Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok Structures Preliminary Design Review #1 October 12, 2000

Basic Layout of Wing Spar -located at the 1/4 chord Sparcaps -spruce -1/8” x 1/8” x 6.6’ Shearweb -balsa -1.5” x 1/16” x 6.6’ Ribs -balsa -spaced every 3 inches from tip -include lightening holes Added balsa at leading and trailing edge

Geometric Layout of rib Typical rib section

Geometric Layout of Wing -Stringers -None at this time -Many model planes do not have them -Would add weight -Wing covering- Monokote -Helps with twisting -Forms the skin

Geometric Layout of Wing Sample of strut layout from NACA report 143

Code Code run using preliminary size of aircraft, load factor, and a chosen spar size -Wing loading -Schrenk’s approximation (Raymer) -Shear force -Moment -Find centroids -Moments of inertia -Normal stress

WING LOADING Trapezoidal approximation Elliptical approximation

SHEAR FORCE

MOMENT

Normal STRESS

Material Properties Table taken from Spring ’99 AAE 451 report (Team WTA)

Further Testing -Test maximum shear stress of balsa using three point load test -Torsional test of wing with and without monokote

Structure -Fuselage - balsa -Tapered box -Modeled as truss structure -Sheet on floor to hold equipment -Horizontal/Vertical tail – balsa -Modeled as a flat plate -May have to add a spruce spar due to the size of tail

Landing Gear -Tail dragger configuration -Front wheels placed in front of center of gravity and to ensure propeller clearance -Spaced horizontally to avoid lateral tip over

Center of Gravity Estimate -Center of Gravity -Within 5-10% static margin in front of aerodynamic center -Moment Balance -Find the weight and moment arm of every component

Questions?