Over view Landing Gear Landing Gear Weight Determination Weight Determination Geometric Layout of Wing Structure Geometric Layout of Wing Structure Analysis.

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Landing GearLanding Gear Weight DeterminationWeight Determination Geometric Layout of Wing StructureGeometric Layout of Wing Structure Analysis of Wing LoadsAnalysis of Wing Loads Fuselage and Tail StructureFuselage and Tail Structure

Landing GearLanding Gear Front Landing GearFront Landing Gear Material: carbon fiberMaterial: carbon fiber 8" wide, 5" tall,1-5/8" 8" wide, 5" tall,1-5/8"

wide at top, 1" at wide at top, 1" at bottom, 1.5 oz. weight. bottom, 1.5 oz. weight.

Main WheelMain Wheel Diameter: 2-1/16" Diameter: 2-1/16" Steerable Tail Landing Steerable Tail Landing

GearGear 2-3/4" x 3" with 7/8" 2-3/4" x 3" with 7/8"

Plain Plain WheelWheel

Landing Gear AnalysisLanding Gear Analysis

Assumptions: Assumptions:

1.1. Main Landing Wheels support 90% of Main Landing Wheels support 90% of weights.weights.

2.2. Taildragger aft tires are about a Taildragger aft tires are about a quarter to a third the size of the main quarter to a third the size of the main tires. tires.

Tire sizing:Tire sizing:

Diameter : 1.96 inDiameter : 1.96 in

Width: 0.9 inWidth: 0.9 in

0.312 B

0.715 A

Width

0.349 B

1.51 A

Diameter

wheelon theweight W

WAor WD

W

BWmainmain

Location of Landing Location of Landing GearsGears

Tip-over AnalysisTip-over Analysis Logitudinal tip-over analysisLogitudinal 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.

α

β γ

θ

Weight DeterminationWeight Determination Center of gravityCenter of gravity

m

m

dm

xdmx

m

m

dm

zdmz

Center of gravity Moment of inertia (results from CATIA)

Gx (in)Gx (in)Gy Gy (in)(in) Gz (in)Gz (in)

11.8311.83 1.321.32 00

Ix Ix (slug*ft^2(slug*ft^2

)) IyIy IzIz IxyIxy IxzIxz IyzIyz

0.1420.142 0.2320.232 0.0970.097 -0.005-0.005-2.334e--2.334e-

005005-1.996e--1.996e-

005005

11.6582418211.65824182

xY

List of ComponentsList of Componentscomponent material weight (lb)

internal body balsawood + foam 0.1444

main wing foam + fiber glass 1.2750

vertical wing foam + fiber glass 0.0946

horizontal stabilizer foam + fiber glass 0.2214

fuselage foam 0.1935

wing Mount balsawood + foam 0.0181

nose cap fiber glass 0.0773

motor (w/ gear box) 0.8000

gyro 0.0400

servo (rudder,elevator,flaperon) 0.3791

receiver 0.0397

speed control 0.1000

battery 0.5000

landing gear 0.1243

payload 1.0000

total (including battery payload) 5.0074

(excluding battery and payload) 3.5074

Total Weight:

5.0074 lb

(excluding control wire, hinge and glue)

Layout of ComponentsLayout of Components

Motor Battery

Payload

Speed controller

GyroReceiver

Servos

(Rudder

Elevator)

Material Properties of Wing Material Properties of Wing StructureStructure

Material Material PropertiesProperties

E-GlassE-Glass

Density (lb/in^3)Density (lb/in^3) 0.0940.094

Tensile Strength (psi)Tensile Strength (psi)493128.32493128.32

99

Tensile Modulus (Psi)Tensile Modulus (Psi)10500732.10500732.

658658

Elongation to break (%)Elongation to break (%) 4.8004.800

EpoxyEpoxy

Tensile Strength (Psi)Tensile Strength (Psi) 11008.36511008.365

% Elongation% Elongation 6.3006.300

Flexural Strength (Psi)Flexural Strength (Psi) 16708.34816708.348

Flexural Modulus (Psi)Flexural Modulus (Psi)464120.78464120.78

00

Short Beam Shear (Psi)Short Beam Shear (Psi) 8006.0838006.083

Density (lb/in^3)Density (lb/in^3) 0.0419080.041908

Balsa woodBalsa wood

Density (lb/in^3)Density (lb/in^3) 0.0050.005

Modules of rupture (Psi)Modules of rupture (Psi) 31403140

maximum shearing maximum shearing strength (Psi)strength (Psi) 300300

Compression Strength Compression Strength (Psi)(Psi) 18901890

Density of CompositeDensity of Composite 50% Epoxy + 50% E-Glass50% Epoxy + 50% E-Glass

Density of Balsa woodDensity of Balsa wood 0.005 (lb/in^3)0.005 (lb/in^3)

Density of foamDensity of foam 0.0011(lb/in^3)0.0011(lb/in^3)

Skin & MaterialSkin & Material

GRP (Glass Reinforced plastic) wing GRP (Glass Reinforced plastic) wing covering (fiber glass w/ epoxy)covering (fiber glass w/ epoxy)

3oz E Glass Satin WeaveThickness: 0.0046“(Two layer 0.0092’’)

Epoxy hardener (205(fast) +206(slow))

Epoxy Resin (105)

Wing AssemblyWing Assembly

Wing Mount

Wing Mount + Foam wing

Complete wing assembly with fiberglass cover

Wing GeometryWing Geometry

V-n DiagramV-n Diagram

angleBank 60 Assuming

anglebank

cos

12

o

2maxmax

n

VW

SCn L

Positive Stall Limit

Negative Stall Limit

Positive Structural Limit

Negative Structural Limit

q Limit

Load (lbf)Load (lbf) 5.005.00

Moment arm (ft)Moment arm (ft) 1.111.11

Moment (lbf *ft)Moment (lbf *ft) 5.555.55

Maximum bending loads

Bending Moment StudyBending Moment Study

(psi) 210000

glassfiber

ofstrength Tensile

(psi) 34983x

x I

My

Wing Tip Vertical Wing Tip Vertical DeflectionDeflection

Vertical deflection of wing tip

0.21 (in)

EI

Mxx

2)(

2

Twist angle = Twist angle = 1(degree)1(degree)

22.015inA

t

dsq

GA2

1

psieG 61

inlbfT 85.6

(Shear modulus of fiber glass)

(Required thickness of fiber glass

over the airfoil)

t

s

GA

q

2

A

Tq2

intrequired 0112.

(Area at the tip)

(Torque)

Skin Materials Trade Skin Materials Trade StudyStudy

Purpose: To compare weight of skin made of different materials

Method: Single cell Thin-walled analysis

Result: Fiber glass has lowest weight

  Foam Balsa WoodFiber

Glass  

Shear Modulus 550 23600 1000000 Psi

Density 1.87 9.68 117.41 lb/ft^3

Required Skin Thickness

38.8970 0.8209 0.0194 in

Volume13.719

7 0.2895 0.0068 ft^3

Mass25.694

4 2.8017 0.8037 lb

Fuselage StructureFuselage Structure•Frame material is wood

•Fuselage body material (foam)

Interior layout

Fully loaded fuselage

Tail Wing StructureTail Wing Structure• Tail wing dimensions

• Tail wing assembly

Materials:

•Wood

•Foam

•Fiberglass

Questions ?