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Uninhabited Air Vehicle Team Multi Purpose UAV

S P A C E Structures, Propulsion, And Control Engineering C e n t e r. Uninhabited Air Vehicle Team Multi Purpose UAV. Faculty Advisors: Dr. Chivey Wu Dr. Helen Boussalis. Team Members: Maria Luviano Roland Chen Juan Pablo Barquero Shing Chi Chan Tom Guyette

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Uninhabited Air Vehicle Team Multi Purpose UAV

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  1. S P A C E Structures, Propulsion, And Control Engineering C e n t e r Uninhabited Air Vehicle TeamMulti Purpose UAV Faculty Advisors: Dr. Chivey Wu Dr. Helen Boussalis Team Members: Maria Luviano Roland Chen Juan Pablo Barquero Shing Chi Chan Tom Guyette Solomon Yitagetsu Winston Young Wess Gates Volunteers: Keith Bacosa Billy Barrios Michael Doan Rama Mbecke Omar Miranda NASA Grant NNX08BA44A

  2. KOSMOS HERMES 55 NASA Grant NNX08BA44A

  3. Overview • Objective • Aircraft performance • Structures • Prototype • Computational fluid dynamics • Flight control system integration • Propulsion • Budget NASA Grant NNX08BA44A

  4. Objective To design an autonomous, heavy payload, lightweight UAV that is capable of carrying out multiple missions. NASA Grant NNX08BA44A

  5. Aircraft Performance NASA Grant NNX08BA44A

  6. Technical Data NASA Grant NNX08BA44A

  7. Lift Curve Slopes and Coefficients • Lift curve slope NASA Grant NNX08BA44A

  8. Aircraft Performance • Lift to drag ratio (L/D)max = 11 NASA Grant NNX08BA44A

  9. Engine Sizing NASA Grant NNX08BA44A

  10. Power Curves (PA)max Vmax NASA Grant NNX08BA44A

  11. Performance • Vmax = 161 ft/s • Rate of climb • (R/C)max = Excess power W • (R/C)max = 34.5 ft/s • Flight velocity for maximum rate of climb • V(L/D)max = (2/ρ)*((K/CD,O)^1/2)*(W/S) • V(L/D)max = 70 ft/s • Maximum climb angle • Sin Θmax = T/W – 1/(L/D)max • Θ = 27 deg. • Flight velocity for maximum angle of attack • Vθmax = Max rate of climb Sin Θmax • Vθmax = 76 ft/s 1/28/10 NASA Grant NNX08BA44A 11

  12. Structures NASA Grant NNX08BA44A 1/28/10

  13. Aircraft Structures • Aircraft structure is required to support two distinct classes of load • Ground load: movement on the ground ( taxiing, landing, and towing) • Air loads: loads during flight by maneuvers and gusts. • Function of structural components: • To transmit and resist loads to provide shape and protect passengers, payload, systems, etc from the environmental conditions found during flight. • Current UAV structural objective: • To have a semi-monocoque structure that has “minimal” structural members. • Have the skin of the UAV to be manufactured with different thicknesses in order to achieve a lighter aircraft weight NASA Grant NNX08BA44A

  14. Concepts Concept 1 – Rib and spar configuration Concept 2 – Lighter rib and spar configuration NASA Grant NNX08BA44A

  15. Concepts Concept 3 – Rib and spar configuration assembled with an uniform wing skin thickness Concept 4 – Structural member with an uniform wing skin thickness NASA Grant NNX08BA44A

  16. Structural Concept • This approach considers the following: • Split the wing in two main sections • Section 1 – have a semi-monocoque structure to absorb most of the loads • Section 2 – completely monocoque where the loads decrease Section 1 – Semi-monocoque structure with skin NASA Grant NNX08BA44A

  17. Structural Concept Section 1 Service panel Fuselage base plate Section 2 NASA Grant NNX08BA44A

  18. Next Steps • Optimize wing internal structural concept • Use of FEA (Finite Element Analysis) • Decrease size of cross members • Optimize skin thickness • Define/design mounting brackets for wing and skin • Define mounting points for control surfaces NASA Grant NNX08BA44A

  19. Prototype NASA Grant NNX08BA44A

  20. Prototype Objectives • Validation of Current Aerodynamics • Canard Design • Aerodynamics of the Wing • Balance and Stability • Practice for Possible Fabrication Techniques • Multiple Interchangeable Wings • Conventional, Composite, etc. • Identify the Proper Parameters for Control • Control Surface optimization • Test Current Landing Gear configuration NASA Grant NNX08BA44A

  21. Half Scale Prototype NASA Grant NNX08BA44A

  22. NASA Grant NNX08BA44A

  23. Specifications • Dimensions: • Length: 45.15 in (1.14 meters) • Height: 17.316 in (0.43 meters) • Wingspan: 63.44 in (1.611376 meters) • Weight: 5-6 pounds (2.26 - 2.72 kilograms) • Propulsion: Electric Motor • Propeller Diameter: 12 in (0.30 meter) NASA Grant NNX08BA44A

  24. Manufacturing • Fuselage and Canard • Cut from Foam • Sand to Final Shape • Wing • Version 1 • Built up from Balsa and Plywood • Covered with film • Future Versions • Fiberglass or Carbon Fiber NASA Grant NNX08BA44A

  25. Computational Fluid Dynamics NASA Grant NNX08BA44A

  26. AVL • Athena Vortex Lattice • Written by Mark Drela • Computes yawing moments, rolling moments, and stability • Models ailerons and flaps • Feeds into simulation effort • Verify hand calculations NASA Grant NNX08BA44A

  27. AVL editor The Cloud Cap Technology software includes an AVL editor for the end user to try out different AVL configurations. The aerodynamic properties are then shown in the AVL editor window along with the appearance of the wing structure.

  28. Inputting Geometry into AVL NASA Grant NNX08BA44A

  29. AVL Model NASA Grant NNX08BA44A

  30. AVL Model NASA Grant NNX08BA44A

  31. Loading NASA Grant NNX08BA44A

  32. Flight Control System Integration NASA Grant NNX08BA44A

  33. T60 Piccolo Hardware Integration Purpose: To learn everything about installing and flying Piccolo in an inexpensive air vehicle so we’ll be ready when our new vehicle is complete. Work completed: • Manual test flight complete (Solomon, Juan, Maria) • Communication issues are resolved • Piccolo has been fit into fuselage (harder than it sounds!) • Piccolo is roughly leveled / squared with fuselage • Manual control through Piccolo link is verified • Control surfaces are calibrated NASA Grant NNX08BA44A Image source: towerhobbies.com, wikipedia.org

  34. T60 Piccolo Hardware Integration Work remaining: • Test running Ground Station from 12V power inverter • Calibrate throttle servo • Gather vibration data • Test GPS • Test comm range • Some remaining mechanical maintenance • Design Deadman power system NASA Grant NNX08BA44A

  35. T60 Piccolo Simulation Purpose: To tell Piccolo everything it needs to know to pilot the vehicle. Available from other sources: Masses, some dimensions, AVL model, rough propulsion model Work remaining: • Model in AVL simulator and XFoil • Measure squareness angles • Measure additional dimensions • Re-calculate and measure CG • Calculate mass moments of inertia (easy, but values are rough) • Measure moments of inertia? (complicated / better values) NASA Grant NNX08BA44A

  36. Propulsion NASA Grant NNX08BA44A

  37. Overview • Engine break in • Engine bench test • SolidWorks model NASA Grant NNX08BA44A

  38. Break in Engine Mount NASA Grant NNX08BA44A

  39. Bench Test Design Strain gage • Three kinds of test will be performed • Thrust • RPM • Fuel flow • Test the propeller’s performance • Compare the result • Which propellers have good efficiency NASA Grant NNX08BA44A

  40. Side View NASA Grant NNX08BA44A

  41. Top View NASA Grant NNX08BA44A

  42. Diagonal View NASA Grant NNX08BA44A

  43. Instrumentation NASA Grant NNX08BA44A

  44. Budget NASA Grant NNX08BA44A

  45. 11/20/2014 NASA Grant NNX08BA44A 45

  46. New Materials • Total budget $13,500 11/20/2014 NASA Grant NNX08BA44A 46

  47. Reference • Corke C. Thomas. Design of Aircraft. 2003. Prentice Hall • Anderson Jr, John D. Aircraft Performance and Design. Mcgraw Hill 1999 • Beer P. Ferdinand, Johnson E. Russell, and Dewolf T. John. Mechanics of Materials. 4th Edition. McGraw Hill. 2003 • T.H.G. Megson. Aircraft Structures for Engineering Students. 3rd Edition. Butterworth Heinenmann. 1999 • Raymer, Daniel P, Aircraft Design: A Conceptual Approach. 3rd Edition. AIAA Education Series 1999 • http://www.sierracomposites.com/carbon-fiber-square-tube-with-2-sides-p/cfst284.htm • http://dragonplate.com/docs/DPSpecRecTube.pdf • http://www.safetycitystore.comhttp://www.bagking.com/Merchant2/merchant.mvc?Screen=PROD&Product_Code=TDH6&qts=googlebase&qtk=TDH6 • http://www.delta7bikes.com/shop-bike.htm • Anderson Jr, John D. Aircraft Performance and Design. Mcgraw Hill 1999 NASA Grant NNX08BA44A

  48. Reference • http://www.powerelectronics.com • http://www.sengpielaudio.com/calculator-cross-section.htm • http://www.batteryuniversity.com/partone-5A.htm • http://www.mpoweruk.com/performance.htm • http://en.wikipedia.org/wiki/Torque • http://www.copperhillmedia.com/VisualSizer/MotorSizingArticles.html • http://www.electricmotors.machinedesign.com/guiEdits/Content/bdeee3/bdeee3_1.aspx • http://rmsmotion.com/resources/step_basics_v1_0.pdf • A Comprehensible Guide to Servo Motor Sizing by Wilfried Voss • http://www.powerstream.com/Wire_Size.htm • http://www.66pacific.com/calculators/wire_calc.aspx • AVL. Mark Drela, Harold Youngren. MIT Aero and Astro • Cloud Cap Technology user guide, software simulation manual, and checklist NASA Grant NNX08BA44A

  49. Thank You Advisors Dr. BoussalisDr. WuDr. GuillaumeDr. PhamDr. Liu NASA Grant NNX08BA44A

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