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RequirementsMission profileWork ProgressUCAVs and system survey
�Existing UCAVs �Armament �Engines�EO/IR sensors �SAR �Satellite comm. �Avionics�Aerial refueling�Yaw Control
Conceptual design �RCS�Definition of two configurations �Initial Sizing�Definition of required thrust �Comparison of configurations with one/two engines
ContentContent
�Engine selection�Weight Breakdown�Airfoils
Preliminary Design�Landing gears�Aerial refueling / Fuel lines�Performance�Layout
Comparison of the two final configurationsConfiguration SelectionSummarySecond Semester Tasks
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Requirements:Requirements:Operation range of 2000 NM with refueling capability
Armament carrying capability of 2x500[kg] smart bombs
BVR (beyond visual range) Capability
Stealth Capability
Capability of carrying EO/IR sensors operating in all
weather conditions, including night time target acquisition
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Mission profileMission profile
1) Taxi To Runway2) Warm-up3) Takeoff4) Climb to 36,000 ft5) Cruise @ M=0.8 for 1,000 nm6) 20 min loiter over target7) Cruise @ M=0.8 for 500 nm8) 10 min loiter for aerial refuel9) Descend to S-L10) Landing and Taxi.
36,000 ft
1,000 nm 500nm20 min 10 min
1 2 3
4 5 6 7 89
10�
Mission RangeMission Range
750 NM – Combat Radius
1500 NM – Max Range
1000 NM – Mission Radius
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Work Process Work Process –– Flow ChartFlow Chart����������
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MQ-9X-45 CX-45 ANeuronBarracudaX-47 BX-47 A
10,000������12,20013,0007,100������5,500Weight [Lb]
3,2002,500350470unknown3,200unknownRange [NM]
����������1,500unknown660�����1,000Ammunition Weight [Lb]
Turboprop
TurboFan
TurboFan
TurboFan
TurboFan
TurboFan
Turbo Fan
propulsion
lowfullfullfullpartialfullfullStealth capability
operational cancelledActive
Demonstratorin DevelopmentCancelled
Prototypebuild
completed
ActiveDemonstratorStatus
UCAVs Survey UCAVs Survey
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Armament SurveyArmament SurveyMain requirements:
Minimum size (length and diameter)
Maximum glide range
High accuracy
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Armament SurveyArmament Survey
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Pratt & Whitney PT6
Honeywell TPE-331-10
Heron 2
Reaper
Propulsion SurveyPropulsion SurveyTurboprop
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Pratt & Whitney F100-220
Honeywell F124-GA-100
Pratt & Whitney JT15D-5C
X-45A
X-47A
X-47B
Turbofan
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EO/IR sensors SurveyEO/IR sensors Survey
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TopliteSonoma 474MX-15 True HDStar SAFIR HD
RAFAELL-3WESCAMFLIRManufacture
Turret:59Turret:86.4Turret:46.72MCU:9.07
TFU:45CEU:10.4
Weight(kg)
662x406Outside dia. 528476x394450x380Size[mm]
MIL-STD-810MIL-STD-461
MIL-STD-810MIL-STD-461
MIL-STD-810MIL-STD-461
MIL-STD-810MIL-STD-461
-40-50[°c]
Endurance
4axisLOS
stabilization<0.7mrad
5 axisLOS
stabilization<2urad
6 axisLOS
stabilization<6urad
6 axisLOS
stabilization<5urad
Stabilization
Not mentioned
IR:640x512IR:640x512CCD:470TV
lines
IR:1280x720CCD:1280x720
Resolution
Not mentioned
Not mentionedyesyesDay and night vision
Not mentioned
202025Laser Range[km]
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EO/IR sensors SurveyEO/IR sensors Survey
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Selected Alternative:
Main requirements:Day & night detection ability
Detection range: height: 10.67[km] (36,000 ft)
horizontal range:9.75[km] (5.4 NM)
Minimum decrease in stealth capability
The EO sensor will be custom made to fit our configuration in a way that minimizes RCS increase.We will use the parameters of the selected alternative.
��
Weight[Kg]Power[W]Frequency[GHz]Rangemodel
5.5753510Km@1-meter"Honeywell"
38800---35 Km"EL/M-2055D"
50850---50 Km"EL/M-2055DX"
12.26016.810Km@4-inch15Km@8-inch23Km@12-inch
“SANDIA-MiniSAR"
Honeywell EL/M-2055D
EL/M-2055DX SANDIA-MiniSAR
SAR SurveySAR Survey
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Weight[Kg]Gain[dB]Frequency[GHz]
Angle coverage[deg]Model
---------0-180"Gimbaled"
45.44210.7-14.510-170"MIJET"
233910.7-14.50-180"MIJETLite"
---3610.7-14.518-65 (each side)"MiniMIJET"
Satellite Communication SurveySatellite Communication Survey
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Avionics SelectionAvionics Selection
GPS/INS – model:” LN-100G”.Lightweight, High MTBF, Low power consumption,Military proven hardware.
Receiver/Transmitter – model:” ARC-210”.Provides services for both the Ku and the C band
antennas, Resistant to jamming.
Identification Transponder – model:” APX-���“.Small ; (limited to line of sight-UHF).
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280x180x180
125x145x165
135x120x210
��C96���;���C65691�$�;����
C-band antenna – model:” ANT5812SN”. Small, Lightweight, Low power consumption.
210x180x45��
Aerial Refueling SurveyAerial Refueling SurveyTwo approaches:
1. “Hose & Drogue”Does not require an operator for the hose.Simultaneous refuel of several crafts capability.
2. “Boom & Receptacle”Does not require a drogue which sticks out of the receiving aircraft.Easy to make contact to refuel (boom operator’s job).The boom is rigid and less susceptible to wind perturbations.The mass fuel flow is greater.
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Yaw control SurveyYaw control Survey
ConsProsYaw moment created by�
PictureControl method
Few information about this
control method
Very low RCS
increment
Upper spoilers with inclinationopening forward
Forward opening spoilers
High couplingwith roll
Light weight
Two elevonsopen in opposite
directions
Crow-mixing
High RCS increment
High moment
Upper and lower spoilers Spoilers
Low RCS increment
Control surface splitsSplitters
• Complexity • High weight
Low dependence
of flight speed
Change of thrustdirection
Thrust vectoring
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RCS (Radar Cross Section)RCS (Radar Cross Section)
The RCS is mostly affected by:RadomeCavitiesLeading edgesFlat sides of fuselageCorner reflectionSurface currents that scatter at discontinuityProtruding elements
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There are several ways to reduce RCS
Minimize reflecting directions
Use of special weapons bays
Upper and curved intake to conceal the
engine compressor�s facing
Slanted/without vertical stabilizer
Use of Radar Absorbing Materials
��
Definition of two configurationsDefinition of two configurations
The design will be based on a flying wing configuration.
We simultaneously developed two configurations :
“Delta” configuration“Zigzag” configuration
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Configuration and AirfoilsConfiguration and AirfoilsFlying wing configuration was selected to meet stealth requirements
Advantages:High fuel efficiency (high L/D)Light weight (Less materials required )Low drag
Disadvantages:Lateral and longitudinal instabilities
Loss of lift due to elevator deflections
Difficulty to create pitching moment
Therefore special care should be applied for the stability margin
Recommended approach:Use of reflex or reverse camber
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Initial size estimationInitial size estimation
Assumption of L/D
Calculation of fuel fracture required for the mission for given L/D
Relation between empty and take-off weight
Comparison with�OtherUCAV’s Yieldstake-off weight�
L/D�Calculation offrom drag polarBased on take-off weight
This is an iterative methodwhich stops with the convergence of take-off weight�
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Initial size estimation�for the two configurations �
The two configurations have the same take-off weight however the delta carries more fuel.��
Assuming Thrust/Weight of 0.38 (average of other UCAV’s)we will need an engine that gives 5700 [Lb] thrust.
Thrust required:
5700 [Lb]
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Comparison parameters
single engine configuration
Twin engines configuration
Engine model P&W pw306A P&W JT15-5D
Volume 932�[lit] 2x563.5=1127�[lit]
Weight 1043�[lb] 2x627=1254�[lb]
Thrust 6400�[lb] 2x3045=6090�[lb]
TSFC 0.394�[lb/hr/lb] 0.55��[lb/hr/lb]
Redundancy One engine Two enginesAccompanying system weight
330�[lb] 430�[lb]
Inlet Weight 150[lb] 310[lb]Inlet Area 4�[ft^2] 4.5[ft^2]Nozzle Weight 21[lb] 30��[lb]
Nozzle Area 2.7�[ft^2] 3[ft^2]
Comparison between single and Comparison between single and twin engine configurationtwin engine configuration
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EngineEngine
Model P&W pw306A
Honeywell AS907
CFE 738-1-2B
PovazskeDV-2A
Rolls Royce Adour MK871
Thrust 6400 [lb st] 6500 [lb st] 5725 [lb st]
5693 [lb st]
6030 [lb st]
Weight 1043 [lb] 1364 [lb] 1325 [lb] 1389 [lb] 1330 [lb]Length 75.6 [in] 90 [in] 99 [in] 68 [in] 76.7 [in]Fan diameter
31.6 [in] 34.2[in] 34.4 [in] 25.4[in] 30.9 [in]
TSFC 0.394 [lb/hr/lb]
0.42 [lb/hr/lb]
0.372 [lb/hr/lb]
0.595 [lb/hr/lb]
BPR 4.5 4.5 5.2 1.16 0.8
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The selected engine is : P&W pw306A
Thrust:6400 [lb st]Weight: 1043 [lb]Fan diameter: 31.6 [in]TSFC min:0.394 [lb/hr/lb]
Conclusion:The selected engine has some advantages over the other engines
Lightest engineGrowth possibilityOne of the shortest enginesGood TSFC
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Weight BreakdownWeight Breakdown
Component Weight [lb]Wing 1009.1
Fuselage 1576.7
Engine 1043
Air induct 177.3
Tailpipe 60.2
Nose landing gear 193.2
Main landing gear 851.9
Propulsion system 177.5
Fuel system 445.4
Hydraulics 171.7
Electrical system 454.3
Avionics 1159.5
Flight control 375.5
ECS + Anti-icing 171.7
Handling gear 4.8
Total empty weight 8658
Component Weight [lb]
Wing 1164.1
Fuselage 1702.9
Engine 1043
Air induct 177.3
Tailpipe 60.2
Nose landing gear 193.1
Main landing gear 851.6
Propulsion system 177.5
Fuel system 435.5
Hydraulics 171.7
Electrical system 454.3
Avionics 1159.5
Flight control 381.6
ECS + Anti-icing 171.7
Handling gear 4.8
Total empty weight 8973
Delta Zig-Zag
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Component Weight [lb] Location [ft]
Wing 1164.1 11.64
Fuselage 1702.9 10.51
Engine 1043 13.02
Air induct 177.3 7.44
Tailpipe 60.2 20.06
Nose landing gear 193.1 2.88
Main landing gear 851.6 13.65
Propulsion system 177.5 13.02
Fuel 3257.9 12.03
Aerial refuel 294.6 8.34
Hydraulics 171.7 13.02
Electrical system 113.6 3.56
Avionics 1159.5 3.56
Flight control 127.2 17.54
Armament 2205 10.54
Misc (spread) 779 10.7
Weight Reserve 816 10.7
Rear C.G. 14300 10.7
Forward C.G. 9114 10.2
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. . 0 Forward
. . 3.3%
8.84%
5.54%C G
C G
C G MAC
X N MAC
X N MAC
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Weight BreakdownWeight Breakdown
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Weight BreakdownWeight Breakdown�5 5�;�����������!���C
Component Weight [lb] Location [ft]
Wing 1009.1 13.86
Fuselage 1576.7 9.24
Engine 1043 13.8
Air induct 177.3 9.51
Tailpipe 60.2 19.75
Nose landing gear 193.2 5.16
Main landing gear 851.9 14.04
Propulsion system 177.5 13.8
Fuel 3750.8 11.21
Aerial refuel 294.6 11.17
Hydraulics 171.7 13.8
Electrical system 113.6 4.26
Avionics 1159.5 4.26
Flight control 125.2 18.04
Armament 2205 10.56
Misc (spread) 764 10.84
Weight Reserve 787 10.84
Rear C.G. 14460 10.84
Forward C.G. 8797 10.73
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. . 0 Forward
. . 0.7%
4.6%
5.3%C G
C G
C G MAC
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Airfoil SelectionAIRFOILMAX.
THICKNESSMAX. CAMBER
EPPLER32512.62% at 34.3%1.75% at 16.3%
EPPLER32612.86% at 33.4%2.17% at 19.5%
EPPLER36012.23% at 36.9%1.54% at 27.2%
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Landing gearsLanding gearslanding gears arrangement selection: Tricycle
Load limitations:
0.05aMB
� 0.2fM
B�
a3
a1 a2
a4
DeltaZig-zagCriterion11.511.5a1 [deg]25.618.73a2 [deg]1515a3 [deg]
49.8640.1a4 [deg]0.1540.116Ma/B0.170.17Mf/B
44H [ft]1.071.07Ma [ft]6.959.24B [ft]
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Aerial Refueling/Fuel Lines Aerial Refueling/Fuel Lines
Selected system: ”Boom & Receptacle”.The boom is standard and has a diameter of 200 mm which is derived using dimension analysis.The receptacle is of a unique designenabling it to grasp and detach the boom.
Fuel LinesFuel systems can be classified in two broad categories:
1. Gravity-Feed Systems.2. Pressure-Feed Systems.
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The fuel lines which carry the fuel from the receptacle to the fuel tanks can use the gravity feed approach.The fuel lines that carry fuel from the fuel tanks to the engine, however, have to utilize fuel pumps; (the fuel pumps are integral in the fuel tanks).
Top View:
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Refueling time calculation:For Zig-Zag : t=0.577[min]=35[sec]
For Delta: t=0.667[min]=40[sec]
Typical fuel pressure in fuel lines: 20[ ]P Psi���
Takeoff distance:
For Delta configuration takeoff distance is 1.15kmFor Zig-Zag configuration takeoff distance is 1.22km
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Performance AnalysisPerformance Analysis
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Landing distance:
For Delta configuration landing distance is 1.03kmFor Zig-Zag configuration landing distance is 1.19km
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Performance AnalysisPerformance Analysis
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Takeoff rotation:
For Zig-Zag with elevon angle is 13.9°For Delta with elevon angle is 5.7°
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212
0.9 cos
e e
e e
TO a TO ref CP CG a L e
elevonsL e l
ref
W M H V S X X M C
SC K C
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Performance AnalysisPerformance Analysis
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Climb Rate:� � � �
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climbclimb
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climb 00
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Dver
DD
V CT K WV V SWW VS
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Altitude [ft]
Climb Rate
[ft/min]
Climb Velocity
[kts]
Mach Number
10,000 7204 333 0.58
20,000 6485 362 0.63
36,000 4606 409 0.71
Altitude [ft]
Climb Rate
[ft/min]
Climb Velocity
[kts]
Mach Number
10,000 7513 350 0.61
20,000 6763 379 0.66
36,000 4869 425 0.74
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Performance AnalysisPerformance Analysis
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Flight envelopes:
Delta
Zig-Zag
Performance AnalysisPerformance Analysis
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LAYOUTLAYOUT
Delta Configuration DevelopmentDelta Configuration Development
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ZigZig--Zag Configuration DevelopmentZag Configuration Development
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Delta ConfigurationDelta Configuration
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Zag ConfigurationZag Configuration--ZigZig
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Delta AnimationDelta Animation
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ZigZig--Zag AnimationZag Animation
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Delta interior componentsDelta interior components?������-E��7��!�������#����� ��F%&�� �'���������������F����������%???���+���������7��!�������;G$%�������#��7
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ZigZig--Zag interior components Zag interior components
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Delta Section View AnimationDelta Section View Animation
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ZigZig--Zag Section View AnimationZag Section View Animation
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DeltaZig-ZagCategory14,460 [lb]14,300 [lb]Weight3,600 [lb]3,117 [lb]Fuel weight34.1AR
36 [lbf/ft^2]30 [lbf/ft^2]Wing loadingP&W pw306AP&W pw306AEngineEppler 360Eppler 360Airfoil40,000 [ft]46,000 [ft]Flight ceiling 1.15 [km]1.22 [km]Takeoff distance
5.7°13.9°Takeoff rotation (elevon angle)1.03 [km]1.19 [km]Landing distance40 [sec]35 [sec]Aerial refueling time
4606 [ft/min]4869 [ft/min]Climb rate (36,000 [ft])Stable Unstable Longitudinal stability 32No. of reflecting surfaces (RCS)
Configuration ComparisonConfiguration Comparison
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Chosen ConfigurationChosen Configuration
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Operation range of 2000 NM with refueling capability
Armament carrying capability of at least 2x500[kg] smart bombs
BVR (beyond visual range) Capability
Stealth Capability
Capability of carrying EO/IR sensors operating in all weather
conditions, including night time target acquisition
SummarySummary
Goal achievement:
��
Second Semester TasksSecond Semester Tasks
Detail design and Analysis of:
Wing structure
Landing gear
Control surfaces
Flight control system
Evaluation of RCS
Wind tunnel test:
Design of wind tunnel model
Manufacture of wind tunnel model
Conducting wind tunnel test�
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