1 HARP - High Altitude HARP - High Altitude Reconnaissance Platform Reconnaissance Platform Design Proposal Design Proposal Dr. James D. Lang, Project Advisor Dr. Leland M. Nicolai, Project Sponsor Dr. Paul A. Wieselmann, Project Steven H. Christenson –Team Lead Ceazar C. Javellana III Marcus A. Artates
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1 HARP - High Altitude Reconnaissance Platform Design Proposal Dr. James D. Lang, Project Advisor Dr. Leland M. Nicolai, Project Sponsor Dr. Paul A. Wieselmann,
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HARP - High Altitude HARP - High Altitude Reconnaissance Platform Reconnaissance Platform
Design ProposalDesign Proposal
Dr. James D. Lang, Project Advisor Dr. Leland M. Nicolai, Project Sponsor Dr.
Paul A. Wieselmann, Project Sponsor
Steven H. Christenson –Team LeadCeazar C. Javellana III Marcus A. Artates
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PresentationPresentation OverviewOverview
-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 Acknowledgements
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RequirementsRequirements
Provide 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 Cost
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Mission Endurance
2*(One-Way Transit) + Time on Station
Time on Station
2*(One-Way Transit) + Turnaround Time
Derived Requirements for 24/7 Derived Requirements for 24/7 Coverage with 2 AircraftCoverage with 2 Aircraft
Transit Transit
TA
TOS
Transit
Transit Transit
Transit
TA
TOS
Transit
TOSTransit
TA
TOS Transit
Aircraft 1
Aircraft 2
Endurance
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ISR MissionISR Mission
Descend to Sea Level
Climb to Cruise
Altitude
Cruise Out 2000 nm Cruise Back 2000 nm
Loiter 16 Hours (TOS)
Sea Level Loiterfor 30 min
55000 ft
Distance (nm)
2000 nm
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Max Distance Ferry Mission Max Distance Ferry Mission
Descend toSea Level
Climb toCruise
Altitude
Cruise 10500 nm
Sea Level Loiterfor 30 min
55000 ft
Distance (nm)10500 nm
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Assume Wto and
W/S
Size Wing
Calculate Component Weights
Calculate Fuel Fractions
Yes/NoDetermine Fuel
Available
Fuel)aval
> Fuel)reqd
Determine Fuel Required for
Mission
Aerodynamics Size Engine Performance
AR, Taper, Sweep
Fuselage Sizing and Shape
Estimate Tail Size
Study Mission Requirements
Refine Wto and
W/S Estimates
Refine Aerodynamic Parameters
Size Control Surfaces/Tail
Calculate Drag
Determine Performance Capabilities
Mission Requirements
Met?
Refine Wto and W/S
Optimize Design
-Assumptions Made/Refined-
-Configuration Assumptions Made/Refined to Meet Mission Requirements-
Cost 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
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Cost EstimationsCost Estimations
Hours
Engineering 7,568,054
Tooling 4,483,622
Manufacturing 13,472,465
Quality Control 1,791,838
Aircraft to be Procured: 100
Flight Test Aircraft: 6
Costs
Development Support 88,831,854
Flight Test 57,056,356
Manufacturing Materials 260,106,607
Engine 206,700,000
Avionics 1,590,000,000
Labor Rates Adjusted to 1999 Dollars
Engineering $85
Tooling $88
Manufacturing $73
Quality Control $81
Estimated RDT&E + Flyaway Cost = $4,470,179,979
44. 7 Million / Aircraft
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Future 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 Configuration
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Future StudyFuture Study
-Utilize VaRTM Technology
-Incorporate High Strength Composites to Replace Traditional Metal Components
-Refine Installed Thrust Data
-Refine Inlet/Nozzle Design
Performance
Cost
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References and References and AcknowledgementsAcknowledgements
References:
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:Acknowledgements:
Dr. James D. Lang, Project AdvisorDr. James D. Lang, Project Advisor
Dr. Leland M. Nicolai, Project SponsorDr. Leland M. Nicolai, Project Sponsor