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The FITSAT 3 Project

The FITSAT 3 Project. The Aerospace Team. Shane Akpeti Sean Reid Alana Xavier Gap The Juan James Booker Fumitaka Goto Thomas Tellier. Overview. Team Organization Preliminary designs The Prototype design The Target Design Budget Gannt Chart Acknowledgments.

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The FITSAT 3 Project

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  1. The FITSAT 3 Project

  2. The Aerospace Team Shane Akpeti Sean Reid Alana Xavier Gap The Juan James Booker Fumitaka Goto Thomas Tellier

  3. Overview Team Organization Preliminary designs The Prototype design The Target Design Budget Gannt Chart Acknowledgments

  4. Team Organization

  5. Parallel Design

  6. Alternate designs Standard Aircraft Design

  7. Alternate Designs Blended Wing And Body

  8. Alternate Designs X –Plane Design

  9. Alternate Design Solid works

  10. The Prototype Design

  11. Wing Cross Section

  12. Aerodynamics Weight Estimation for Prototype A Preliminary estimate was conducted with design weight upper limit: 1.48 Kg (3.28) lbs    W = mg ( Weight) Preliminary weight = 14.59 N

  13. Aerodynamics Wing Geometry Main Wing Airfoil NACA 4412 Cl = 0.4 at 0 AOA Wing Tip Airfoil NACA 0006      Fuselage Airfoil NACA 2412 cl = 0.2 at 0 AOA

  14. Aerodynamics The Airfoil

  15. Aerodynamics Estimation of Lift and Drag

  16. Aerodynamics

  17. Aerodynamics Lift Total positive lift on wing = 12.62 N Total Negative lift on wing = -3.23 N Total Lift from Wing = 9 N Total lift from body = 5.12 N Total lift of aircraft = 14.59 N or 3.28 lbs

  18. Thrust Analysis The Equations

  19. Thrust Analysis

  20. Thrust Analysis

  21. Propulsion Power Plant Selected : ŸPelikan Brushless Motor 200 Watts In 180 Watts out Weight 5.4 ounces Max Velocity available 43 m/s

  22. Aircraft Performance Take Off Performance Estimate of 15 m/s

  23. Aircraft Performance Take off Distance Estimate = 33.3 m

  24. Rate of Climb

  25. Aircraft Electronics

  26. 4 basic criteria to meet Stability and Control Static Longitudinal Stability Static Lateral Stability Dynamic Longitudinal Stability Dynamic Lateral Stability

  27. Equilibrium in Pitching moment • Lift produced by wing body equals to weight of airplane mg at level flight. The net moment acting on the airplane has equal to zero for the airplane to be stable. • Therefore movement coefficients also equal to zero.

  28. Aerodynamic center x dy dS y b/2

  29. Simple Drawing of planeThe drawing show thenegative lift at the end of the wing that occurs because of the twist in it.

  30. 3-D Drawing of Twisted Wing

  31. Materials • fiber glass weight - 4 oz per square yard • A layer of foam • A layer of fiberglass • A layer of epoxy • A layer of epoxy hardener

  32. The Control Surfaces Moving parts of the airplane

  33. Moving Parts of the airplane

  34. Servos • 4 servos: 2 in each wing • HS-85BB Servo #31085 (micro servo)

  35. HS-85BB Servo #31085 Control System: +Pulse Width Control 1500usec Neutral Required Pulse: 3-5 Volt Peak to Peak Square Wave Operating Voltage: 4.8-6.0 Volts Operating Temperature Range: -20 to +60 Degree C Operating Speed (4.8V): 0.16sec/60 degrees at no load Operating Speed (6.0V): 0.14sec/60 degrees at no load Stall Torque (4.8V): 41.66 oz/in. (3kg.cm) Stall Torque (6.0V): 48.6 oz/in. (3.5kg.cm) Operating Angle: 40 Deg. one side pulse traveling 400usec 360 Modifiable: Yes Direction: Clockwise/Pulse Traveling 1500 to 1900usec Current Drain (4.8V): 8mA/idle and 240mA no load operating Current Drain (6.0V): 8.6mA/idle and 260mA no load operating Dead Band Width: 8usec Motor Type:  3 Pole Ferrite Potentiometer Drive: Direct Drive Bearing Type: Single Ball Bearing Gear Type: All Nylon Gears Connector Wire Length: 6.29" (160mm) Dimensions: 1.14" x 0.51"x 1.18" (29 x 13 x 30mm) Weight: 0.77oz (21.9g)

  36. Manufacturing Parts List

  37. Construction of the Prototype

  38. Construction of the Prototype

  39. Construction of the Prototype

  40. Construction of the Prototype

  41. Construction of the Prototype

  42. The Target Design

  43. The Target Design Target design weight = 44.14 N or 10 lbs Estimated Dimensions for the Wing Wing Span 2 m Chord Length 0.20 m Flight Speed for steady level Flight 30 m/s at 0 AOA Airfoil NACA 4415 and 2415

  44. Thrust Analysis for Target Weight

  45. Propulsion 500 Watts in 300 Watts out Weight 9.5 ounces Gear Ratio 2.38 to 1 Diameter 1.32 inches

  46. Wing Deployment Mechanism Tension Spring Release System Preliminary Concept

  47. Four Bar Mechanism

  48. The Gliding Flight The thrust is zero because the power of the aircraft is off. D = Wsinq (1) L = Wcosq (2) dividing (1) by (2) D/L = tanq Or tanq = 1/(L/D)

  49. The Maximum Range tanqmin = 1/(L/D)max tanqmin = 1/14.981 qmin = 3.88o R = h / tanq Rmax = h / (L/D)max Rmax = (10,000)/(15.354) Rmax = 651.296ft

  50. Budget

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