P10232: UAV Airframe C Project Review

1. P10232: UAV Airframe CProject Review Alex Funiciello Dan Graves Mike Hardbarger Jim Reepmeyer Brian Smaszcz May 14, 2010

2. Agenda • Project Overview • Customer Needs • Airframe C spec sheet • Involved Testing • Airframe C Testing Videos • Meeting Customer Needs & Engineering Specs • Objective Evaluation of Project • Suggested Design Changes

3. Project Overview Mission Statement: The goal of the UAV Airframe C project is to provide an unmanned aerial platform used for an aerial imaging system. The airframe must support the weight and interfaces for the designed imaging system. The aircraft must be operated remotely and be a viable alternative to current aerial imaging methods. This is a second generation airframe, expanding on the previously laid ground work established by the P09232 UAV B Senior Design Project.

4. Customer Needs • 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

6. Extensive Testing Process • Carbon Spar Test • 3-Pt Bending • Load Deflection • Motor Test. • Duration • Static Thrust • Structural Test • Payload Securing • Total Weight • Wing Loading/Deflection • Balancing • Ground Test • Assembly and Transport • Ground Control on Tarmac or Grass • Flight Test • Skip, Circle, Figure of Eight • Weighted Flight

7. Airframe C Testing • Imagine RIT Video • Ground Maneuvers • Skip test • First Flight • Second Flight All videos open in browser (youtube)

8. Customer Needs • 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

9. Engineering Specs • The aircraft shall have a maximum weight of 25 lbs without payload (40 lbs gross) • 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 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) • The aircraft shall sustain steady flight in a controllable manner for at least 20 minutes • The aircraft shall be able to re-launch as soon as it has been re-fueled or re-charged • The aircraft shall be able to operate for at least 12 regular flights without needing routine maintenance

10. The aircraft shall be able to take off under its own power from a 1000 ft grass runway • The aircraft shall have a sufficiently powerful motor • 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 • The aircraft shall be able to navigate while on the ground • The final cost shall be less than the cost of renting a Cessna for a day (~$8000) • The aircraft should have similar flight characteristics to a trainer RC plane • The wing shall support the plane’s gross weight under +4/-2 G loading • The wings shall not become detached from the plane while in flight • The wings shall not deflect to a degree that interferes with the operation of the flight control surfaces (will not jam the servos) • The propulsion system shall provide uninterrupted, constant power for at least 20 min • The landing gear shall hold the plane at an optimal angle of attack while on the ground • 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

11. Objective Evaluation of Project • All applicable customer needs have been addressed. • Most engineering specs were met or exceeded • Exceptions: • Airplane weight is 3 pounds over expected • Flight ceiling is limited by law to 400ft • Due to time and weather constraints the aircraft was not tested with payload on board • Wing tip loading and XFLR5 analysis leave us confident the plane is capable of carrying 15 lbs • Due to safety concerns the airframe was not flown until the batteries died.

12. Objective Evaluation of Project • The aircraft was unable to complete 12 flights. A maximum of 2 flights were performed in rapid succession. • Maximum air speed cannot be confirmed due to lack of on-board telemetry.

13. Suggested Design Changes • Wing • Keeping the wing root uniform with the wing and re-shaping the wing box • Fiberglassing the entire wing • Carbon strips on the underside stringers • End-grained (shear webbing) in the wing and tail • Tail • Increase horizontal tail area (and elevator area) • Servo connection in the tail

14. Suggested Design Changes • Landing Gear • Reduce landing gear weight • Addition of landing gear damping (to prevent rebound) • Creation of carbon fiber landing gear • Prop Clearance • Use of a smaller diameter prop to increase ground clearance (recommend a 22 in. propeller) • Possible increase in front landing gear height • Do not recommend shortening the plane body

15. P10232: UAV Airframe CProject Review Alex Funiciello Dan Graves Mike Hardbarger Jim Reepmeyer Brian Smaszcz May 14, 2010