洛克希德马丁+高空无人侦察机+机密资料+谨慎传阅.ppt

1、1,HARP - High Altitude Reconnaissance Platform Design Proposal,Dr. James D. Lang, Project Advisor Dr. Leland M. Nicolai, Project Sponsor Dr. Paul A. Wieselmann, Project Sponsor,Steven H. Christenson Team Lead Ceazar C. Javellana III Marcus A. Artates,2,Presentation Overview,-Define Requirements -Des

2、ign 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,3,Requirements,Provide 24/7 ISR Coverag

3、e 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,4,Mission Endurance 2*(One-Way Transit) + Time on Station Time on Station 2

4、*(One-Way Transit) + Turnaround Time,Derived Requirements for 24/7 Coverage with 2 Aircraft,5,ISR Mission,Descend to Sea Level,Climb to Cruise Altitude,Cruise Out 2000 nm,Cruise Back 2000 nm,Loiter 16 Hours (TOS),Sea Level Loiter for 30 min,55000 ft,Distance (nm),2000 nm,6,Max Distance Ferry Mission

5、,Descend to Sea Level,Climb to Cruise Altitude,Cruise 10500 nm,Sea Level Loiter for 30 min,55000 ft,Distance (nm),10500 nm,7,Assume Wto and W/S,Size Wing Calculate Component Weights Calculate Fuel Fractions,Yes/No,Determine Fuel Available,Fuel)aval Fuel)reqd,Determine Fuel Required for Mission,Aerod

6、ynamics 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/

7、S Optimize Design,-Assumptions Made/Refined-,-Configuration Assumptions Made/Refined to Meet Mission Requirements-,Design Process,Yes/No,8,Aircraft 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 T

8、echnology Turbofan Engine at Full Power and 55000 ft,Design Analysis Based on the Following Assumptions:,9,Aircraft Configuration,Wto = 50000 lbW/S = 60 lb/ft2 Wing Area = 833 ft2Wing Span = 129 ft Wing Sweep = 0 degAspect Ratio = 20,10,Radar Geometry,X Band Radar (4) -3.3 x 6.1 ft -Azimuth Field of

9、 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 Side,11,Horizon Distance,Design Array Angles for Desired Footprint,12,Aircraft Configuration,Wing Area = 833 ft2Wing Span = 129 ft Wing Sweep = 0 degAs

10、pect Ratio = 20,Fuselage Length = 62 ft Height = 6 ft Width = 10 ft,13,Aircraft Configuration,14,Aircraft Configuration,Wing Fuel Tank,Center of Gravity & Aerodynamic Center,15,Start up/Take-Off.970 Climb to Cruise Alt.950 Cruise Out.902 Loiter on Station.754 Loiter Fuel10219 lb Maneuvering Fuel671

11、lb Cruise Back.902 Descend to SL1.00 Loiter 20 min.994,Take-Off Weight50000 lb Fuel Weight 23874 lb Fuel Fraction.48 Fuel Volume3511 gal,Weight 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 = .16,16,-16 Hour TOS-

12、 Cl = .864 L/D)max = 31.52 Mach .6 and 55000 ft,ISR Mission Compliance,Mission 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 = .628L/D = 29.72

13、Mach .6 and 55000 ft,Total Mission Fuel Required: 23874 lb = 3511 gal,17,Weight Fractions - Ferry,Start up/Take-Off.970 Climb to Cruise Alt.950 Cruise 10500 nm.567 Descend to SL1.00 Loiter 20 min.994,Take-Off Weight50000 lb Fuel Weight 24685 lb Fuel Fraction.49 Fuel Volume3630 gal,Design Pushed by 1

14、0500 nm Ferry Flight Approx 800 lb Additional Fuel Required,18,Aerodynamics,Aspect Ratio = 20Span = 129 ft Wing Sweep = 0 dege = .9 t/c = .15 K = .01768 Taper Ratio = .50MAC = 6.7 ft Croot = 8.6 ftCtip = 4.3 ft Airfoil: Modified Lockheed Martin Sensorcraft Wing15% to Provide 60% Laminar Flow,19,Aero

15、dynamics,L/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 Plot,20,Aerodynamics,Cl =

16、 .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 Flaps,21,Aerodynamics,Fuselage Sized to Hold Radar Arrays,Length = 62 ft Depth = 6 ft Width = 10 ft Fineness Rat

17、io = 6.2,Volume = 2922 ft3 Wetted Area = 1067 ft2 Max Cross Sectional Area = 47 ft2,22,Aerodynamics,L/D)max = 31.52,23,Aerodynamics,24,Aerodynamics,-Insufficient Data in References to Accurately Calculate MDD -Concern that at Cruise Velocity and Altitude (M .6 55000 ft) Airfoil is Near MDD -Supercri

18、tical Wing,MDD, Drag Divergent Mach Number,25,Performance,Limit Load Factor1.25 Ultimate Load Factor1.88 Turn Load Factor1.15 Maneuvering Turn Rate 1.8 deg/s Dynamic Pres Limit450 lb/ft2,Stall Velocity159 ft/s Take-Off Velocity 191 ft/s Take-Off Distance5000 ft Landing Distance4000 ft Braking Accele

19、ration 7 ft/s2,26,Performance,27,Performance,28,Performance,29,Propulsion,2015 Technology Turbofan Engine Moderate Bypass Ratio 8000 lb Thrust (Sea Level Static) .40 TSFC (Sea Level Static) Dimensions: Length115 in (9.6 ft) Diameter41 in (3.4 ft) Engine Weight: 1600 lb System Weight:3100 lb,-Pitot I

20、nlet, 10 ft2 Capture Area -Fixed Convergent Nozzle, 6 ft2 Exit Area,30,Propulsion,31,Propulsion,32,Propulsion,33,Auxiliary Power,Required Power128 kW Power Available from Engine70 kW = .061*Talt Additional Power Required58 kW,Total Weight1304 lb APU Fuel Weight595 lb Total Weight1899 lb,APU Continen

21、tal L/TSIO-360,34,Auxiliary Power,Engine Excess Power,kW = .061*Talt Additional Thrust 957 lb Additional Fuel8562 lb,(T-D)*V = Power Additional Thrust 58 lb Additional Fuel523 lb,Average Additional Fuel4542 lb,35,Fuselage3415 lb Wing4928 lb Control Surface(s)2508 lb Tail297 lb Landing Gear1677 lb Pr

22、opulsion System3100 lb Flight Systems460 lb Fuel System/Tanks496 lb Hydraulic System172 lb Electrical System849 lb Air Cond/Anti-ice Sys794 lb Payload (Installed)6963 lb,Take-Off Weight50000 lb Empty Weight18697 lb Weight with Payload25660 lb Fuel Weight Available24340 lb Fuel Fraction.49 Fuel Volum

23、e3579 gal,Weight Build-up,-Fuselage and Landing Gear Weight Reduced by 15% and 5%, respectively, for 2015 Technology Target Factors,36,Stability and Control,Center of Gravity and Fuel Schedule,37,Stability and Control,Static Margin (SM) Summary,38,Stability and Control,Cmo = .0681,39,Stability and C

24、ontrol,Ailerons Area = 37.9 ft2 each MAC = 1.47 ft Span = 25.8 ft,Flap Chord: 25% Wing Chord at Root Flap Span: 27% of Wing Span,Flaps Area = 38.0 ft2 each MAC = 2.15 ft Span = 17.7 ft,Total Control Surface Area: 152 ft2,Aileron Chord: 22% of Wing MAC Aileron Span: 40% of Wing Span,40,Stability and

25、Control,V-Tail Cvt = .0145Svt = 55.7 ft2 Cht = .34Sht = 67.7 ft2 42 deg from Vertical Rudder Area = 18.6 ft2 = (1/3)Svt,41,Materials and Structure,Carbon Fiber -Wings -Control Surfaces -Fuselage Fiberglass -Array Panels,Material Selection,Structural Concept,Semi-Monocoque Fuselage Structure Carbon F

26、iber Wing Box, Spars and Landing Gear Struts,42,Materials and Structure,43,Materials and Structure,44,Materials and Structure,45,Materials and Structure,Ixx = 2.89E3 slug-ft2 Iyy = 1.93E5 slug-ft2 Izz = 6.86E5 slug-ft2,Mass Moments of Inertia Based on Historical Data,46,Cost Estimations,Engineering

27、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 -Max

28、imum 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,47,Cost Estimations,Hours Engineering 7,568,054 Tooli

29、ng 4,483,622 Manufacturing 13,472,465 Quality Control 1,791,838,Aircraft to be Procured: 100 Flight Test Aircraft: 6,Costs Development Support88,831,854 Flight Test57,056,356 Manufacturing Materials260,106,607 Engine 206,700,000 Avionics 1,590,000,000,Labor Rates Adjusted to 1999 Dollars Engineering$85 Tooling$8