Structures QDR #2 AAE451 – Team 3 November 13, 2003 Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian

Introduction Analysis of tail beams Internal Structure Layout Explanation of Loads Analysis of Deflection at Tip (end of tail) Internal Structure Layout Landing gear ideas No analysis currently

Rear View of Tail NOTES Torsion can effectively be reduced with appropriate beam spacing Bending can be reduced by increasing moment of inertia of beams (not spacing) Some torsion is inherent, torsion can not be negated as it could in wing Side force from V-stab creates torsion effect on beams Downward force from H-stab creates bending moment on beams

Deflection at Tip (Rear of Tail) Load (lbf) Ref. Gere pg. 892 L (in) Where Load = (lbf) L = Length (in) E = Young’s Modulus (psi) I = Moment of Inertia (in4) Assumptions: Small Deflections Safety Factor = 1.5 G-loading = 5.0 Rectangular Beams Trim conditions (this will change pending control surface sizing) Current Known Values: L = 6.2 ft Load ~ 8 lbf Moment of inertia of rectangular beam: I (in4) = (t)(h3)/12 t and h shown on next slide

Deflection at Tip (Rear of Tail) Green = spruce Black = bass h h=2 in t h=3 in

Deflection at Tip (Rear of Tail) Green = spruce Black = bass h h=2 in t h=3 in Required t ~0.55 in

Internal Aircraft Structure

Quick Look at Gear

Questions?