UCAVs and system survey - Dror Artzi · 2013-01-20 · Engine 1043 Air induct 177.3 Tailpipe 60.2...

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

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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




-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.

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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).

B��

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

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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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Weight BreakdownWeight Breakdown

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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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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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Takeoff rotation:

For Zig-Zag with elevon angle is 13.9°For Delta with elevon angle is 5.7°

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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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Flight envelopes:

Delta

Zig-Zag


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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:

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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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UCAVs and system survey - Dror Artzi · 2013-01-20 · Engine 1043 Air induct 177.3 Tailpipe 60.2...

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Transcript of UCAVs and system survey - Dror Artzi · 2013-01-20 · Engine 1043 Air induct 177.3 Tailpipe 60.2...