Team 5Structures PDR

Presented By: Ross MayJames RoeschCharles Stangle

AAE 451 – Team 5March 3, 2005 2

Outline

Landing Gear Weights and CG Wing Geometry Wing Loads Fuselage and Tail Structures

AAE 451 – Team 5March 3, 2005 3

Landing Gear Solid spring main gear

Aluminum struts 1.5 inch diameter wheels 30° angle for lateral stability 20° in front of CG for longitudinal stability

Skid/tail dragger gear Negates propeller and tail strike 5º slope from horizontal for skid 18 gauge steel wire

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Landing Gear

Main gear trade study Option 1

Single beam, t = 0.0017 ft Stroke = 0.0215 ft Weight = 0.0014 lbf

Option 2 Single beam, t = 0.0034 ft Stroke = 0.0027 ft Weight = 0.0029 lbf

Option 3 Dual beam, t = 0.0017 ft Stroke = 1.2e-8 ft Weight = 0.0032 lbf

•Parameters•θ = 30°•Material = Al•Ngear = 3 (Gen. Av.)

3

sin3

FlS

EI

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Landing Gear

Drop test h = 3.6 * (wing loading)1/2 -Raymer

Height will be 2 ft

Raised to 4 ft to simulate drop from carrying height

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Weights/CG

Sizing Actual distances above - specified on next page Weight : 0.84 lbs

AC

CG

Components

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Weights/CG

CG 31.3% AC 40.7% Static Margin 9.4%

Values are for Micro

size components

  Weight (lbf) Location (ft)

Motor 0.090 1.208

Speed Control 0.063 0.146

Batteries 0.350 0.059

Gear Box 0.033 1.222

Wing 0.080 0.309

Tails 0.035 1.981

Booms 0.057 1.798

Wheels 0.019 0.393

Radio 0.013 0.146

Gyro 0.063 0.146

Wing Servos 0.028 0.871

H-Tail Servo 0.014 1.981

V-Tail Servo 0.014 2.010

    CG

TOTAL 0.857 0.551

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Load Analysis

Structural loads from code – basic equations usedτ max = 2.40 lbf/ft2

Mroot = 0.26 ft-lbfσmax = 0.0048 lbf/ft2

Deflectionsδy = 9.1e-11 ftδΦ = 1.1e-4 degrees

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Load Analysis Continued…

Torsion Loads T = 0.1 ft-lbf. at high

maneuver

Failure of wing (most likely due to buckling) occurs at ncr = 38 or at σcr = 32lbf.

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V-n Diagram

Maximum Loading never reached (n=5 for

homebuilt)

qmax occurs at around 32 ft/s

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Wing Geometry Section

Eppler E212 Main Elements

W/S = 0.33 lbf/ft2

b = 3.24 ft ctip = 0.33 ft croot = 1.11 ft

Construction Elements CNC from single foam core block Single layer of bi-directional S-glass

Polyester Matrix

0 0.2 0.4 0.6 0.8 1

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

e212

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Fuselage

CNC solid shape for blended fuselageStronger main sectionEasily and precisely created

Fiberglass skinProvides load bearing structure for wingStrength VS weight tradeoff very acceptable

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Horizontal Tails

Based on Eppler 169 Foam core on CNC Fiberglass skin

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Vertical Tails

Based on NACA 0010 Same foam and

fiberglass construction

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Control Surface Layout

Ailerons as shown Elevator will be

approximately half of horizontal tail area

Rudder will again be approximately half of total surface

Vertical Tail

AAE 451 – Team 5March 3, 2005 16

Questions?