Rear spar for control surface hinges Styrene foam wing core Balsa spars carry bending load 0.25 in x 0.25 in T.E. Reinforcement Materials Employed: Balsa: Light weight & Strong; Horizontal-Tail Styrene Foam: Easily Workable;True airfoil shape Composites: Fiber Glass Pods and hollow Carbon Fiber Booms Assumptions: Load Carrying ability. Structures

Mathematical Model Assumptions: Wing and Weight loading Method of Analysis (Theoretical Model) Safety Factor = 2.5g x 1.5 Wing P Boom Horizontal Tail

Bending Moments Max Moment = lbf/ft

Stress in the Wing Sigma max = 2003 psi Sigma critical = 1725 psi (Actual Test Result; Whiskey Tango Team, Spring 1999) Reasons:  Light Weight Structure (not Bulky)  Safety Factor (worst case scenario)  Wing Test Results 1.5ft P

Horizontal Tail & Boom Horizontal Tail: Max Stress = 850psi Spar Sizes = 1/8 in x 1/16in Booms: Max deflection = 0.24 in SF = 2.5g’s x 1.5 Assuming Young Modulus (E) for a Carbon Epoxy matrix. Testing needed to verify result.

Moment Equations Wing: Horizontal Tail: Boom:

Deflection Equations Wing: Horizontal Tail: Boom:

Deflection of Wing

Moment & Deflection of Horizontal Tail

Moment & Deflection of Boom

Structural Materials: Wing Balsa Light weight/very strong in compression and tension with the grain Density = 11lb/ft 3 E= 625 ksi Yield Stress = 1725 psi Styrene Foam Easily worked with hotwire or cutting tools Gives true airfoil shape Works well in compression when load is well distributed-serves as shear member Not strong enough for bending loads Density = 1.42 lb/ft 3

Fiberglass Good for complex shapes Strong Skills needed 3 layers of 1.5 oz cloth with resin = 9 oz/sq. yd. Carbon Fiber Booms Light weight & Strong Structural Materials: Fuselage and Pods

Geometry and Configuration Wing: Sref = 13.5 sq.ft. Span = 11 ft. Aspect Ratio = 9 Taper Ratio = 0.6 tip section Airfoil: S1220 Horizontal Stabilizer: Area = 2.1 sq ft. Span = 3.0 ft. Vertical Stabilizer: Total Area: 2.0 sq.ft. 11.1’ 5.8’ Boiler Xpress