Team 3 Structures and Weights PDR 2 Presented by: Stacie Pedersen Jason Hargraves Lazo Trkulja

Overview Landing Gear Weights Model Wing Structure Wing Load Analysis Fuselage and Tail Structure

Landing Gear Analysis Layout according to Raymer Lateral tip-over at 30° Longitudinal tip-over at 15° 19.4 in 9.6 in b/2=27.8 in. 46.8 in

Landing Gear Layout b=55.6 in L=46.8 in Wingtip strike at 17° bank Tail strike negligible ---exceeds 15° tip-over Approx. 1.5 in propeller ground clearance CG

Weights Model Current Take-off Weight  1.92 lbs Airframe Weight Breakdown Wing  0.54 lbs Canard  0.09 lbs Vertical Stabilizer 0.063 lbs Fuselage  0.22 lbs

Weights Cont. CG Moments of inertia

Summary Weights Breakdown Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Airframe 0.92 -0.17 -0.15 Propulsion 0.55 -2.14 -1.18 Avionics 0.28 -0.32 -0.09 Landing Gear 0.11 -1.13 -0.12 Miscellaneous 0.06 -0.63 -0.04 TOTAL 1.92 -0.85 -1.64 Origin at wing root c/4 Nose-up moments are positive

Airframe Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Wing 0.53 0.24 0.13 Canard 0.10 -1.80 -0.19 Vertical Stabilizer 0.06 0.54 0.03 Fuselage 0.22 -0.58 -0.13 AIRFRAME 0.92 -0.17 -0.15

Propulsion Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Battery 0.086 -1.17 -0.10 ESC 0.026 -1.42 -0.04 Motor 0.163 -2.21 -0.36 Gearbox 0.156 -2.43 -0.38 Propeller 0.120 -2.53 -0.30 PROPULSION 0.551 -2.14 -1.18

Avionics Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Receiver 0.094 -0.84 -0.08 Gyro 0.031 -0.92 -0.03 Ruder Servo 0.020 0.35 0.01 Elevator Servo -1.94 Flaperon Servos 0.040 0.00 Gear Servo 0.077 AVIONICS 0.282 -0.32 -0.09

Landing Gear Weights Weight (lbs.) Arm (ft.) Moment (ft.-lbs.) Main Gear 0.056 -0.73 -0.04 Main Wheels 0.004 0.00 Nose Gear 0.044 -1.82 -0.08 Nose Wheel 0.002 LANDING GEAR 0.106 -1.13 -0.12

Wing Structure Balsa Skin (wing covering) Blue Foam Leading Edge Balsa Spar Balsa Control Surface Attachment Spar Balsa Skin (wing covering) Blue Foam

Wing Root Structural Dimensions 0.97 ft 0.194 ft 0.04 ft Trailing Edge Spar Thickness  3/16 in Balsa

Wing Structure

Wing Load Distribution Assume Elliptical Loading: e=1 USNPS-4

Bending Equations To find max allowable tensile & compressive bending moments Modeled as beam with no taper To find moments and deflections

Bending Results

Bending Results Max Allowable Tensile Moment  31.83 lbf-ft Max Allowable Compressive Moment  88.05 lbf-ft Max Bending Moment in Loiter  9.18 lbf-ft Max Bending Moment in Turning Flight 9.73 lbf-ft

V-n Diagram

Torsion Equations and Assumptions Torque Resultant Chord Equation T = -0.993 ft-lbs.

Failure, Deflection and Inertias Failure occurs at 2.25 Gs Excludes reinforcement from fillets Will demonstrate 2.0 Gs prior to flight Max tip deflection  0.04 ft Ixx = 2.50 lb-ft2 Iyy = 1.08 lb-ft2 Izz = 1.74 lb-ft2

Fuselage Structure Foam Panels Hollow Inner Balsa Box

Wing & Canard Attachment to Fuselage Wing will attach to the bottom of the fuselage via a foam saddle piece between the wing and the inner fuselage box Canard will attach to the fuselage similar to the wing

Vertical Tail Construction 0.80 ft 0.30 ft 0.76 ft Vertical tail will attach to the fuselage using tri-stock on each side of base

Questions