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nullHARP - High Altitude Reconnaissance Platform Design ProposalHARP - High Altitude Reconnaissance Platform Design ProposalDr. James D. Lang, Project Advisor Dr. Leland M. Nicolai, Project Sponsor Dr. Paul A. Wieselmann, Project SponsorSteven H. Christenson –Team Leadhttp://www.panoramio.com/user/500685/tags/DARPA Ceazar C. Javellana III Marcus A. ArtatesPresentation OverviewPresentation Overview-Define Requirements -Design Process and Assumptions -Aircraft Configuration/Sizing -Weight Breakdown -Mission Analysis and Compliance -Aerodynamics -Performance-Propulsion -Stability and Control -Materials and Structure -Cost Estimations -Future Work -References and AcknowledgementsRequirementsRequirementsProvide 24/7 ISR Coverage with 2 Aircraft 2000 nm Radius for ISR Mission 10500 nm Ferry Flight 6963 lb Payload (Installed Weight) -(4) X Band Radar Arrays – 3.3 x 6.1 ft -(2) UHF Radar Arrays – 4.9 x 40.6 ft Minimize Take-off Weight and Life Cycle CostDerived Requirements for 24/7 Coverage with 2 AircraftMission Endurance 2*(One-Way Transit) + Time on Station Time on Station 2*(One-Way Transit) + Turnaround Time Derived Requirements for 24/7 Coverage with 2 AircraftISR MissionISR MissionDescend to Sea LevelClimb to Cruise AltitudeCruise Out 2000 nmCruise Back 2000 nmLoiter 16 Hours (TOS)Sea Level Loiter for 30 min55000 ftDistance (nm)2000 nmMax Distance Ferry Mission Max Distance Ferry Mission Descend to Sea LevelClimb to Cruise AltitudeCruise 10500 nmSea Level Loiter for 30 min55000 ftDistance (nm)10500 nmDesign ProcessAssume Wto and W/SSize Wing Calculate Component Weights Calculate Fuel FractionsYes/NoDetermine Fuel AvailableFuel)aval> Fuel)reqdDetermine Fuel Required for MissionAerodynamics Size Engine PerformanceAR, Taper, Sweep Fuselage Sizing and Shape Estimate Tail SizeStudy Mission Requirements Refine Wto and W/S EstimatesRefine Aerodynamic Parameters Size Control Surfaces/Tail Calculate Drag Determine Performance CapabilitiesMission Requirements Met?Refine Wto and W/S Optimize Design-Assumptions Made/Refined--Configuration Assumptions Made/Refined to Meet Mission Requirements-Design ProcessYes/NoAircraft ConfigurationAircraft Configuration-L/D)max,wing = 35 for 0 deg Sweep, 20 AR, 60% Laminar Flow Lockheed Martin Aerodynamic Data -2250 lb Thrust, .55 TSFC for 2015 Advanced Technology Turbofan Engine at Full Power and 55000 ftDesign Analysis Based on the Following Assumptions:Aircraft ConfigurationAircraft ConfigurationWto = 50000 lb W/S = 60 lb/ft^2 Wing Area = 833 ft^2 Wing Span = 129 ft Wing Sweep = 0 deg Aspect Ratio = 20Radar GeometryRadar GeometryX Band Radar (4) -3.3 x 6.1 ft -Azimuth Field of Regard (FOR) +/- 70 degrees -Located to give 360 Degree Coverage UHF Radar (2) -4.9 x 40.6 ft -Azimuth FOR +/- 70 degrees -Located to View Out Each SideHorizon DistanceHorizon DistanceDesign Array Angles for Desired FootprintAircraft ConfigurationAircraft ConfigurationWing Area = 833 ft^2 Wing Span = 129 ft Wing Sweep = 0 deg Aspect Ratio = 20Fuselage Length = 62 ft Height = 6 ft Width = 10 ftAircraft ConfigurationAircraft ConfigurationAircraft ConfigurationAircraft ConfigurationWing Fuel TankCenter of Gravity & Aerodynamic CenterWeight Fractions -ISRStart up/Take-Off .970 Climb to Cruise Alt .950 Cruise Out .902 Loiter on Station .754 Loiter Fuel 10219 lb Maneuvering Fuel 671 lb Cruise Back .902 Descend to SL 1.00 Loiter 20 min .994Take-Off Weight 50000 lb Fuel Weight 23874 lb Fuel Fraction .48 Fuel Volume 3511 galWeight Fractions -ISR-Cruise at .943*L/D)max -Loiter at L/D)max(1) 2015 Technology Turbofan Engine SLS Thrust = 8000 lb SLS TSFC = .40 T/W = .16ISR Mission Compliance-16 Hour TOS- Cl = .864 L/D)max = 31.52 Mach .6 and 55000 ft ISR Mission ComplianceMission Endurance 2*(One-Way Transit) + Time on Station = 2*(5.52) + 16.2 hr = 28.4 hr Time on Station 2*(One-Way Transit) + Turnaround Time = 12.2 hr + 4 hr = 16.2 hr -Two Aircraft Coverage--2000 nm Range- Cl = .628 L/D = 29.72 Mach .6 and 55000 ft Total Mission Fuel Required: 23874 lb = 3511 galWeight Fractions - FerryWeight Fractions - FerryStart up/Take-Off .970 Climb to Cruise Alt .950 Cruise 10500 nm .567 Descend to SL 1.00 Loiter 20 min .994Take-Off Weight 50000 lb Fuel Weight 24685 lb Fuel Fraction .49 Fuel Volume 3630 galDesign Pushed by 10500 nm Ferry Flight Approx 800 lb Additional Fuel RequiredAerodynamicsAerodynamicsAspect Ratio = 20 Span = 129 ft Wing Sweep = 0 deg e = .9 t/c = .15 K = .01768 Taper Ratio = .50 MAC = 6.7 ft Croot = 8.6 ft Ctip = 4.3 ft Airfoil: Modified Lockheed Martin Sensorcraft Wing15% to Provide 60% Laminar FlowAerodynamicsAerodynamicsL/D)max,wing = 35 Lockheed Martin Aerodynamics Data Cdo)wing = .00817 Referenced to Sref Cdo)fuselage = .00369 Referenced to Sref Cdo)tail = .00121 Referenced to Sref Cdo)aircraft = .01393 Calculated with Interference Effects L/D)max,aircraft = 31.52 From L/D vs Cl PlotAerodynamicsAerodynamicsCl = .864 for L/D)max and Minimum Drag Clalpha = 6.9 rad-1 = .12 deg-1 at Mach .6 Stall Velocity Based on Cl)max of 2.0 Candidate High Lift Devices -Mission Adaptive Wing (MAW) -Trailing Edge FlapsAerodynamicsAerodynamicsFuselage Sized to Hold Radar ArraysLength = 62 ft Depth = 6 ft Width = 10 ft Fineness Ratio = 6.2 Volume = 2922 ft^3 Wetted Area = 1067 ft^2 Max Cross Sectional Area = 47 ft^2AerodynamicsAerodynamicsL/D)max = 31.52AerodynamicsAerodynamicsAerodynamicsAerodynamics-Insufficient Data in References to Accurately Calculate MDD -Concern that at Cruise Velocity and Altitude (M .6 @ 55000 ft) Airfoil is Near MDD -Supercritical WingMDD, Drag Divergent Mach NumberPerformancePerformanceLimit Load Factor 1.25 Ultimate Load Factor 1.88 Turn Load Factor 1.15 Maneuvering Turn Rate 1.8 deg/s Dynamic Pres Limit 450 lb/ft^2Stall Velocity 159 ft/s Take-Off Velocity 191 ft/s Take-Off Distance 5000 ft Landing Distance 4000 ft Braking Acceleration –7 ft/s^2PerformancePerformancePerformancePerformancePerformancePerformancePropulsionPropulsion2015 Technology Turbofan Engine Moderate Bypass Ratio 8000 lb Thrust (Sea Level Static) .40 TSFC (Sea Level Static) Dimensions: Length 115 in (9.6 ft) Diameter 41 in (3.4 ft) Engine Weight: 1600 lb System Weight: 3100 lb-Pitot Inlet, 10 ft^2 Capture Area -Fixed Convergent Nozzle, 6 ft^2 Exit AreaPropulsionPropulsionPropulsionPropulsionPropulsionPropulsionAuxiliary PowerAuxiliary PowerRequired Power 128 kW Power Available from Engine 70 kW = .061*Talt Additional Power Required 58 kWTotal Weight 1304 lb APU Fuel Weight 595 lb Total Weight 1899 lbAPU – Continental L/TSIO-360Auxiliary PowerAuxiliary PowerEngine Excess PowerkW = .061*Talt Additional Thrust 957 lb Additional Fuel 8562 lb(T-D)*V = Power Additional Thrust 58 lb Additional Fuel 523 lbAverage Additional Fuel 4542 lbWeight Build-upFuselage 3415 lb Wing 4928 lb Control Surface(s) 2508 lb Tail 297 lb Landing Gear 1677 lb Propulsion System 3100 lb Flight Systems 460 lb Fuel System/Tanks 496 lb Hydraulic System 172 lb Electrical System 849 lb Air Cond/Anti-ice Sys 794 lb Payload (Installed) 6963 lbTake-Off Weight 50000 lb Empty Weight 18697 lb Weight with Payload 25660 lb Fuel Weight Available 24340 lb Fuel Fraction .49 Fuel Volume 3579 galWeight Build-up-Fuselage and Landing Gear Weight Reduced by 15% and 5%, respectively, for 2015 Technology Target Factors Stability and ControlStability and ControlCenter of Gravity and Fuel ScheduleStability and ControlStability and ControlStatic Margin (SM) SummaryStability and ControlStability and ControlCmo = .0681Stability and ControlStability and ControlAilerons Area = 37.9 ft^2 each MAC = 1.47 ft Span = 25.8 ftFlap Chord: 25% Wing Chord at Root Flap Span: 27% of Wing SpanFlaps Area = 38.0 ft^2 each MAC = 2.15 ft Span = 17.7 ftTotal Control Surface Area: 152 ft^2Aileron Chord: 22% of Wing MAC Aileron Span: 40% of Wing SpanStability and ControlStability and ControlV-Tail Cvt = .0145 Svt = 55.7 ft^2 Cht = .34 Sht = 67.7 ft^2 42 deg from Vertical Rudder Area = 18.6 ft^2 = (1/3)Svt Materials and StructureMaterials and StructureCarbon Fiber -Wings -Control Surfaces -Fuselage Fiberglass -Array PanelsMaterial SelectionStructural ConceptSemi-Monocoque Fuselage Structure Carbon Fiber Wing Box, Spars and Landing Gear StrutsMaterials and StructureMaterials and StructureMaterials and StructureMaterials and StructureMaterials and StructureMaterials and StructureMaterials and StructureMaterials and StructureIxx = 2.89E3 slug-ft^2 Iyy = 1.93E5 slug-ft^2 Izz = 6.86E5 slug-ft^2Mass Moments of Inertia Based on Historical DataCost EstimationsCost EstimationsEngineering Hours, Tooling Hours, Manufacturing Hours and Manufacturing Material Costs Based on Historical Data and: -Number of Aircraft Produced -Aircraft Take-off Gross Weight -Maximum Velocity Flight Test Costs Based on Historical Data and: -Number of Flight Test Aircraft -Aircraft Take-off Gross Weight -Maximum Velocity Quality Control Hours Based on Historical Data and: -Manufacturing Hours Development Support Cost Based on Historical Data and: -Aircraft Take-off Gross Weight -Maximum Velocity Engine and Avionics Cost Provided By: -Lockheed Martin Cost EstimationsCost EstimationsHours Engineering 7,568,054 Tooling 4,483,622 Manufacturing 13,472,465 Quality Control 1,791,838Aircraft to be Procured: 100 Flight Test Aircraft: 6Costs Development Support 88,831,854 Flight Test 57,056,356 Manufacturing Materials 260,106,607 Engine 206,700,000 Avionics 1,590,000,000Labor Rates Adjusted to 1999 Dollars Engineering $85 Tooling $88 Manufacturing $73 Quality Control $81Estimated RDT&E + Flyaway Cost = $4,470,179,979 44. 7 Million / AircraftFuture StudyFuture Study -Tailor Fuselage Shape to Minimize Flow Separation -Analyze Control and High Lift Concepts Mission Adaptive Wing (MAW) -Analyze Desired Radar Footprint for Exact Array Orientation -Wing Dihedral -Low Observables -Possible Requirement for Satellite Antenna System ConfigurationFuture StudyFuture Study -Utilize VaRTM Technology -Incorporate High Strength Composites to Replace Traditional Metal Components -Refine Installed Thrust Data -Refine Inlet/Nozzle DesignPerformanceCost References and AcknowledgementsReferences and AcknowledgementsReferences: Fundamentals of Aircraft Design, Nicolai, L.M., Revised 1984 Lockheed Martin Aerodynamic Data, Nicolai, L.M. Aircraft Design: A Conceptual Approach, Raymer, D.P., Third Edition Acknowledgements: Dr. James D. Lang, Project Advisor Dr. Leland M. Nicolai, Project Sponsor Dr. Paul A. Wieselmann, Project SponsorThank YouThank You