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

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.

6. Risk Assessment ID Risk Item Effect Importance Action to Minimize Risk 1 Flight Test Failure Team fails to meet project deliverable9 Design aircraft and associated tests correctly. Study weather for optimal test conditions 2 Meeting Project Deadlines Project will run behind schedule, or project deliverables are not met6 Create proper schedules with an appropriate buffer time between dependent actions 3 Component Redesign Forced project redesign can force the project to run over deadlines3 Smart aircraft design with proper backing analysis. Compliance with subsystem interface designs. 4 H1N1/Illness Team members can fall behind in work3 Proper cleanliness and Hygiene

7. Risk Assessment ID Risk Item Effect Importance Action to Minimize Risk 5 Build Time Runs Over Delay in meeting project deliverable, flight testing does not run on schedule4 Begin build phase early and maintain positive team morale 6 Component Testing Failure Delay in project deliverable or testing schedule2 Test parts early and properly design all critical systems 7 Miscellaneous Damages/Theft Loss of progress and time3 Ensure all parts are properly stored and secured 8 Budget Increase Needed Unable to purchase critical parts needed for aircraft design and build2 Have budget clearly defined and avoid expensive components where possible 9 Budget Driven Redesign Team will have to redesign aircraft systems, increasing time needed for completion3 Have budget clearly defined and avoid expensive components where possible

8. Risk Assessment ID Risk Item Effect Importance Action to Minimize Risk 10 Part Lead Time Parts required for assembly delay build progress2 Order parts at the end of MSDI and make sure all parts are ordered 11 Team Member Injury Team member can fall behind in work resulting in a progress delay2 Every team member acts in a responsible manner ensure work is done in a timely manner 12 Critical Data Loss Component re-design or analysis will need to be repeated2 All documents are backed up on EDGE 13 Winter Break Start Up Ramp up time for project build is longer due to winter break2 Continue work and project updates during the winter quarter

9. Control Interfaces (physical)

10. Control Interfaces (electrical)

11. 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.

12. 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

13. 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

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

15. Airframe Selection Matrix MonoplaneBi-planeDelta Flying Wing Tandem Wing Split Body Boom Tail Design 0--- - Cost (initial) 0-0+- + Piloting Difficulty 0-- +0 Transport 0+----+ Flight Time 000++++0 Payload Flexibility 00-- ++-- Payload Weight 000++++0 Airspeed 0-+-0-0 Total 0-3 -4-2-3

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

17. Airframe Tail Selection Matrix CamberedH-TailV-TailT-TailCruciform Stability0++-- Design Difficulty0--- Weight0-+-- Controllability0+-++ Drag0++00 Flight Envelope000++ Cost0---- Total00-3

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

19. 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./ft 2.  The wing shall be structurally sound.  The wing shall resist deformation under loading.

20. Airfoil Selection Matrix High Camber- Flat Bottom High Camber - Under Cambered Low CamberReflexSymmetric Lift0+-- Drag0++-- Stall Angle0+--0 Stall Speed0+--0 Moment0-++++ Structure0-000 Total02-2-3-2

21. 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

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

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

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

25. General Comparison S7055 (10.5%) Flat- BottomedNACA-9412 Thickness (%)10.511.979 Camber (%)3.5488.998 Trailing Edge Angle (%)10.87613.718 Lower Surface Flatness91.6338.129 Leading Edge Radius (%)1.3791.671 Maximum Lift (CL)1.2032.096 Maximum Lift Angle-of-Attack (deg)912.5 Maximum Lift-to-drag (L/D)52.64658.659 Lift at Maximum Lift-to-drag0.9421.412 Angle-of-Attack for Maximum Lift-to-drag (L/D)5.53.5 Stall Angle9.012.5 Data from the Airfoil Investigation Database

26. 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

27. 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

28. 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.

29. 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

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

31. Landing Gear Selection Matrix Conventional Tricycle Skid Plates Pontoon/Floats Skis Drag0++- 0 Ground Control00- -0 Nose Over0++-00 Ground Loop0+-00 Cost0-++- Load Handling0-++0 Risk of Prop Damage0---0 Cargo Protection0-- 00 Operational Environment Restrictions00-- Total00-5-4-3

32. 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.

33. Flight Control Actuation Selection Electric (servo) Electric (stepper)PneumaticHydraulicEHA Difficulty of Design0----- Complexity0---- Quick Connect compatible00-- 0 Weight0----0 Power output00+++ Maintenance00--- Cost (initial)0-0--- Cost (sustained)0-0-- Total0-6-5-7-6

34. 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.

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

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

37. 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.

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

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

40. Gas Critical Analysis

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

42. Propulsion Selection Matrix Glow/NitroGasolineElectric Initial Cost*00 Running Cost00+ Controllability00+ Power*0- Weight00- Design Flexibility00++ Fuel/Battery Consumption 000 20 min Flight Time*00 Vibration00+ Reliability-0++ Maintenance00++ TotalN/A05 *Glow engines of the size required would need to be a custom made part, as such they are not available for our use

43. 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

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