ground impact flying machine could be stifled or anticipated utilizing a pitch rate criticism framework at paces from 20 ft/s to 45 ft/s for a lift unsettling influence which ordinarily would bring about dissimilarity.

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Thanks To Auburn University and Dr. Ron Barrett for support and specialized counsel To Christoph Burger and Adam Chesler for lab cause and development exhortation To Graham Taylor for the WIZZYWIG arrangements and specialized guidance To the various workers of the Adaptive Aerostructures Lab for their periodic assistance and consolation

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References 1. On the web. "Uniqueness". 2005. April 1, 2005. http://www.hypercraft-partners/disparity/divergence.htm. 2. On the web. The Wig Page. "Wing in Ground Effect Aerodynamics." 2005. February 14, 2005. http://www.se-technology.com/wig/index.php. 3. On the web. "Wing in Ground Effect Aerodynamics." 2005. Walk 18, 2005. http://www.aerospaceweb.org/address/streamlined features/q0130.shtml. 4. On the web. 2005. Walk 18, 2005. http://foxxaero.homestead.com/indrad_044.html. 5. Taylor, G. K., "Would you say you are feeling the loss of the vessel? The Ekranoplan in the 21 st Century Its Possibilities and Limitations". February 2002, 18 th Fast Ferry Conference, 2002.

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