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 20-40 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: http://pma263webdev.bowheadsupport.com/studentcomp2010/default.html

Wing Design Flow Chart

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.

  Item Total Oz.  1"x55"  14.32  1"x55"  14.32  7/8"x84"  19.083  3/4"x104"  19.682  5/8"x144"  23.28  Wing Bolts 0.071  1/8x4x36" 1.128  1/4"x1/4"x25" 0.141  3/8"x1/2"x27.375" 1.27  3/32"x4"x15" 0.282  3/8"x1/4"x36" 0.353  1.375"x1/2"x28.5" 1.235Electronics Receiver 1.34  Servos 5.08  Paparrazi w/ IRH,IRV 1.31  Aircraft Flight Pack 6.5

Power Plant Hacker A80-10 Motor 51.2

  Masterspin Spin-Control 9.5

  Batteries (Lipo) 105.84

Accessories Structure 16.8

  Monokote 15

  Video Camera 6.5

  Gimbal Setup 5

  Battery for Electronics 6.5

  Landing Gear 20

  Tail Wheel Assembly 6.5

  Main Wheel 14

  Wing Struts 12

  Propeller 9

  Misc Fasteners/Glue 5

  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?