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1
Oculus Superne
Andy Cottle Sean DuncanLin Haack Afzaal Hassan Brian Roth Dave Stinson Jeff Studtman Justin Wheeler
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
2
CoDR Overview
• Introduction• Mission Statement
& Market• Operations• Walk Around• Payload and
Capabilities
• Aircraft Sizing• Aerodynamics• Stability/Trim• Propulsion• Structures• Cost Analysis• Summary
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
3
Mission Statement
• To provide a multi-service UAS which acts as the primary detection method for third party infringement of pipelines, performs power-line equipment inspection, and detects threats to forested areas. The system will also facilitate a rapid response in the event of a complete system failure or natural disaster.
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
4
Target Market
Mission• Power Line• Pipeline• Forest Monitoring
• Business Plan• Target Customers
• DOT• NPS• Private Oil/Gas Companies
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
5
Customer Attributes
• Patrolling the Right-of-
Way
– Third Party Infringement
• Constant Coverage
• Cost Reduction
• Safety Factors
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
6
Engineering RequirementsEngineering
AttributesImportance (Absolute)
Improtance (Relative)
GPS Accuracy 243 10.90%Number of Operators
225 10.09%
Sense and Avoid Accuracy
211 9.47%
Engine Efficiency 201 9.02%Communication
Relay Time 190 8.52%
Empty Weight 162 7.27%Number of Systems
162 7.27%
Operational Altitude
134 6.01%
Endurance 124 5.56%
Payload Capability 123 5.52%
Time between Overhauls
118 5.29%
Operational Speed
107 4.80%
Stall Speed 93 4.17%T/O Length 87 3.90%
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
7
Operation Profile• Type of Equipment
– Ground Stations– Relay Stations– UAV
• Takeoff/Landing on Rough Airfield• Operate from 1000 ft (AGL)• Observe & Transmit to Local Relay Stations• Relay Stations Transmit Information Back to
Operator• Number and Frequency of UAV Flight Completely
Customer Defined
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
8
Walk Around1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
9
Internal Walk Around1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
10
Sensors• LIDAR (Laser Imaging
Detection and Ranging)– Corridor Mapping– Land Surveying– Vegetation Growth / Density LiteMapper 5600 components
Airborne Lidar Terrain Mapping System
• IR/Visual Camera
- Thermal Imaging
- Video Tracking
- Detailed Pictures
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
11
Payload RequirementsWeight (lbs) Dimensions (ft) W hp
LIDAR 13 1.8x.66x.71 30 0.04CCNS 9 .82x.69x.43 25 0.034
IR / Visual Camera 20 .66(d)x1.1(h) 100 0.134Total 42 1.5 ft3 155 0.21
Power From Alternator N/A N/A 1500 2
Installation Weight (40% of Total Payload Weight)
Power Consumption
17 N/A N/A N/A
• LIDAR
– Operates Optimally at 650-1300ft AGL
– Used Only During Inspection
• IR / Visual Camera – Runs Throughout Mission– @ 1000 ft AGL
• 271,212 ft2
– @ 12 x Zoom• 1462 ft2
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
12
Sizing Information and Assumptions
• Sizing Code: Avid ACS v4.1
• Equation Sets– General Aviation Component Weight
Equations– Tail Volume Coefficient
• Fixed Engine – Weight – Horsepower
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
13
Carpet Plot Constraints and Inputs
• Constraints– 925 ft takeoff
constraint (ground roll + 50 ft obstacle clearance)
– 550 ft landing constraint
– Stall speed, ceiling and 2g maneuver not influential
CLmax 1.5
Cruise altitude 5000
Velocity [kts] 100
Range [n.m.] 1300
Payload Weight [lbs] 60
Engine Weight [lbs] 48
Power [hp] 40
Propeller Diameter [ft] 2.5
[ft] MSL
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
14
Carpet Plot
250
252
254
256
258
260
262
264
266
268
Wing Loading [lbs/ft2]
Gro
ss
Ta
ke
Off
We
igh
t [l
bs
]
AR =10 AR = 12 AR = 14
AR = 16 Landing Constraint Take Off Constraint
Sto = 925 SL = 550ft
AR = 10
AR = 12
AR = 14
AR = 16
W/S = 18 [lbs/ft2]
W/S = 20 [lbs/ft2]
W/S = 22 [lbs/ft2]
Design Point
Feasible area
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
15
Sizing Code OutputGross Weight [lbs] 255
W/S 20.3
Aspect Ratio 10
Wing Area [ft2] 12.55
Endurance [hrs] 14.388
Take off Distance [ft] 915.6
Landing Distance [ft] 537.7
Fuel Weight [lbs] 39
L/D 13
Power/Weight [hp/lbs] 0.15ηp 0.821
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
16
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
17
Compliance MatrixParameter Targets Threshold CurrentGross Weight [lbs] 300 500 255Payload Capability Installed [lbs] 30 50 60Endurance [hrs] 24 12 14
SFC at Cruise [lb/bhp/hr] 0.4 0.6 0.48
Operational Altitude [ft AGL] 1000 2000 1000
Loiter Velocity [kts] 150 100 100
Stall Speed [kts] 30 40 60
Takeoff Length w / 50ft obstacle [ft] 500 1500 936
GPS Accuracy [in] 4 20 4
Propeller Efficiency 0.9 0.7 0.82
Number of Operators 2 4 2
Communication Relay Time [secs] 5 10 -
Sense and Avoid Accuracy [ft] 1 5 -
Time between Overhauls [hrs] 2000 750 600
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
18
0 50 100 150 200
-1
-0.5
0
0.5
1
1.5
2
Ve (knots)
n
V-n diagramPerformance
Takeoff Velocity
Landing Velocity
75 kts
80 kts
60 ktsStall Velocity @ 5000 ft MSLand 85% GTOW
Operational Velocity 100 kts
50 100 150 200 2500
0.5
1
1.5
2
2.5
3
3.5
4
4.5x 10
4
Airspeed (knots)
Alti
tude
Flight Envelope
n=1
n=2
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
(ft
MSL)
19
Lift Distribution
• Ideal Elliptical Lift(Too costly)
• Linear distribution cost effective
• Still gives acceptable performance
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
(ft2
/sec)
20
Airfoil selection
Alpha Versus L/D
-25
0
25
50
75
100
125
150
175
200
-5 0 5 10 15
Alpha
L/D
NLF1015
LNV109a
NACA 642-415
• Considered 3 airfoils– NASA NLF-
1015– Liebeck
LNV109a– NACA 642-415
(baseline)
• Chose NLF-1015– Superior L/D at
operating conditions (Low alpha)
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
21
Drag Buildup• Component CD0 build for major components
of aircraft
• CD0 - parasite drag on the aircraft
CD,misc 0.015CD0,wing 0.000635CD0,tail 0.000224CD0,Fuselage 0.0017CD0 0.0176
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
22
Lift curve slope
-0.5
0
0.5
1
1.5
2
-5 0 5 10 15
alpha
Cl
LNV109a
NACA 642-415
NLF1015
Aerodynamic performance, lift, and drag from XFoil at Mach number for cruise
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
23
Longitudinal Stability Analysis
• Static margin for a fully loaded aircraft 34%
• Static margin with no fuel 41%
Xcg .467 %
CLα .14
Xac,wing .46 %
Xac,ht .932%
Cmα -.048
Static Margin
.343
(Percentages of Aircraft Length)
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
24
Cruise Trim: V = 100 kts, q = 32.46 => C_L = .4467
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
25
Lateral Trim• Crosswind correction
– Capable of steady level flight in a crosswind that is 30% of takeoff speed at a 11.5o side slip angle with no more than 20o of rudder deflection.
• Final sizes:– Rudder: cf/c = 0.8– Aileron: cf/c = 0.2
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
26
Engine Selection
• UAV Engines Ltd– Model AR741
Max Power [hp] 40
Cruise RPM 7000
Engine weight [lbs] 23.5
Installed Weight w/ Generator [lbs] 48.2
Generator Capacity [V] 28
Generator Output [W] 1500
Fuel Type Auto Gasoline
Engine Specifications
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
27
Propeller Selection• Helices Halter
– Model HH yr7022fa
• Specifically designed for the AR741 Engine
• Fixed Pitch• Beech Wood
Composite
C_Root [in] 2.5Diameter [ft] 2.5Advance Ratio 0.675Coefficient of Power 0.083Taper Ratio 0.52Activity factor 80Blades 2Twist 22.5Propeller Efficiency 0.824
Propeller Specifics
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
[deg]
28
Material Selection• Al-2024 for the fuselage
and Al-7075 landing gear.• Aluminum inexpensive,
$3-4/lb• Strong (E = 106 psi) and
light • Resists corrosion and has
good fracture toughness properties
• AS4/3501 -6 Carbon Epoxy for the wing and tail skin
Mechanics of Materials, James Gere
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
29
Weight StatementWeight (lb)
Wing 25
Fuselage 25
V-Tail 8
Nacelles 5
Landing gear 7
Total 70
Engines 48
Fuel Systems 3
Total 51
Hydraulics 3
Electrical 15
Avionics 12
Flight Controls 5
Total 35
Propulsion
Fixed Equipment
Airframe StructureWeight (lb)
Unusable Fuel and Oil 1Fuel 39
Lidar 13CCNS 9Camera 20
Total 42
Operating Items
Payload
Total Component Weight (lb)
Empty Weight 155
Fuel 40
Installed Payload 60
Total 255
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
30
Reliability and Maintainability
• Minimal Maneuvers
• Steady Static Margin
• Minimal Parts– Non-retractable Landing Gear– Few Payload Parts
• Highly Reliable Data from Sensors
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
31
Cost Analysis Life-Cycle
• Modified around DAPCA IV Cost Model• Scaled to a UAV application• Analysis based off of Trans-Alaskan Pipeline
Customer
Break Down CostProduction Cost $50,000.00RDT&E $993,000.00Cost Per Aircraft $62,600.00Break Even Point 80 UAVs @ 5 years
Operation & Maintenance cost (per year) $154,000.00Operation Cost Per Day $428.00Cost Per Mile (1600 Miles of Pipeline) $0.27
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
32
Summary• Future Work
– More Structural Analysis
– CFD Analysis– More Research In
Operation Costs
Parameter Targets Threshold Current
Gross Weight [lbs] 300 500 255Endurance [hrs] 24 12 14Takeoff Length [ft] 500 1500 936Payload Capability Installed [lbs] 30 50 60Loiter Velocity [kts] 150 100 100
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary
33
Questions?
1.) Introduction
2.) Mission & Market
3.) Operations
4.) Walk Around
5.) Payload
6.) Aircraft Sizing
7.) Aerodynamics
8.) Stability/Trim
9.) Propulsion
10.) Structures
11.) Cost
12.) Summary