Justin DeStories Aircraft Design

Objective/Requirements  The UAV team at Arizona State University is designing, optimizing, and building an autonomous Unmanned Aerial Vehicle (UAV) to compete in a 2010 UAV aerial imaging contest.  The objectives of the contest are: (1) to fly an UAV via autopilot non-stop for minutes in a square search area of 1 square miles, and (2) use onboard/remote human detectors to locate and identify targets marked by colored alphabets  Additional contest rules: (1) fly between 100 and 750 feet above ground, (2) fly over way points (GPS), (3) some targets are along route/some are not, and (4) better performance = higher score Website: mp2010/default.html

Wing Design Flow Chart Brainstorm/ Research Filter using Requirements Chose Conventional Wing Design Research Various Airfoil Profiles Chose Clark-Y Airfoil Calculated a Preliminary Weight Budget Calculated Wing Size Using Wing Loading Chose Wing Sweep, Wing Taper Ratio and Dihedral Angle Completed Simplified Structural Analysis to Determine Materials and Rib Spacing Acknowledged and Took Into Consideration Self- Imposed Design Constraints Completed CAD Model of Wing Completed Wing Construction Phase

Wing Design Analysis (cont)  Relatively good at floating.  But not as fast due to the thicker airfoil (11.7%).  Is flat on the lower surface from 30% of the chord back.  It gives reasonable overall performance in respect of its lift to drag ratio.  Has gentle stall characteristics.

Preliminary Weight Budget  Researched Weights of components that were going to be used for building operating the aircraft. ItemTotal Oz. 1"x55" "x55" /8"x84" /4"x104" /8"x144"23.28 Wing Bolts /8x4x36" /4"x1/4"x25" /8"x1/2"x27.375"1.27 3/32"x4"x15" /8"x1/4"x36" "x1/2"x28.5"1.235 ElectronicsReceiver1.34 Servos5.08 Paparrazi w/ IRH,IRV1.31 Aircraft Flight Pack6.5 Power PlantHacker A80-10 Motor51.2 Masterspin Spin-Control9.5 Batteries (Lipo) AccessoriesStructure16.8 Monokote15 Video Camera6.5 Gimbal Setup5 Battery for Electronics6.5 Landing Gear20 Tail Wheel Assembly6.5 Main Wheel14 Wing Struts12 Propeller9 Misc Fasteners/Glue5 Total Weight (lbs)24.5

Wing Design Analysis  From research, choose Wing Loading and used it to determine the initial size of the aircraft.  For ease of construction and stability considerations the Wing Loading for our aircraft is

Wing Design Analysis (cont)  From Wing Loading and Chord length, all other wing parameters were calculated  Wing Planform Area (S)  Wing Span (b)  Aspect Ratio

Wing Design Considerations  Ease of Construction  Ease of Maintenance  Transportability 3 Separate Wing Sections 1 2 3

Wing Construction

Fuselage Design and Fabrication  Designed for ample room of equipment.  Batteries  Autopilot System  Flight Pack/Reciever  Antennas  Mini Computer (future)

Next Up  Ground/flight testing  Testing of the Autopilot  Camera Gimbal Setup Any Question?