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Team 5 Structures and Weights QDR #2

Team 5 Structures and Weights QDR #2. Scott Bird Mike Downes Kelby Haase Grant Hile Cyrus Sigari Sarah Umberger Jen Watson. Preview. Walk Around Sizing Criteria Material Selection Wing Box Properties Pod Support. Walk-Around. Data Boom. Pod. Pod Entrance. Engine.

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Team 5 Structures and Weights QDR #2

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  1. Team 5 Structures and Weights QDR #2 • Scott Bird • Mike Downes • Kelby Haase • Grant Hile • Cyrus Sigari • Sarah Umberger • Jen Watson QDR

  2. Preview • Walk Around • Sizing Criteria • Material Selection • Wing Box Properties • Pod Support QDR

  3. Walk-Around Data Boom Pod Pod Entrance Engine Tail Dragging Landing Gear QDR

  4. Wing Box Design Sizing Criteria • Maximum Bending Stress • Iy>=My*z/σxx • θ<1 degree at tip • Deflection at tip <=2in 1/4c Lift c Lift a b QDR

  5. Wing Box Properties Front Spar- Tip Deflection Limiting Criteria Rear Spar- Tip Rotation Limiting Criteria QDR

  6. Final Wing Box Properties Material • Spruce (lowest weight) • Heights defined by airfoil • Front Spar • I-beam • %20 chord • Rear Spar • Rectangle • %60 chord .75in 2.88in 2.25in .125in 1.2in QDR

  7. Performance of Wing Box • Θ=.072 deg • Tip deflection= 1.77 inches • Total Wing Weight= • Front Spar • + Rear Spar • + 15 Ribs • =7.4401 lbs QDR

  8. Pod Support • My=q*L^2/12 • My-maximum bending stress • q=distributed load • (1/2 pod weight) • L=length • Iy>=My*z/σxx q L QDR

  9. Fuselage Layout QDR

  10. Results to come…. • Wing Failure Analysis • Wing Attachment • Boom Sizing • Fuselage Structure Analysis • Tail Structure QDR

  11. Questions? QDR

  12. Material Properties ”Selection and use of Engineering Materials”, J.A. Charles QDR

  13. ”Mechanics of Materials”, James Gere ”Selection and use of Engineering Materials”, J.A. Charles Appendix (References) QDR hf

  14. Span-wise Loading • Assumed Elliptical Loading • Maximum at Root • Max bending at root =245 lbf-ft QDR

  15. Wing Box Properties (Rotation Requirements) • Requirement: θ<1 degree at tip • T=Lift*(distance to shear center) • L=Half span • dis=distance between spars tf hf hr tr b QDR

  16. Wing Tip Deflection for Aluminum QDR

  17. Weight of Wing Structure (half span of front spar) • Weight=density*Cross sectional area*length QDR

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