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System Design Review P10232 – UAV Airframe C

Daniel Graves – Project Lead James Reepmeyer – Lead Engineer Brian Smaszcz – Airframe Design Alex Funiciello – Airfoil Design Michael Hardbarger – Control Systems. System Design Review P10232 – UAV Airframe C. Project Definition. Mission Statement:

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System Design Review P10232 – UAV Airframe C

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  1. Daniel Graves – Project Lead James Reepmeyer – Lead Engineer Brian Smaszcz – Airframe Design Alex Funiciello – Airfoil Design Michael Hardbarger – Control Systems System Design ReviewP10232 – UAV Airframe C

  2. Project Definition Mission Statement: The goal of the UAV Airframe C project is to provide an unmanned aerial platform used for an aerial imaging system. The airframe must support the weight and interfaces for the designed imaging system. The aircraft must be operated remotely and be a viable alternative to current aerial imaging methods. This is a second generation airframe, expanding on the previously laid ground work established by the P09232 UAV B Senior Design Project.

  3. Customer Needs Key Project Goals: • Airframe must be able to carry a fifteen pound payload • Easy integration with measurement controls box and different aerial imaging systems • Ability to remotely control aircraft and activate payload • Ability for flight communication between aircraft and ground relay • Aircraft provides twenty minutes of flight time for local area photography • Aircraft has the potential to take off and land on site • Easy assembly and disassembly of the aircraft for transportation

  4. Lessons Learned From P09232 • The aircraft’s wings sheared off shortly before impact. The failure was determined to be from the bending stress applied to the wings during the banked turned. • After analysis, it was concluded that the main fiberglass spar used to support the wing was not selected properly to handle the flight loading. • High bend in the wing during flight inhibited the pilot’s control of the aircraft by reducing the effectiveness of the control surfaces.

  5. Risk Assessment

  6. Risk Assessment

  7. Risk Assessment

  8. Control Interfaces (physical)

  9. Control Interfaces (electrical)

  10. Body Structure • The structure shall support 15lbs of payload. • The structure shall have an accessible payload bay. • The structure shall assemble/ disassemble for transport. • The structure shall resist deformation under normal operation. • The structure shall house the planes power system and provide a mount for the engine. • The structure shall be durable, enabling multiple flights without servicing.

  11. Airframe Concept Goals • Reduce weight of airframe compared to UAV B • Improve aerodynamics • Improve in-flight stability and handling properties • Optimize payload integration and removal • Design airframe to highest “open architecture” capability http://mae.ucdavis.edu/~EAE127/index_files/1008033.jpg

  12. Airframe Concept Selection • Standard monoplane design. • Top mounting wing capability. • Detachable conventional tail section. • Configuration used in small aircraft and RC trainer planes. • Simple design allows for shorter build time. http://www.hooked-on-rc-airplanes.com/images/rc-trainer-planes6.jpg http://www.excelaviation.ca/index_files/image004.jpg

  13. Airframe Fuselage Concepts • Twin-boom • Tandem wing • Canard Style • Flying wing • Delta wing http://www.spyflight.co.uk/images/ http://upload.wikimedia.org/wikipedia/commons/4/4a/YB49-2_300.jpg www.viswiki.com/en/Tandem_wing http://commons.wikimedia.org/wiki/File:Vulcan.delta.arp.jpg http://advancedaerospacellc.com/jcfly%2015%25.jpg

  14. Airframe Selection Matrix

  15. Airframe Tail Concepts • Cruciform • Twin-Tail • V-Tail • Conventional • T-Tail http://en.wikipedia.org/wiki/File:Jetstream31.jpg http://www.flightdesignusa.com/ http://media.photobucket.com/ http://www.aviationspectator.com/ http://farm2.static.flickr.com

  16. Airframe Tail Selection Matrix

  17. Tail Airfoil Selection • Lifting tail will be used to counter wing moment • A low cambered foil will be used to minimize drag

  18. Airfoil Specifications • The airfoil shall provide enough lift to carry the craft. • The airfoil shall minimize drag. • The wing shall be able to be disassembled. • The wing shall be structurally rigid and free of in flight flutter. • The wing shall contain control surfaces. • The wing planform area shall be designed such that wing loading is kept under 20 oz./ft2. • The wing shall be structurally sound. • The wing shall resist deformation under loading.

  19. Airfoil Selection Matrix

  20. Airfoil Concept Selection • Add additional camber compared to last year • flat bottom under camber design • Increase lift • Decreases stall speed • Decrease required chord and wingspan

  21. Flat bottom v. Under Camber S7055 NACA-9412 Airfoil coordinates from UIUC airfoil database

  22. Airfoil Lift comparison Comparison from the Airfoil Investigation Database, with data taken from the UIUC airfoil database

  23. Airfoil Drag Comparison Comparison from the Airfoil Investigation Database, with data taken from the UIUC airfoil database

  24. General Comparison Data from the Airfoil Investigation Database

  25. Airfoil selection • Final selection of the airfoil will be based on XFOIL analysis • Using refined weight estimates, a specific lift requirement may be chosen • Planform area will be selected based on desired wing loading to maintain trainer like flight behaviors • Power restrictions of the selected motor will mandate the specific drag requirements

  26. Launch and Recovery Concept Selection • Catapult (or crossbow) style launch platform • Car-top launch setup • Removable (leave-behind) Landing Gear • Retractable landing gear http://mm04.nasaimages.org/MediaManager/srvr?mediafile=/Size4/nasaNAS-9-NA/59991/0100743.jpg&userid=1&username=admin&resolution=4&servertype=JVA&cid=9&iid=nasaNAS&vcid=NA&usergroup=Marshall_-_nasa-9-Admin&profileid=41 http://www.uavs.biz/images/catapult_launch.jpg

  27. Landing gear • The landing gear shall allow the plane to taxi and takeoff. • The landing gear shall protect the plane during takeoff, landing, and taxiing. • The landing gear shall provide minimal resistance on a grass runway.

  28. Landing Gear • Skids or Skis • Floats (Pontoons) • 2 or fewer wheels (combination of wheels and skids) • 3 wheels (traditional setup) • More than 3 wheels http://www.oursbiz.com/Products/b/195/Pitts-S-2A-SP-002--987230.jpg http://anjo.com/rc/aircraft/dr1/dr1.gear.1.jpg

  29. Landing Gear Layout http://www.jacksonrcclub.org/images/landing_gear_types.jpg

  30. Landing Gear Selection Matrix

  31. Flight controls • The flight control system shall allow the aircraft to be flown like a basic trainer aircraft. • The control system shall maintain reliable control for at least 20 min. • The control system shall interface with the payload.

  32. Flight Control Actuation Selection

  33. Propulsion • The propulsion system shall provide power for at least 20 min. • The propulsion system shall provide enough thrust to accelerate to flight speed. • The propulsion system shall be clean and easy to maintain. • The propulsion system shall be reusable.

  34. Propulsion Concept Selection RC Airplanes Rely on 1 of 3 Types of Propulsion • Gas • Glow/Nitro • Electric

  35. Gas Propulsion • Small Gasoline Powered Engine • Typically Two-Cycle • Traditional RC Aircraft Propulsion Method • Longer Flight Time with Gas RC Planes

  36. Glow/Nitro (?) • Fuel: Nitrous Oxide (?) • Will not be considered for this project due to fact that it is not manufactured in sizes not large enough for the scope of this project.

  37. Electric • Uses Batteries to Power Motor • Brushed DC • Brushless DC • Due to Need for Batteries it has a Short Flight Time

  38. Battery Capacity • To find the required battery capacity to operate each motor for 20 minutes the following equation was used:

  39. Gas Critical Analysis

  40. Electric Critical Analysis • All Motors Analyzed Were DC Brushless • Two Different Typical Li-Po Battery Packs Were Used

  41. Propulsion Selection Matrix *Glow engines of the size required would need to be a custom made part, as such they are not available for our use

  42. P10232 System Design Concept • Monoplane • Electric propulsion? • Standard cambered tail section • Under-cambered airfoil • Rectangular wing section • Top-mounted wing to the airframe • Conventional landing gear

  43. Questions? • P10232 Team • Daniel Graves • James Reepmeyer • Brian Smaszcz • Alex Funiciello • Michael Hardbarger https://edge.rit.edu/content/P10232/public/Home

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