Over view Landing Gear Landing Gear Weight Determination Weight Determination Geometric Layout of Wing Structure Geometric Layout of Wing Structure Analysis of Wing Loads Analysis of Wing Loads Fuselage and Tail Structure Fuselage and Tail Structure

Landing Gear Front Landing Gear Front Landing Gear Material: carbon fiber Material: carbon fiber 8" wide, 5" tall,1-5/8" wide at top, 1" at bottom, 1.5 oz. weight. 8" wide, 5" tall,1-5/8" wide at top, 1" at bottom, 1.5 oz. weight. Main Wheel Main Wheel Diameter: 2-1/16" Diameter: 2-1/16" Steerable Tail Landing Gear Steerable Tail Landing Gear 2-3/4" x 3" with 7/8" Plain Wheel 2-3/4" x 3" with 7/8" Plain Wheel

Landing Gear Analysis Assumptions: Assumptions: 1. Main Landing Wheels support 90% of weights. 2. Taildragger aft tires are about a quarter to a third the size of the main tires. Tire sizing: Tire sizing: Diameter : 1.96 in Diameter : 1.96 in Width: 0.9 in Width: 0.9 in

Location of Landing Gears

Tip-over Analysis Logitudinal tip-over analysis Logitudinal tip-over analysis α & β should be between 16 to 25 degrees. γ should be between 10 to 15 degrees Lateral tip over analysis. θ should be bigger than 25 degrees. αβαβ γ θ

Weight Determination Center of gravity Center of gravity Center of gravityMoment of inertia (results from CATIA) Gx (in) Gy (in) Gz (in) Ix (slug*ft^2) IyIzIxyIxzIyz e e x Y

List of Components componentmaterialweight (lb) internal bodybalsawood + foam main wingfoam + fiber glass vertical wingfoam + fiber glass horizontal stabilizerfoam + fiber glass fuselagefoam wing Mountbalsawood + foam nose capfiber glass motor (w/ gear box) gyro servo (rudder,elevator,flaperon) receiver speed control battery landing gear payload total(including battery payload) (excluding battery and payload) Total Weight: lb (excluding control wire, hinge and glue)

Layout of Components Motor Battery Payload Speed controller Gyro Receiver Servos (Rudder Elevator)

Material Properties of Wing Structure Material Properties E-Glass Density (lb/in^3) Tensile Strength (psi) Tensile Modulus (Psi) Elongation to break (%) Epoxy Tensile Strength (Psi) % Elongation Flexural Strength (Psi) Flexural Modulus (Psi) Short Beam Shear (Psi) Density (lb/in^3) Balsa wood Density (lb/in^3) Modules of rupture (Psi) 3140 maximum shearing strength (Psi) 300 Compression Strength (Psi) 1890  Density of Composite  50% Epoxy + 50% E-Glass  Density of Balsa wood  (lb/in^3)  Density of foam  (lb/in^3)

Skin & Material  GRP (Glass Reinforced plastic) wing covering (fiber glass w/ epoxy) 3oz E Glass Satin Weave Thickness: “ (Two layer ’’) Epoxy hardener (205(fast) +206(slow)) Epoxy Resin (105)

Wing Assembly Wing Mount Wing Mount + Foam wing Complete wing assembly with fiberglass cover

Wing Geometry

V-n Diagram Positive Stall Limit Negative Stall Limit Positive Structural Limit Negative Structural Limit q Limit

Load (lbf) 5.00 Moment arm (ft) 1.11 Moment (lbf *ft) 5.55 Maximum bending loads

Bending Moment Study

Wing Tip Vertical Deflection Vertical deflection of wing tip 0.21 (in)

Twist angle = 1(degree) (Shear modulus of fiber glass) (Required thickness of fiber glass over the airfoil) (Area at the tip) (Torque)

Skin Materials Trade Study Purpose: To compare weight of skin made of different materials Method: Single cell Thin-walled analysis Result: Fiber glass has lowest weight FoamBalsa WoodFiber Glass Shear Modulus Psi Density lb/ft^3 Required Skin Thickness in Volume ft^3 Mass lb

Fuselage Structure Frame material is wood Fuselage body material (foam) Interior layout Fully loaded fuselage

Tail Wing Structure Tail wing dimensions Tail wing assembly Materials: Wood Foam Fiberglass

Questions ?