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Team Beta

Team Beta. L O C K H E E D M A R T I N. Laura Brandt ~ Team Lead Melissa Doyle ~ Propulsion Luis Jimenez ~ Aerodynamics Nic Seid ~ Structures. Project Advisor: Dr. James D. Lang, Project Sponsor: Dr. Leland M. Nicolai. Outline. Design Process Requirements Mission Profile

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Team Beta

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  1. Team Beta L O C K H E E D M A R T I N Laura Brandt ~ Team Lead Melissa Doyle ~ Propulsion Luis Jimenez ~ Aerodynamics Nic Seid ~ Structures Project Advisor: Dr. James D. Lang, Project Sponsor: Dr. Leland M. Nicolai

  2. Outline Design Process Requirements Mission Profile Initial Concepts Aircraft Configuration Weight Aerodynamics Propulsion Stability Materials and Structures Cost Analysis Final Comments

  3. Schedule Initial Schedule Real Schedule

  4. Outlined Requirements Mission Profile Assumed 2 planes for minimum LCC Initial Concepts Selected Concept Sized Fuselage around payload Airfoil Design and Selection Assumed W/S, AR, b, engine Calculated Component Weights and built up Empty Weight (Wempty), Sized Tail, Performance Calculations, and Aerodynamic Analysis Assumed Take off Weight Fuel Fractions Calculate Empty Weight and compare to Wempty Calculate Fuel Required Trade Studies Evaluate Design Number and Type of Engines BCM and BCA Best Patrol Altitude and Mach Wing Span and Aspect Ratio Design Process

  5. RequirementsMission • High Altitude, Long Endurance, Standoff ISR • Unmanned/autonomous With Man-in-the-loop • Continuous Coverage (24/7) • Loiter/ISR Altitude: 50,000 – 65,000 Feet • Operate From B-52/B-2 Bases • Mission Radius = 3000 nm • Low signature side sector • 50 nm standoff racetrack flight path

  6. RequirementsSystems • 360° Continuous Coverage With GMTI, AMTI and FOPEN • 4 X Band Radar Antenna (4.5’x4.5’) • 2 UHF Radar Antenna (4’x46’) • Defensive Payload • On-board jammer (ULQ-21) • Towed decoy (12 ALE-50 decoys) • Flares (ALE-40 with 360 flares) • Threat warning system (RF/EO/IR) part of sensor suite

  7. RequirementsDefensive Payload Systems ITEM WEIGHT POWER COOLING (lb) (watts) (watts) EW/ULQ-21 117 3000 2525 Towed decoy/ ALE-50 193 470 - • 12 decoy unit plus installation • Deploy 2 per RF missile Flares/ ALE-40 828 80 - • 12 flare buckets with 360 flares plus installation • Deploy 60 per IR missile Total 1138 3550 2525 (all air cooled) Missile Warning System (MWS) and DIRCM part of EO/IR sensor suite Radar Warning system (RWR) part of ELINT sensor system

  8. RequirementsSensor ITEM WEIGHT POWER COOLING (lb) (watts) (watts) X Band Radar 2227 63200 • 4 antennas @ 4.5’x4.5’ 9500 (L)/ located in fuselage, broadside 44000 (A)/ UHF Radar 1900 67500 • 2 antennas @ 4’x46’ 25300 (L) located in fuselage, broadside (includes FOPEN) EO/IR 30 600 0 SIGINT 918 1200 1200 (L) Shared Processor 150 770 770 (L) Installation (10%) 523 - - Total (All systems on) 5748 133270 80770

  9. RequirementsFlight Avionics ITEM WEIGHT POWER COOLING (lb) (watts) (watts) Vehicle Management System 700 538 • Autopilot 203 • Air Data System 45 • Radar altimeter 14 • Flight Termination System 38 • IFF 78 Communications 3100 2125 • VHF/UHF (Link 16 & SATCOM) 44 • HF/Link 22 130 • CDL/Ka SATCOM 18 Installation (15%) 86 Total 655 3800 2663 (all air cooled)

  10. RequirementsAirframe System ITEM WEIGHT POWER COOLING (lb) (watts) (watts) Surface Control TBD 500 0 Instruments 137 50 0 Landing Gear TBD 550 0 ECS 414 140 140 Engine TBD • GCCU (engine generator)2300 2300 • Digital Fuel Control450 0 Fuel System 865 400 0 Electrical System & Control 874 2000 2000 • Secondary Power (battery controller) 350 350 Hydraulic 138 50 0 APU TBD TBD TBD

  11. RequirementsWeight/Power/Cooling Totals ITEM WEIGHT POWER COOLING (lb) (kW) (kW) Defensive Payload Systems 1138 3.6 2.5 Sensors 5748 133.3 80.8 Flight Avionics 655 3.8 2.7 Miscellaneous Airframe Systems 2428* 6.8** 4.8** Total 9969 147.4 90.7 *Control Surfaces, Engine, Landing Gear, and APU not included **APU not included

  12. RequirementsSensor, Communications and ECM/Decoy Dimensions/Volumes • X Band: 4 @ 4.5’x4.5’x1’ • UHF: 2 @ 4’x46’x1’ • X Band: REX and front end processor 1240 cubic inches • UHF: REX and front end processor 1720 cubic inches • Sensor apertures: 5 @ 3” diameter x 8” depth • Electronics: 420 cubic inches • Antennas: 8 blade antennas 4’x1’x1.25” (retract when not in use) • Receivers: 808 cubic inches • VHF/UHF (Link 16, voice, SATCOM): 12.5”x10”x7.5” • Microwave (CDL/SATCOM): 15”x6”x5” • HF: RX/EX: 25”x25”x10”, PA: 20”x10”x10”, Coupler: 20”x6”x6” • Electronics: one box @ 7.5”x5.7”x14” • Each decoy canister: 2.74”x2.74”x20.25” Radar antennas: Radar electronics: EO/IR: SIGINT: Central HPPS processor for radar, EO/IR and SIGINT: 4 cubic feet Communications: ALE-50 Towed RF decoy: ALE-40 chaff/flare dispenser: 10.6”x8.5”x6.7” each dispenser carries 30 flares ECM/ULQ-21: 1671 cubic inches

  13. Mission Endurance TOS Endurance 1st Aircraft 2nd Aircraft Transit TOS Turnaround Time on Station (TOS) 2*(Transit Time) + Turnaround Time = 20 hours Minimum Endurance Time 2*(Transit Time) + Time on Station = 36 hours Turnaround Time = 4 hours Total Transit Time = 16 hours (Assumed based on U-2) (Calculated based on Mach .65 at 50,000 ft)

  14. Lakenheath Cyprus Patrick Kadena UAE Mission Theater Minimum time on station = 20 hours Minimum number of planes per station = 2 planes Require 4 planes in reserve at Patrick, Lakenheath, UAE, and Kadena Total number of planes = 14 planes

  15. Mission Profile Altitude Cruise Out 8 hr Cruise Back 8 hr Descend to Sea Level 50,000 ft Loiter 20 hr Sea Level Loiter for 30 min Climb to Altitude Takeoff Distance 3,000 NM 3,000 NM

  16. Radar Geometry X Band Radar (4) : 4.5’ x 4.5’ UHF Radar (2) : 4’ x 46’ Field of Regard is +/- 70 degrees in the vertical and horizontal

  17. 5 degrees Horizon LOS GA Altitude Standoff Distance Radar Geometry Angle Antennas are to be placed: 1.85 degrees Altitude 50,000 ft (9.052Nm) LOS = 250 Nm Grazing Angle = 5.2 degrees Standoff Distance = 100 Nm

  18. Initial ConceptsDesign A Inlet NG X-Band Antenna MG MG UHF Antenna UHF Antenna Engine

  19. Initial ConceptsDesign B X-Band Antenna X-Band Antenna UHF Antenna UHF Antenna MG Inlet X-Band Antenna X-Band Antenna Inlet Engine Engine

  20. UHF Antenna UHF Antenna Nozzle Engine Inlet LG LG Avionics X-Band Antenna Initial ConceptsDesign C

  21. Initial Concepts A modified version of Concept B was Selected

  22. Aircraft Configuration TOGW = 50,900 lb W/S = 60 Span = 184 ft MAC = 4.89 ft Wing Area = 850 ft^2 Aspect Ratio = 40 Wing Sweep = 0 deg Airfoil: Custom Airfoil (Modified CAST 10-2/DOA 2 Transonic Airfoil) 60% Laminar Flow Engine: Two AE3007 Turbofan Fuselage Length = 60 ft Fuselage Height = 6 ft Fuselage Mean Cross Section Area = 32.5 ft2 T/W = .32

  23. Aircraft Configuration

  24. Aircraft Configuration3-View Drawing 2.83 ft. 6.6 ft. 184 ft. 14.7 ft. 3.5 ft. 6 ft. 5.9 ft. 60 ft.

  25. X-Band AE-3007’s Rear Landing Gear Aerodynamic Center Inlet V-Tail Fuselage Fuel Cell UHF Antenna C.G. APU X-Band Antenna Front Landing Gear Avionics Bicycle Landing Gear Aircraft ConfigurationInternal Components

  26. Weight Take-Off Weight Empty Weight Fuel Weight Fuel Fraction Fuel Volume 50,900 lb* 26,800 lb 24,100 lb 0.47 3,500 gal *Takeoff weight is estimated to be within 500 lb of Actual Gross weight

  27. Weight Fractions • Start up/Take-Off • Climb to Cruise Alt • Cruise Out • On Station • Cruise Back • Descend to Sea Level • Loiter 30 min Best Cruise Altitude = 50,000 ft Best Cruise Mach = .65 Best Loiter Altitude = 50,000 ft Best Loiter Mach = .62

  28. Aerodynamics Aspect Ratio = 40 Span = 184 ft Reference Area = 850 ft2 Taper Ratio = .4 MAC = 4.89 ft Croot = 6.6 ft Ctip = 2.83 ft Wing Sweep = 0 deg Airfoil: Custom Airfoil (Modified CAST 10-2/DOA 2 Transonic Airfoil) 60% Laminar Flow t/c = .15 e = .63 * K = 0.013 CLmax = 1.2 * Estimated ‘e’ using Wing Efficiency vs Aspect Ratio Graph provided by Lockheed Martin

  29. AerodynamicsAt 50,000 ft and M=.62 L/Dmax = 50.58 @ CL=.8 CLmax = 1.2 Zero Lift Drag = 0.008 Clalpha = 10.4 rad-1 = .18 deg-1 at Mach .62 Vstall = 479 ft/s (at half fuel weight)

  30. Aerodynamics

  31. Sears Haack

  32. Aerodynamics50,000 ft at Mach .62 Begin Loiter at CL = .8

  33. L/Dmax = 50.58 at CL of .8 Aerodynamics50,000 ft at Mach .65

  34. (deg) AerodynamicsDrag Divergent Mach Number Mdd = Mdd(L=0)*LFdd – 0.05*Cl Mdd is higher than loiter and range mach numbers. Mdd(L=0) was taken from Boeing chart for uncambered airfoils, which typically resulted in Mdd of about 0.08 mach above critical mach number. LFdd taken from plot intended to adjust Mdd to actual lift coefficient.

  35. Aerodynamics 60% laminar flow airfoil was desired Computer programs such as Profili and XFOIL were used in order to simulate fluid flow across different airfoils. Laminar separation points and Pressure coefficients were obtained using various lift coefficients.

  36. Aerodynamics XFOIL was used to determine the Separation Bubble Profili and Excel were used to modify different characteristics of airfoils such as camber, leading edge radius, and percent thickness. A trade study involving how thickness affects the range of laminar flow along the airfoil, was done through viscous operations on XFOIL

  37. Aerodynamics Final Airfoil Modified CAST 10-2/DOA transonic airfoil Specifications Max. Thickness 14.98% Max. Thickness at 45.6% of Chord Max. Camber 1.90% Max. Camber at 69.5% of Chord Laminar Separation at 60.34% of chord

  38. Aerodynamics Graph using a Lift Coefficient of 0.8

  39. AerodynamicsKarman-Millikan Method Alternate method of determining laminar separation. Relates pressure coefficients from XFOIL to velocity profiles. Cp = 1 – (U/Uo)2 Iteration of velocity gradient with pressure coefficients resulted in separation point using plot of Us/Uo versus F.

  40. AerodynamicsKarman-Millikan Method Used to verify laminar separation through velocity profile. U/Uo = 1 for 0 < x/xe < 1 U/Uo = 1 + F * ((x-xe)/xe) for 1< x/xe x = distance along surface from leading edge. xe = length from leading edge to center of pressure. U = velocity outside boundary layer. Uo = maximum velocity. F = velocity gradient.

  41. AerodynamicsKarman-Millikan Method Us = velocity at laminar separation point.

  42. AerodynamicsThickness to Chord Variation Trade study involving same airfoil and camber as a control basis, then thickness as a variation. Percent thickness versus laminar flow was plotted to depict a trend or tendency. Plot shows ideal thickness of about 15% in order to achieve a relative maximum laminar flow of about 60% (for CAST 10-2/DOA 2 transonic airfoil).

  43. Aerodynamics Airfoil thickness trade study t/c selected was .15

  44. AerodynamicsCp Distribution

  45. AerodynamicsCdo at half fuel weight

  46. Aerodynamicsfor Sref = 850 ft2 Aircrafts wing span is 184 ft with an aspect ratio of 40

  47. Aerodynamics BCA 50,000 ft at BCM 0.65

  48. Aerodynamics Best Loiter Altitude 50,000 ft at Best Loiter Mach 0.62

  49. Performance Stall Velocity at Sea Level 205 ft/s Take-Off Velocity 225 ft/s Take-Off Distance 3995 ft Landing Distance 3770 ft

  50. PerformanceRobust Structural Design - Taking Into Account Gust Loading Limit Load Factor 3.5 Ultimate Negative Load Factor 3.85 Ultimate Positive Load Factor 5.25 Sustained Turn Load Factor 3.52 Sustained Turn Rate 9.84 deg/s Dynamic Pressure Limit 99.6 lb/ft2

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