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

2. 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

3. 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

4. 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

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

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

7. Internal Aircraft Structure

8. Quick Look at Gear

9. Questions?