fall final presentation november 30, 2004 maverick solutions todd adkins leroy cohen jr. adam...
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Fall Final Fall Final PresentationPresentation
November 30, 2004November 30, 2004
MAVerick SolutionsMAVerick Solutions
Todd AdkinsTodd Adkins
Leroy Cohen Jr.Leroy Cohen Jr.
Adam HollrithAdam Hollrith
Brian MooreBrian Moore
OVERVIEWOVERVIEW
ObjectivesWing ConceptsDeployment MechanismsDesign AnalysisCost AnalysisCurrent WorkFuture Work
ObjectivesObjectives
Design and fabricate component technology that will provide a MAV the capability to collapse/fold all wing surfaces along the body of the fuselage
Assess current materials and technologies that will maximize subsystem performance and minimize size and weight (i.e. composites, plastic actuators)
Demonstrate final concept design at Eglin AFB
Furnish final report documenting project objective, approach, results, budget analysis for hardware used, and conclusions/recommendations
SpecificationsSpecificationsParameters Specifications
Wing Dimensions 6” wingspan, 3-4” width
Deploy/Retract time interval 1-3 seconds
Fuselage dimensions 1-1.5 in. diameter x-sec., 4-6 in. lengthLanding System No
Wing/On-board Power Source 10-12 V
MAV recoverable Yes
Wing Material Carbon Fiber
System Weight 100-200 gm
Vehicle Velocity < 25 mph
MAV control Remote
Fuselage Material Carbon fiber
Stowed DimensionsMAV cross section must fit in 3"
diameter tube, Wings may not extend past tips of fuselage
Activation DevicesMicro Servos, Micro Actuators,
Micro Motors, Springs
System PackagingAll mechanical and structural
components to be contained within a single module
System ModuleTo be easily implemented into the
existing MAV fuslage
Wing ConceptsWing Concepts
Concept #1
Involves a pair of wings that fold along the sides of the fuselage Pros- Compact design
Cons- Complicated deployment path- Multiple driving mechanisms- Two separately moving wings
Wing ConceptsWing Concepts
Concept #2
Involves a one-piece, rotating wing Pros- Simple deployment- Compact design- One rotating mechanism- One-piece wing design
Cons- Concentrated stress on single support- Possible interference with tail of MAV
Wing ConceptsWing Concepts
Concept #3
Involves a bi-wing design that will allow for greater lift capabilities and improved glide slope
Pros- Greater lift capabilities than concept 2- One-piece wing design- Central rotating mechanism
Cons- Possible wing interference- Greater weight
Wing ConceptsWing Concepts
Concept #4
Comprised of a two-wing system that simply rotates into deployment The wings overlap on the top of the vehicle fuselage while stowed Pros- Simple and quick deployment- Compact design
Cons- Interference caused by overlapping wings- Two wing attachment points
Wing ConceptsWing Concepts
Concept #5
Comprised of one central connection between the wings and the fuselage Both wings will rotate from the same point Pros- Central rotation point- Compact design- Simple and quick deployment
Cons- Interference from overlapping wings- Relatively more complex concentric shafts
Actuator DeploymentActuator Deployment
Linkage DeploymentLinkage Deployment
Gear Set DeploymentGear Set Deployment
Design Analysis - Lift and DragDesign Analysis - Lift and Drag
Lift Force (N) vs. Velocity of MAV (mph) Coefficient of Lift
0 2.5 5 7.5 10 12.5 15 17.5 20 22.5 250
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
FL_1 VMAV N
FL_1.25 VMAV N
FL_1.5 VMAV N
FL_1.75 VMAV N
FL_2.0 VMAV N
VMAV
mph
CL_2.0 3
CL_1.75 2.5
CL_1.5 2.0
Need to be above (0.981 N) ------->CL_1.25 1.5
CL_1 1
FL WMAV
FL 0.981N
Lift Force must be equal to 0.981 N for MAV to fly
Design Analysis - Lift and DragDesign Analysis - Lift and Drag
Coefficient of Drag
0 2.5 5 7.5 10 12.5 15 17.5 20 22.5 251 10
10
0.04
0.08
0.12
0.16
0.2
0.24
0.28
0.32
0.36
0.4
Momentwings_1 VMAV N cm
Momentwings_2 VMAV N cm
Momentwings_3 VMAV N cm
Momentwings_4 VMAV N cm
Momentwings_5 VMAV N cm
VMAV
mph
CD_5 0.05Max. Moment --------->
CD_4 0.04
CD_3 0.03
CD_2 0.02
CD_1 0.01
Moment on Wings (N*cm) vs. Velocity of MAV (mph)
Maximum Torque on Wings@ Maximum Velocity (25mph)
TorqueWings 0.376N cm
Torque Provided by Servo (UsingLowest Torque from Servos Chosen)
TorqueServo 4.3 oz in( ) g
TorqueServo 3.036N cm
Design Analysis – LinkagesDesign Analysis – Linkages
0 10 20 30 40 50 60 70 80 90170
180
190
200
210
220
230
240
250
260
270
280
4 in deg
in
deg
4 0deg( ) 270deg
4 90deg( ) 180deg
Design Analysis – LinkagesDesign Analysis – Linkages
0 9 18 27 36 45 54 63 72 81 90135
137
139
141
143
145
147
149
151
153
155155
135
3 in deg
900 in
deg
0.2 0.25 0.3 0.35 0.4 0.45 0.5 0.550.15
0.11
0.064
0.021
0.021
0.064
0.11
0.15.15
0.15
P y in in
0.55.20 P x in in
Design Analysis – GearsDesign Analysis – Gears
Teeth on pinion/gear
Np 22 Ng 33
Gear Ratio
mG
Ng
Np
mG 1.5
Diameter of pinion
dp
Np
pd
dp 0.183in
Diameter of gear
dg
Ng
pd
dg 0.275inTorque on pinion shaft
Tp .0376N cmrp 0.092in
Bending - Stress
b_pinion 206.05psi b_gear 191.827psi
Safety Factors
Nb_pinion 53.628 Nb_gear 57.604
Servos Cost AnalysisServos Cost Analysis
Servos Weight Torque Speed Supply Voltage Dimension CostBlue Arrow 3.9g 0.31 kg*cm 0.12sec/60deg 4.8V 19.6mm x 17.6mm x 8mm 16.95$ Cirrus CS 4.4g 1.30 kg*cm 0.10sec/60deg 4.8V 18mm x 7.5mm x 15.7mm 29.99$ Micro JST 3.0g 0.50 kg*cm 0.12sec/60deg 4.8V 20mm x 6mm x 6mm 49.99$
HE 490 4.8g 0.72 kg*cm 0.08sec/60deg 4.8V 20mm x 7mm x 16mm 19.95$ Hitec HS-55 7.9 g 1.10 kg*cm 0.17sec/60deg 4.8V 23mm x 12mm x 24mm 16.49$
BA-TS 4.3g 0.40 kg*cm 0.12sec/60deg 4.8V 19.6mm x19.6mm x 8mm 14.50$
Blue Arrow Cirrus CS Micro JST HE 490 Hitec HS-55 BA-TS
Connectors & Rods Connectors & Rods Cost AnalysisCost Analysis
Rod Material Type Diameter Weight Cost Round Carbon Fiber Carbon Fiber Round .02 in - .125 in 0.27g - 11.0g $1.50 - $3.50Flat Carbon Fiber Carbon Fiber Flat .02 in - .09 in 2.2g - 17.7 g $2.15 - $8.00Micro Pushrod System Aluminum Round 0.32 in N/A $4.95K-Mac Fiberglass Rod Fiberglass Round .125 in - .375 in N/A $4.26 - $7.76
Connector Material Type Diameter Weight Cost Mini E/Z Connector Aluminum Round N/A 0.25g $2.49Micro Horns Plastic L shape 0.5 in N/A $1.00
Gears Cost AnalysisGears Cost Analysis
Material Number of teeth Pressure Angle Face Width PriceAcetal 22 20 deg 0.187 8.29$ Nylon 24 20 deg 0.375 2.09$
2024 Aluminum 22 20 deg 0.125 12.98$ 303 Stainless Steel 22 20 deg 0.125 14.38$
Pro-E DrawingsPro-E Drawings
Pro-E DrawingsPro-E Drawings
Pro-E DrawingsPro-E Drawings
Current WorkCurrent Work
Incorporate Fuselage from Sponsor
Compile component order list
Continue researching component material
Future WorkFuture Work
Construct several prototypes of the MAV
Test the deployment systems
Operations Manual
Webpage
Final Report
Open House
SummarySummary
ObjectivesWing ConceptsDeployment MechanismsDesign AnalysisCost AnalysisCurrent WorkFuture Work
ReferencesReferences
http://www.eflightdesigns.com/cgi-bin/products.cgi?CAT=23
http://www.nyblimp.com/superior/carbon-rods.htm
http://www.robotcombat.com/marketplace_carbonfiber.html
http://www.stevensaero.addr.com/e-flight_servos.html
http://www.hobbypeople.net/gallery/877815.asp
http://www.nyltite.com/L20.html
https://sdp-si.com/eStore/
http://www.nyblimp.com/superior/DB.htm
QUESTIONS ???QUESTIONS ???