1. Daniel Graves –Project Lead James Reepmeyer – Lead Engineer Brian Smaszcz– Airframe Design Alex Funiciello – Airfoil Design Michael Hardbarger – Control Systems

2. Customer Needs Key Project Goals:  Airframe must be able to carry a fifteen pound payload  Easy integration with measurement controls box and different aerial imaging systems  Ability to remotely control aircraft and activate payload  Ability for flight communication between aircraft and ground relay  Aircraft provides twenty minutes of flight time for local area photography  Aircraft has the potential to take off and land on site  Easy assembly and disassembly of the aircraft for transportation

3. Lessons Learned From P09232  The aircraft’s wings sheared off shortly before impact. The failure was determined to be from the bending stress applied to the wings during the banked turned.  After analysis, it was concluded that the main fiberglass spar used to support the wing was not selected properly to handle the flight loading.  High bend in the wing during flight inhibited the pilot’s control of the aircraft by reducing the effectiveness of the control surfaces.

4. Design goals based on lessons learned from P09232  Reduce wingspan (reduced bending moment)  Re-enforce wing spar  Reduce plane weight  Re-evaluate electric propulsion

5. Project Status  CAD model – Nearly done, ready to start creating laser drawings  Propulsion / Controls – Ready to place order on motor and battery  Landing Gear – Re-use last year’s  Wing Spar – One piece spar is satisfactory; pending confirmation from supplier on specs and availability  Airfoil – Airfoil will lift plane and allow for flight control  Wing box / wing design – Pending wing spar information

7. Action Items  Prove control surface equations viable with analysis  Optimum lift/drag and airspeed  Optimum rate of climb with analysis  Look into carbon fiber rod cost/practicality of constructing our own

8. Action items  Look into carbon fiber rod cost/practicality of constructing our own Carbon Fiber is the best option for the main spar Quality control on home-made carbon fiber spars is very lose  Maximum bending load of carbon fiber rod Carbon Fiber rod should be sufficient to support plane weight; pending supplier specifications

9. Action Items  Approximation of distributed load as a point load at wing center Prior analysis was correct, action item dismissed  Check loading analysis loading vectors (banked turn FBD) Analysis deemed unnecessary

10. Action Items  Tabulate detailed calculation Detailed calculations are being updated and documented  Correct ply-wood B.O.M. error Actual ply-wood required: 3 sheets, not 44 Total ply-wood costs is approx. $73.00  Run some numbers on the loading and aero CG The aero CG is located at the 3/4 chord of the wing

11. Action Items  Notch the corner for the bottom plate of the main payload bay The plane body has been adapted to receive the wing mounting  Provide proof airframe is stable at 40mph Airframe can be controlled and stabilized at cruise speed using designed control surfaces  Provide proof airframe can power itself at 40 mph The airframe requires approximately 734 watts of power to maintain 40 mph

12. Action Items  Look into an analysis of torque on the elevator Servos will be able to control all flight control surfaces  Crush load on wood for wing mount The plane body has been adapted to receive the wing mounting  Nail down wing box design Wing box mounting design has not yet been finalized

13. Action Items  Nail down tail mount design Tail mount has been finalized, similar to mount from airframe B

15. Airframe must be able to carry a fifteen pound payload  The aircraft shall have a maximum weight of 25 lbs without payload (40 lbs gross)  The aircraft shall be capable of stable flight with a 15 lb payload  The aircraft shall be able to take off under its own power from a 1000 ft grass runway

16. Easy integration with measurement controls box and different aerial imaging systems  The aircraft shall utilize an open architecture payload interface  The aircraft shall be capable of stable flight with a 15 lb payload  The aircraft shall provide a secure anchoring connection for the photographic instrument payload  The aircraft shall provide a secure mounting location for the flight control electronics package (P10236)

17. Ability to remotely control aircraft and activate payload  The aircraft shall utilize an open architecture payload interface  The aircraft shall provide a mechanical interface to the payload  The aircraft shall provide a secure anchoring connection for the photographic instrument payload  The aircraft shall provide a secure mounting location for the flight control electronics package (P10236)

18. Ability for flight communication between aircraft and ground relay  The aircraft shall provide a secure mounting location for the flight control electronics package (P10236 and P10231)

19. Aircraft provides twenty minutes of flight time for local area photography  The aircraft shall have a flight ceiling of 1000 ft  The aircraft shall be able to sustain a flight of at least 40mph in calm conditions  The aircraft shall be capable of stable flight with a 15 lb payload  The propulsion system shall provide uninterrupted, constant power for at least 20 min  The servos shall be of sufficient power to control the plane’s control surfaces at speeds up to 50 mph  The aircraft shall be structurally sound; no parts shall leave the aircraft while in flight

20. Aircraft has the potential to take off and land on site  The aircraft shall be able to take off under its own power from a 1000 ft grass runway  The landing gear shall hold the plane at an optimal angle of attack while on the ground  The aircraft shall be able to navigate while on the ground

21. Easy assembly and disassembly of the aircraft for transportation  The aircraft shall be able to be transported in a motor vehicle when disassembled  The aircraft should be easy to assemble and disassemble by one person

22. Risk Management https://edge.rit.edu/content/P10232/public/Risk%20Man agment%20Rev%202.pdf