Vehicle Sizing AAE 451: Team 2 Michael Caldwell Jeff Haddin Asif Hossain James Kobyra John McKinnis Kathleen Mondino Andrew Rodenbeck Jason Tang Joe Taylor Tyler Wilhelm

Revised Design

Modified Mission Objectives 15 minute endurance Take-off distance less than 60 ft Vstall less than 15 ft/s VLoiter less than 25 ft/s Turn radius of 35 ft Tabletop defined as 6 ft x 6 ft

Constraint Diagram Modified MATLAB code from Prof. Andrisani AAE 451

Mean Chord Investigation Assumptions 6 ft span, 2.2 lbs aircraft weight Speeds between 15 and 25 ft/s Trends Airfoil CLmax = 1.5 Airfoil CL loiter = 1.0

Mean Chord Investigation 12 inch mean chord selected

Motor & Propeller Feigao 1208436L Brushless Motor 0.038 lbs 0.472 in. Diameter x 1.22 in. Long $40 Connected by 0.03 lb 9.66:1 Gearbox Slow Flyer Electric Propeller (EP-1147) 0.022 lbs 11 in. diameter $1.88 All available at www.balsapr.com

Batteries Two Worley Lithium Polymer batteries 0.10 lbs total 340mAh each 7.4 V each 1.86 x 1.19 x 0.21 in. $22.99 each

Mission Energy Budget

Tail Sizing From Raymer’s Aircraft Design: A Conceptual Approach Horizontal tail (canard) coefficient = 0.3 Vertical tail coefficient = 0.06 Assume tail control surfaces half the total surface area

Interior Layout CG AC

Stability Analysis Estimation of CG and AC Distance measured from front of aircraft CG = 1.668 ft AC = 1.830 ft Static margin = 16.2%

Aircraft Dimensions Wing Main Fuselage Support Fuselages Wingspan = 72 inches Mean chord = 12 inches Main Fuselage Length = 20 inches Radius = 2 inches Support Fuselages Length = 36 inches Radius = 1 inch

Aerodynamic Surfaces Wing area = 864 in2 Aileron area = 96.77 in2 Total canard area = 172.80 in2 Elevator area = 86.40 in2 Vertical tail area = 339.32 in2 Rudder area = 169.66 in2

Aircraft Weights Estimated to be 85% foam, 15% balsa Weight of structure = 1.80 lbs Weight of batteries = 0.10 lbs Weight of electronic gear = 0.25 lbs Weight of motor & prop = 0.06 lbs Weight of gear box = 0.03 lbs Total weight = 2.24 lbs

Weight Breakdown

Immediate Plans Comparison to historical data Mission specific drag model Airfoil selection Trade studies

Questions?