Poseidons Fury

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Poseidons Fury
AIAA Student Design Build Fly Electric Airplane
Kristina Morace Jonathan Moore Ryan
Holmes University of Central Florida
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Outline
1. Required and Desired Features 2. General
Design Overview 3. Drain and Structural
Analysis 4. Aerodynamics and Flight
Performance 5. Propulsion System 6. Summary
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Aircraft Features

• Required
• R/C Electric powered
• 5 lbs max NiCad batteries
• 4 liters max payload
• 0.5" max drain orifice
• Complete 2 missions
• Pass wing tip tests
• 4' x 2' x 1' box

• Desired
• Carry 4 liters
• Drain Time 30 sec
• Lift capacity 25 lb
• Flight Stability
• Battery weight 3 lb
• High pitch speed
• Low RAC

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Rated Aircraft Cost
RAC (300MEW 1500REP 20MFHR)/1000 where
MEW Empty Weight REP Battery Weight
MFHR Component Summation Total Score
Written Report Flight Score RAC
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Aircraft Overview
- Wing span 9.5 ft - Length 5 ft - Height
28 in
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Drain System
- Custom 4 liter tank - Custom ball valve
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Main Fuselage
Inner-wing
5th Bulkhead
- 7 Bulkheads - Inner-wing - 5th bulkhead
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Landing Gear
- Tricycle Configuration - Carbon Fiber -
Detachable
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Twin Booms
- Carbon Fiber - Detachable
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Wing Sections
- Secure booms - Bolt to inner wing - Detachable
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Inverted V-tail
- Pins into booms - Detachable
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Powerplant
- Motor - Batteries - Spinner - Propeller
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Aft Cone
- Twists on/off - Access to electronics
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Drain System
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Valve Design

• Good seal
• Actuate in flight
• True ½ inch orifice
• Manufactured using stereolithography
• Drain Coefficient
• Between 0.6 - 1.0
• Actual 0.8
• Drain time 55 sec

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Tank Design

• Holds 4 liters
• Baffles
• Modified Geometry
• Predicted drain time
• 32 seconds
• Actual Drain time
• 30 seconds
• 45 reduction!

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Wing Spar
5th Bulkhead
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Wing Spar

• Laminate ply
• 2 layers of carbon fiber
• 4 attach points
• Built to support full load 20 lbs

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Spar Analysis

• Wing Tip Test
• Symmetric
• 10 lb load at tip
• Max stress 27.9 ksi

Max Stress 27.9 ksi
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Landing Gear Analysis

• Aluminum Gear (661-T6)
• 3g load
• Max Von Mises 20.6 ksi
• FOS 1.9
• Weighs 0.75 lbs

• Carbon Fiber Gear
• 3g load
• Max Tensile Stress 22.2 ksi
• FOS 2.0
• Weighs 0.43 lbs

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Aerodynamics and Flight Performance
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Aerodynamics Goals

• Low Reynolds Number (105)
• Lift Coefficient gt 1.2
• Lift to Drag Ratio gt 5
• Low Camber
• Low RAC

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Aerodynamics Test Verification
Predicted
Test
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Aerodynamics Airfoil

• Eppler 216

• Exceeds Needs
• CL,max 1.4
• (L/D)max 22
• Problem
• Thickness to Chord Ratio Too Small
• Design 10.4
• Need 12.5

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Aerodynamics Airfoil

• Eppler 216 Modified

Modified
E216
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Aerodynamics Airfoil

• Eppler 216 Modified

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Aerodynamics Wing
9.5
AC 25 of Chord
CG 25 of Chord
10.5
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Aerodynamics Empennage
Actual Path

• Inverted V Configuration
• Pro-verse Yaw Characteristics
• Aircraft Score Rewards

Ideal Turn
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Aerodynamics Empennage

• Inverted V Configuration
• Pro-verse Yaw Characteristics
• Aircraft Score Rewards

• Twin Boom Configuration
• No Ground Strike
• Robust and Modular

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Aerodynamics Empennage
Angle Between Panels 110 deg.
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7.5
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Flight Performance
The Difference Longitudinal Stability
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Performance Phugoid Stability
Period 14 minutes Flight Characteristics
Level 2
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Performance Short Period Stability
Period 21.5 s Flight Characteristics Level 1
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Performance Stability

• Pilot Rating (Cooper-Harper Scale)

• 1st Flight resulted in a 5
• Poor Roll control from Adverse Yaw
• Aileron Differential Added
• Poor Ground Handling
• Corrected Steering Control

Remaining Flights are a 1
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Performance Flight Testing
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Performance Flight Testing
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Performance Flight Testing
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Propulsion System
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Propulsion System

• Nomenclature
• System Requirements
• Predicting Outputs
• Testing
• System Integration
• Safety Features

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Nomenclature

• Energy Density

• Sanyo 1700 mA-hr
• A size Ni-Cad battery

• Sanyo 2400 mA-hr
• C size Ni-Cad battery

36 cells
32 cells
3 lb
5 lb

• Rated Aircraft Cost (RAC)
• Rated Engine Power (REP)
• Manufacturer's Empty Weight (MEW)

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System Requirements

• Take-Off
• Thrust gt 4 lbf
• Speed gt 30 mph
• Distance lt 150 ft
• Steady Level Flight
• Thrust gt 1 lbf
• Minimize RAC

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Predicting Outputs

• ThrustHP Calculator Software
• Inputs
• Propeller
• Diameter
• Pitch
• RPM
• Outputs
• Pitch Speed
• Static Thrust

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Testing Schematic
Stroboscope
Spring Scale
Multimeter (Voltage)
External Power Source
Multimeter (Current)
Speed Controller
Radio Transmitter
Current Divider
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Testing
Thrust Sled
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Test Results
Minimum Thrust
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Test Results
32 C batteries
Minimum Pitch Speed
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Propulsion Results Summary

• 33 reduction in MEW and REP
• First 3 minutes
• 6 lbf Static Thrust
• 47 mph Pitch Speed

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Propulsion Integration
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Propulsion Safety Features

• Kill Switches
• 40 Amp Fuse
• PCM Receiver
• Air Scoops

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Summary

• Satisfies all competition requirements
• carries 3 lbs of batteries
• passes loaded wing tip test
• takes off in 132 ft
• easily fits into box
• Contains all desired features
• carries 4 liter payload
• drains in 30 seconds
• minimized RAC
• Successfully completes loaded and unloaded
  missions

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Acknowledgements

• Team Members
• Michael Denton
• Craig Daniels
• Underclassmen
• Advisor
• Dr. Eric Petersen

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Questions?