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Team 3 Structures and Weights PDR 2
Presented by: Stacie Pedersen Jason Hargraves Lazo Trkulja
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Overview Landing Gear Weights Model Wing Structure Wing Load Analysis
Fuselage and Tail Structure
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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
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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
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Weights Model Current Take-off Weight 1.92 lbs
Airframe Weight Breakdown Wing 0.54 lbs Canard 0.09 lbs Vertical Stabilizer lbs Fuselage 0.22 lbs
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Weights Cont. CG Moments of inertia
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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
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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
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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
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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
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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
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Wing Structure Balsa Skin (wing covering) Blue Foam
Leading Edge Balsa Spar Balsa Control Surface Attachment Spar Balsa Skin (wing covering) Blue Foam
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Wing Root Structural Dimensions
0.97 ft 0.194 ft 0.04 ft Trailing Edge Spar Thickness 3/16 in Balsa
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Wing Structure
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Wing Load Distribution
Assume Elliptical Loading: e=1 USNPS-4
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Bending Equations To find max allowable tensile & compressive bending moments Modeled as beam with no taper To find moments and deflections
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Bending Results
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Bending Results Max Allowable Tensile Moment 31.83 lbf-ft
Max Allowable Compressive Moment lbf-ft Max Bending Moment in Loiter 9.18 lbf-ft Max Bending Moment in Turning Flight 9.73 lbf-ft
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V-n Diagram
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Torsion Equations and Assumptions
Torque Resultant Chord Equation T = ft-lbs.
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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
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Fuselage Structure Foam Panels Hollow Inner Balsa Box
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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
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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
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Questions
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