Prelim inary Design Review Micro Air Vehicle Surveillance Platform - - PowerPoint PPT Presentation

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Slide 1

Prelim inary Design Review

Micro Air Vehicle Surveillance Platform

RIT Multidisciplinary Senior Design 2005-2006 Project Number P06007

February 24, 2006

• Dr. Jeffrey Kozak

Project Advisor

• Dr. Alan Nye

Project Coordinator Matteo Blanc Mechanical Engineering Joe Calandro Systems Engineering Adam Gillis Electrical Engineering Shane Healey Mechanical Engineering Josh Joseph Mechanical Engineering Applied Mathematics Mike Koelemay Mechanical Engineering BS/Meng Project Manager John Lemmon Mechanical Engineering Michael Reid Mechanical Engineering BS/MS Andrew Streett Mechanical Engineering BS/MS

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Slide 2

Presentation Outline

• Introduction
• Needs Assessment
• Concept Development and Feasibility
• Subsystems Design Analysis
• Electronics
• Aerodynamics
• Materials and Manufacturing
• Preliminary Design
• Next Steps

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Slide 3

I ntroduction

• Micro Air Vehicle (MAV) History
• DARPA
• MAV Program Initiative 1996
• International Micro Air Vehicle Competition
• 10th year
• 4 Objectives

Surveillance Endurance Ornithopter Design Report

• RIT History
• 4th year (3rd in competition)

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Slide 4

I ntroduction – Team Structure

• The MAV is broken into 4 subsystems
• Aerodynamics
• Materials and Manufacturing
• Electronics
• Propulsion System

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Slide 5

Com petition Objective - Surveillance

• The objective of the competition is to design

and build the smallest MAV that can fly and photograph a 1.5-meter sized symbol on the ground located 600 meters from the launch site.

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Slide 6

Needs Assessm ent

• Electronics
• Record an image
• Lightweight
• Small
• Control surface movement
• Minimal power consumption
• Aerodynam ics
• Stability
• Minimize the max linear dimension
• Scalability
• Aerodynamic control
• Materials and Manufacturing
• Lightweight
• Durable
• Effectively integrate all systems
• Precise and consistent manufacturing

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Slide 7

Concept Developm ent and Feasibility – Com bined System

• Quality Function Deployment, Phase I
• Quality Function Deployment, Phase II
• Morphological Analysis
• Pugh Analysis

QFD1, QFD2, MA, PA1, PA2

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Slide 8

Concept Developm ent and Feasibility – Com bined System

• Quality Function

Deployment Analysis, Phase I

Key

0 = not important 1 = slightly important 3 = important 9 = very important

Customer Requirements

Able to fly 600 meters (linear) Able to take a “legible” picture Wireless remote control Stay within budget Stable, consistent launching unnecessary Able to be flown accurately Must be durable Must provide hard copy of photo Onboard power supply

Customer Weight

9 9 9 3 9 3 3 9 9

Engineering Metrics Weight (g)

Dimensions (cm)

Resolution Power (mAh) Thrust (g) RF Power (mW)

1 1 3 3 3 3 1 1 3 3 1 3

Voice of the Customer

9 3 1 1 9 3 9 3 1 1 1 9 9 1 3 3 1 3 1 9 1 1 9 3

Technical Target

80 Weight (g) Dimensions (cm) Resolution (lines) Power (mAh) Thrust (g) RF Power (mW) Optimization 3 1 9 9 1 1 1 1

Key

0 = not correlated 1 = slightly correlated 3 = correlated 9 = highly correlated 65 300

380 25.4

100 Raw Score Relative Weight 84 78 108 300 150 204 .09 .08 .12 .32 .16 .22

Back

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Slide 9

Concept Developm ent and Feasibility – Com bined System

• Quality Function

Deployment Analysis, Phase II

Engineering Metrics Phase I Relative Weights

Weight (g) Dimensions (cm) Resolution (lines) Power (mAh) Thrust (g) RF Power (mW) Raw Score Relative Weight

Wing Pod Propulsion System Camera System Servos MAV Parts

.09 .08 .12 .32 .16 .22 1 1 9 3 1 9 1 1 1 9 9 9 3 9 3 3 3

Key

0 = no contribution 1 = slight contribution 3 = notable contribution 9 = large contribution

.81 .17 5.87 4.97 1.71 .06 .01 .43 .37 .13

Back

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Slide 10

Concept Developm ent and Feasibility – Com bined System

• Morphological

Analysis

Control

Power

Camera System

Skin

Propu- lsion Wing/ Pod Flight - Yaw Flight - Pitch Flight - Roll

02 03 04 01 05 06 07 08 09 10 11 12

Remote Control (Human Operator) Remote Control (Computer/Hu man Operator) Stability Augmenta-tion Autonomo-us None Lithium Polymer Battery Gas Microturbi-ne Alkaline Batteries Capacitor Camera with Film Storage Camera with Digital Storage Camera with Transmitter Infrared Camera with Transmitter Night Vision Camera with Transmitter Movable Camera with Transmitter Shrink-wrap Tissue Paper Parylene-C Resin/Epo-xy Mylar Durobatics Fabric Polymers Latex Chemical Resin Dip Electric Motor/Pro- pellor Gas Motor/Pro- pellor Compress-ed Air Ornithopter Electric Motor/Pro- pellor/Shr-oud Polymers Rapid Prototyping Durobatics Aramid Carbon Fiber Fiberglass Composite Rods Composite Tow Aramid/Ca- rbon Combo Titanium Alloy Balsa Carbon/La-tex Combo Rudder Spoilers Morphing Thrust Vectoring (Drag) Differential Morphing Elevon Movable C.G. Thrust Elevator Elevons Thrust Vectoring Morphing Movable C.G. Elevons Flaperons Ailerons Thrust Vectoring Spoilers Morphing Movable C.G. Fiberglass None

Back

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Slide 11

Concept Developm ent and Feasibility – Com bined System

• Pugh

Analysis, Part I

Design Concepts 01 Control Power Camera System Skin Propulsion Wing/Pod Flight - Yaw Flight - Pitch Flight - Roll Sub-Functions

Remote Control (Human Operator)

02 03 04

Lithium Polymer Battery Camera with Transmitter Parylene-C Electric Motor/Propeller Carbon Fiber Rudder Elevons Elevons Remote Control (Human Operator) Lithium Polymer Battery Camera with Transmitter Shrink-wrap Electric Motor/Propeller/Shroud Aramid/Carbon Combo Rudder Elevons Elevons Remote Control (Human Operator) Lithium Polymer Battery Camera with Digital Storage Fiberglass Electric Motor/Propeller Aramid/Carbon Combo None Elevons Elevons Remote Control (Human Operator) Lithium Polymer Battery Movable Camera with Transmitter Latex Electric Motor/Propeller Carbon/Latex Combo None Morphing Morphing

Criteria Able to fly 600 meters (linear) Able to take a “legible” picture Wireless remote control Stay within budget Stable, consistent launching unnecessary Able to be flown accurately Must be durable Must provide hard copy of photo Onboard power supply Score # +’s # S’s # -’s 01 02 03 04 Design Concepts S S + + + S S S

• +
• +

+ S + S

• S

S

• S

S S S 3 1 4 5 4 4 1 4 1 Criteria Able to fly 600 meters (linear) Able to take a “legible” picture Wireless remote control Stay within budget Stable, consistent launching unnecessary Able to be flown accurately Must be durable Must provide hard copy of photo Onboard power supply Score # +’s # S’s # -’s 01 02 03 04 Design Concepts S S S

• S

S S S +

• S
• S

S

• S

S

• S

S S S 1 5 3 8 3 6 1

R E F E R E N C E R E F E R E N C E

+

• Back

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Slide 12

Concept Developm ent and Feasibility – Com bined System

• Pugh

Analysis, Part II

Criteria Able to fly 600 meters (linear) Able to take a “legible” picture Wireless remote control Stay within budget Stable, consistent launching unnecessary Able to be flown accurately Must be durable Must provide hard copy of photo Onboard power supply Score # +’s # S’s # -’s 01 02 03 04 Design Concepts S S S + + + S S S + + + + + + + + + + + + + S S S 6 6 6 3 3 3 Criteria Able to fly 600 meters (linear) Able to take a “legible” picture Wireless remote control Stay within budget Stable, consistent launching unnecessary Able to be flown accurately Must be durable Must provide hard copy of photo Onboard power supply Score # +’s # S’s # -’s 01 02 03 04 Design Concepts S S S S

• S

S S +

• +

S

• S
• S
• S

S

• S

S S S 1 1 8 3 5 6 3

R E F E R E N C E R E F E R E N C E

+ + Design Concepts 01 Control Power Camera System Skin Propulsion Wing/Pod Flight - Yaw Flight - Pitch Flight - Roll Sub-Functions

Remote Control (Human Operator)

02 03 04

Lithium Polymer Battery Camera with Transmitter Parylene-C Electric Motor/Propeller Carbon Fiber Rudder Elevons Elevons Remote Control (Human Operator) Lithium Polymer Battery Camera with Transmitter Shrink-wrap Electric Motor/Propeller/Shroud Aramid/Carbon Combo Rudder Elevons Elevons Remote Control (Human Operator) Lithium Polymer Battery Camera with Digital Storage Fiberglass Electric Motor/Propeller Aramid/Carbon Combo None Elevons Elevons Remote Control (Human Operator) Lithium Polymer Battery Movable Camera with Transmitter Latex Electric Motor/Propeller Carbon/Latex Combo None Morphing Morphing

Back

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Slide 13

Concept Developm ent and Feasibility – Com bined System

• Conclusion of Feasibility Analysis for Entire MAV:

Concept 1 Concept 2 MAV Control Remote Control (Human Operator) Remote Control (Human Operator) Camera System Color Camera with Transmitter Color Camera with Transmitter Skin Parylene-C Shrink Wrap Wing/Pod Carbon Fiber Aramid/Carbon Combination Yaw Control None Rudder Pitch Control Elevons Elevons Roll Control Elevons Elevons Concept 3 Concept 4 MAV Control Remote Control (Human Operator) Remote Control (Human Operator) Camera System Color Camera with Digital Storage Movable Color Camera with Transmitter Skin Fiberglass Latex Wing/Pod Aramid/Carbon Combination Carbon/Latex Combination Yaw Control None Rudder Pitch Control Elevons Elevons Roll Control Elevons Elevons

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Slide 14

Electrical Subsystem

Propulsion System

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Propulsion Electronic System W iring Diagram

p/n: Firefly 799 Coreless Motor

Speed Controller p/n: Astro 200

LiPoly Battery (3.7V @ 1.5A) p/n: LP300 LiPoly Battery (3.7V @ 1.5A) p/n: LP300 LiPoly Battery (3.7V @ 1.5A) p/n: LP300

Power Source (11.1V @ 1.5A)

Micro 2R Polarized Connectors p/n: 1222 RF Receiver p/n: 805FM72V2

Throttle Channel (Typically 3)

Servo Connector

Ch 46 Crystal Oscillator p/n: RXQTM72-(41-50) White = signal Black = ground Red = Power (+5V) Propeller p/n: GWS6030 or Equivalent

Back

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Slide 16

Electronics - Requirem ents

• Picture
• Data transmission
• Power consumption
• Size
• Weight

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Electronics - Literature Review

• Camera
• Imaging
• Resolution
• Casing Removal
• Transmitter
• Frequency
• Casing Removal
• RF-Power

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Electronics - Cam era/ Transm itter System s

Camera Transmitter 1 8 0.612 80 6423.7 2 CM-588 SDX-21LP 5.5 0.63 25 1515.6 3 CM-588 SDX-22 5.5 0.96 80 2007.2 4 CM-524 SDX-22 8.5 0.96 80 4511.2 RF-Power (mW) Volume (mm3) Combination Model number CMDX-22 Weight (grams) Power (W)

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Electronics – Cam era/ Transm itter Design Matrix

1 2 3 4 1 2 3 3 4 1 2 3 3 1 1 4 4 1 1 1 1 4 1 1 13 9 8 12 Sub-Functions Design Concepts Power Consumption Size Weight Rf-Power output Total Resolution

System Feasibility Matrix

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Slide 20

Electronics - Antenna and Receiver

• Antenna
• Model: HG2424G
• Receiver
• VRX-24L

Antenna Comparison, Receiver Sensitivity vs. Distance

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Electronics – Antenna Com parison Matrix

Back

Model Type Frequency Gain (dBi) Horizontal Vertical HG2411DP patch antenna 2.4-2.5GHz 11 60° 30° HG2424G dish antenna 2.4-2.5GHz 24 8° 8° HG2409P patch antenna 2.4-2.5GHz 8 75° 65° HG2416P patch 2.4-2.5GHz 15.5 25° 25° HG2415U-PRO omni directional 2.4-2.5GHz 15 360° 8° HG2412Y yagi 2.4-2.5GHz 12 45° 45° HG2415Y yagi 2.4-2.5GHz 14.5 30° 30° HG2412P mini panel 2.4-2.5GHz 12 65° 34° Beam width

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Slide 22

Receiver - Required Sensitivity at Various Distances

Distance (meters) With No Signal Error (dBm) With 30% Signal Error 400

• 51.1
• 66.4

500

• 53.1
• 69.0

600

• 54.6
• 71.0

700

• 56.0
• 72.8

800

• 57.1
• 74.3

900

• 58.2
• 75.6

nna cieve ante Gain of re wer antenna po transmitt es Cable loss FSL ensitivity Receiver S + + + =

dBm in Gain 30 ) P ( 10 = + ⋅ Log

)] ( 20 ) ( 20 56 . 36 [ 1 D Log F Log FSL ⋅ + ⋅ + ⋅ − =

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Slide 23

Receiver - Distance vs. Sensitivity

Distance to Transmitter vs. Sensitivity sensitivity = -8.6859Ln(D) + 0.9267

• 80.0
• 70.0
• 60.0
• 50.0
• 40.0
• 30.0
• 20.0
• 10.0

0.0 10.0 500 1000 1500 2000 2500 3000 3500

Distance (meters) Sensitivity(dbm)

Back

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Slide 24

Electronics - Servos

• Blue Bird Ultra Servo BMS-303
• 130 mA Current Draw

Servo Weight (grams) Blue Bird Ultra Servo BMS-303 3.7 Blue Arrow BA-TS-4.3 4.3 Cirrus CS-101 4 Futaba S3111 6.6 Hitec HS-55 8 Hitec HS-50 6.5

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Electronics - Final System Concept

Maximum Current Draw 35 mA + 60 mA + 130 mA + 130 mA = 355 mA Total Current Available = 450 mA

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Pow er Budget

Power Distribution Breakdown Summary of Component Power Requirements

Video cam era 1 % Pow er Surplus Pow er Source RF receiver 1 % Speed controller 1 % Electric m otor Video transm itter 2 % Servo m otors

Component Part Number Description Current (A) Power Source LP300 (x3) LiPoly 300mAh 1.5 Speed controller Astro 200 Coreless speed controller 0.025 RF receiver FMA M5v2 Sub-micro receiver 0.025 Electric motor 799 Firefly coreless motor 0.98 Servo motors BMS-303 Light weight servo motors (x2) 0.26 Video camera CM-588 50mW Video Transmitter 0.035 Video transmitter SDX-22 Panasonic Camera 0.06 Power Surplus

• 0.115

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Slide 27

Aerodynam ics - Literature Review

• Airfoil Development

Thin airfoil advantages XFOIL

• Static Stability

Pitch requirements Yaw requirements Roll requirements

• Wing Development

Possible shapes Aspect ratio / Surface area

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Aerodynam ics – Requirem ents and Specifications

• System Level

Generate lift in access of weight Insure static stability Minimize max linear dimension Scalable platform

• Subsystem Level

Airfoil – maximize CL/ CD and ensure pitch stability Wing – minimize max linear dimension, minimize tip effects Vertical tail – insure yaw stability Control surfaces – pitch and roll control, minimize drag effects

Detailed Requirements

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Slide 29

Aerodynam ic Requirem ents

• Aerodynamic Stability:
• Must be stable in pitch, yaw, roll
• Aircraft will have a positive pitching moment intercept and a negative slope
• Elevons shall be effective in controlling pitch rates
• Aircraft shall be critically damped in yaw direction
• Aircraft yawing moment curve must be positive and 0 intercept
• Aircraft shall have a negative rolling moment and 0 intercept
• Elevons shall be effective in controlling roll rates
• Force on control surfaces shall not exceed force provided by servo
• The CG shall be located to ensure stability
• Elevon operation shall have minimal effect on yaw
• Lift and Drag:
• Planform must minimize tip vortices
• Size:
• Planform that optimizes lift for smallest maximum linear dimension
• Endurance:
• Maintain stability/ lift/ drag for the duration of the flight

Back

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Aerodynam ics – Concept Developm ent and Feasibility

• Airfoil

Traditional (NACA series), Low Reynolds number, Top and MCL surface, Nth order polynomial, and Bezier

• Planform

Square, Taper, Circle, Modified Circle, 3 Circle, Zimmerman, I nverse Zim m erm an

• Vertical Tail

Airfoil, Flat Plate, and Size, Location

• Control Surfaces

Elevons, rudder, elevator, ailerons Hinged, Morphable, Full length, Segmented

Wing, Vertical Tail Feasibility, Surface Area vs. Chord Length

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Aerodynam ics - W ing, Vertical Tail Feasibility

Planform (Wing Shape)

Circle Inverse Zimmerman 3-Circle Modified Circle Zimmer man Elliptical Tapered

No Tip Vortex Control Integration Control Surfaces

Pro’s

Max Linear Dimension (1)

Control Integration (3)

4

Pro’s Surface Area (2) Stability (1)

3

Pro’s Aspect Ratio (3) Control Surfaces (2)

5

No Control Sur. Tip Vortexes Bad Flow Large Leading Edge No Max Linear Dimension Surface Area No Control Sur. Max Linear Dimension Ease of Manufacturing Surface Area

Back

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Slide 32

Aerodynam ics – Surface Area vs. Chord Length

10 20 30 40 50 60 70 80 5 5.5 6 6.5 7 7.5 8 b MLD s AR b (g = 1.2) MLD (g = 1.2) s (g = 1.2) AR (g= 1.2)

Surface Area (in2) Chord Length (in) Back

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Slide 33

Aerodynam ics - Design Analysis and Synthesis

• Airfoil Design

XFOIL Analysis Linear relationship of Cl,max and camber Optimal Cl/ Cd

• Planform Design

3 circle design method Airfoil distribution

• Vertical Tail Design

Effects in yaw and roll Dynamic testing

• Control Surface Design

Preliminary measurements of control effectiveness parameters

Arcs c* LE TE Center of Arcs Control Surface Effectiveness, CL/CD vs. Camber

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Control Surface Effectiveness

Back

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Aerodynam ics - Design Analysis and Synthesis

Back

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Slide 36

Materials and Manufacturing – Literature Review

• Previous Work

2001 Black Widow Solid polystyrene foam 2001+

• U. of Florida

Prepreg carbon fiber skeleton with latex skin 2002

• U. of Arizona

Carbon rods with fiberglass skin 2004 Microbat Titanium alloy spars and parylene-c skin 2004-05 RIT Insulation foam 2005 Lehigh Depron and water jet CNC machine

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Materials and Manufacturing – Literature Review

• Materials Background

Composites - Glass/ Carbon/ Aramid, continuous fiber stain weave and tow, epoxy resin Polymers - Shrink wrap, mylar, durobatics foam, insulation foam, latex rubber, thin plastic film, ABS plastic, parylene-c Requirements: Lightweight, durable, integration

• Manufacturing Background

Composites - Hand lay-up, vacuum bagging, autoclaving, RIT carbon and Kevlar rods Molds - Fusion deposition molding techniques, CNC with aluminum Skin Materials - Latex rubber and parylene-c Requirements: Precise and cost effective

More

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Graphs/ Charts for Lit. Review

Back

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Slide 39

Materials and Manufacturing – Concept Developm ent and Feasibility

• Wing Skeleton/ Control Surfaces

Requirements: 1. Adhere to Aerodynamics Specifications and Planform Size/ Shape 2. Durable, Lightweight and Effective in Dynamic Loading 3. Resolve Connectivity issues Feasible Materials Assessed: Fiberglass, Carbon, Aramid, Carbon/ Aramid – Tow and Satin Weave

Specific Specific Specific Low Shear in-plane & Materials: Strength Stiffness Modulus Density interlaminar Fiberglass 2 3 3 3 1 12 Carbon Fiber 1 1 1 2 1 6 Aramid 1 3 2 1 2 9 Carbon/Aramid 2 2 2 2 1 9 Totals

Skeleton Material Properties Feasibility Chart

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Materials and Manufacturing – Concept Developm ent and Feasibility

• Wing Skin/ Control Surfaces

Requirements: 1. High Strength, lightweight and meet flexibility/ rigidity needs 2. Integrate fully with wing skeleton 3. Effective in dynamic loading Feasible Materials Assessed: Shrink wrap, Mylar, Durobatics foam, insulation foam, latex rubber, thin plastic film, ABS plastic, parylene-c

• Component Housing

Requirements: 1. Durable to house expensive components 2. Static center of gravity 3. Integrate completely with wing skeleton and all necessary components Feasible Materials Assessed: Fiberglass, carbon, aramid, carbon/ aramid, latex

Feasibility Charts

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Materials and Manufacturing – Concept Developm ent and Feasibility

Specific Specific Specific Low Shear in-plane & Materials: Strength Stiffness Modulus Density interlaminar Fiberglass 2 3 3 3 1 12 Carbon Fiber 1 1 1 2 1 6 Aramid 1 3 2 1 2 9 Carbon/Aramid 2 2 2 2 1 9 Totals

Skeleton Material Properties Feasibility Chart

Type of Fibrous Composites: Drapability Weight Crimp Totals Unidirectional 3 1 3 7 Plain Weave 2 2 2 6 Twill Weave 2 2 2 6 Satin Weave 1 2 1 4 Multiaxial (4+ layers) 2 3 3 8 Tow 1 1 1 3 Prepreg 2 3 3 8

Skeleton Material Type Feasibility Chart

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Materials and Manufacturing – Concept Developm ent and Feasibility

Specific Strength Gauge Environmental Materials: (puncture resist) Thickness Added Weight Adhesion Considerations Shrink Wrap 2 3 2 1 2 2 2 1 15 Mylar 2 3 2 2 2 2 2 1 16 Durobatics foam 3 1 3 1 1 2 2 2 15 Insulation foam 1 3 3 3 1 2 2 2 17 Latex Rubber 2 1 1 2 1 2 2 3 14 Thin Plastic Film 2 1 1 1 1 2 2 1 11 ABS Plastic 1 3 3 3 2 3 3 1 19 Parylene-C 1 2 1 1 3 1 1 1 11 Totals Adhesion to Wing Skeleton Morphability Density Cost

Skin Material Feasibility Chart Specific Specific Specific Low Ease of Strength Stiffness Modulus Density Integration Materials: (Impact Resist) (Static CG) (Containment) (Weight) (Molds) Fiberglass 3 3 3 3 2 14 Carbon Fiber 2 1 2 2 2 9 Aramid 1 2 2 2 2 9 Carbon/Aramid 1 2 2 2 2 9 Latex 3 3 1 1 1 9 Totals: Component Housing Material Feasibility Chart

Back

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Materials and Manufacturing – Final Concept

Wing Skeleton/Control Surfaces:

Carbon Tow and satin weave

Wing Skin/Control Surfaces:

Thin Film or Parylene-C

Component Housing:

Carbon/Aramid Manufacturing Exploded Diagram

Mold for Creating Wing Skeleton

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Materials and Manufacturing – Design Analysis and Synthesis

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Materials and Manufacturing – Concept Developm ent and Feasibility

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Prelim inary Design Sum m ary

Component Design or Part Airfoil Bezier or Top Surface Planform 3-Circle Vertical Tail Below, thin plate, carbon fiber/aramid Control Surfaces Morphable Elevons Wing Skeleton Material Carbon Fiber, Satin Weave, Tow Wing Skin Material Thin Plastic Film, Parylene-C Component Housing Material Carbon Fiber, Aramid, Carbon/Aramid, Latex Camera CM-588 Transmitter SDX-22 Servos BMS-303 Antenna HG2424G Receiver VRX-24L Control Surface Linkage Steel cables through sheathing Propulsion From P06002

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Prelim inary Cost Analysis

Project / Part Name Cost per Qty Cost at Qty Supplier Part Number(s) Low Density Carbon Fiber $ 19.50 0.1 $ 1.95 www.uscomposites.com FG-CF5530 Low Density Carbon/Kevlar $ 36.50 0.1 $ 3.65 www.uscomposites.com FG-CK99250 Carbon Tow $ 19.50 0.2 $ 3.90 www.hexcel.com IM7-G 12K 199 Resin $ 49.99 0.02 $ 1.00 www.uscomposites.com 635 Thin Plastic Film $ 2.00 0.1 $ 0.20 Lowes none specified Servos $ 18.95 2 $ 37.90 www.balsapr.com BMS-303 Cables/Sheaths $ 2.50 1 $ 2.50 GE Inspection Technologies none specified Camera, Transmitter, Receiver, Antenna, Amplifier $ 900.00 1 $ 900.00 www.rf-links.com CM-588, SDX-22, BMS-303, HG2424G, VRX-24L Propulsion System $ 100.00 1 $ 100.00 Senior Design Team P06007 none specified

Total Cost: $ 1,051.10

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Slide 48

Surveillance MAV Project – Road Map – Senior Design II

Order Parts

Electronics Aerodynamics/Integration

Week 1 Week 5,6 Week 7,8 Optimize System Components Finalize System Develop Equations Make Molds Make Rods/Wings Visualization Tests (Dynamic) Flight Tests Static/Dynamic Testing Analysis Week 2,3,4 Week 9,10 Final MAV Feedback Testing – Camera, Transmitter, Antenna, Receiver

1-3 Iterations

Feedback

Gantt Chart

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Surveillance MAV Project – Gantt Chart – Senior Design II

Electronics Aerodynamics/Integration

W 1 Flight Tests Static/Dynamic Testing Make Molds (Create) Make Rods/Wings Specifics (Equations) Analysis Visualization Tests (Dynamic) Finalize System Order Parts Test Camera Test Transmitter Test Antenna/Receiver Optimize System Components W 2 W 3 W 4 W 5 W 6 W 7 W 8 W 9 W 10

Subsystem Details

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Slide 50

Next Steps

• System
• Manufacturing
• Flight testing
• Propulsion system integration
• Aerodynamics
• Dynamic stability design assessment
• Electronics
• Testing transmission ranges
• Subsystem integration

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Slide 51

We would like to thank the following sponsors for their generous donations and support!! Impact Technologies Boeing GE Inspection Technologies Ornithopter Zone

Thank you!