Project Review Alex Funiciello Dan Graves Mike Hardbarger Jim Reepmeyer Brian Smaszcz May 14 2010 Agenda Project Overview Customer Needs Airframe C spec sheet Involved Testing ID: 606620
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P10232: UAV Airframe CProject Review
Alex Funiciello Dan Graves Mike Hardbarger Jim Reepmeyer Brian SmaszczMay 14, 2010Slide2
AgendaProject Overview
Customer NeedsAirframe C spec sheetInvolved TestingAirframe C Testing VideosMeeting
Customer Needs & Engineering SpecsObjective Evaluation of Project
Suggested Design Changes2Slide3
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.
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Customer Needs
Airframe must be able to carry a fifteen pound payloadEasy integration with measurement controls box and different aerial imaging systemsAbility 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
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UAV-C Spec Sheet
General
Specs
Assembled
Specs
Type
Conventional Monoplane
Length
8.5ft
Tail
Cambered
Wingspan
10 ft Landing GearTail Dragger Weight (unloaded)28 lbf Camera ControlManual with Servo Propulsion Total Cost$1,969.36 Motor3250 Watts Airframe Construction Propeller26x10 Main Structure1/4" Light Ply Static Thrust26 lbf Stringers1/8" Balsa Battery Capacity10000 mAh Battery Voltage42V (nominal) Wing Airfoils1/8" Balsa ESC110A max Skin6" Monokote Wing Wing AttachmentWing Box Fixed to Bottom of Plane Airfoil DesignNACA 9412 Main Wing Spar3/4" Carbon Fiber ConstructionFiberglass/Balsa Wood Chord16 in
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Extensive Testing Process
Carbon Spar Test3-Pt BendingLoad DeflectionMotor Test.DurationStatic ThrustStructural Test
Payload SecuringTotal WeightWing Loading/DeflectionBalancing
Ground TestAssembly and Transport
Ground Control on Tarmac or Grass
Flight Test
Skip, Circle, Figure of Eight
Weighted Flight
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Airframe C Testing
Imagine RIT VideoGround ManeuversSkip testFirst FlightSecond Flight
All videos open in browser (youtube)
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Customer Needs
Airframe must be able to carry a fifteen pound payloadEasy integration with measurement controls box and different aerial imaging systemsAbility 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
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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 ftThe 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 payloadThe aircraft shall utilize an open architecture payload interfaceThe aircraft shall provide a mechanical interface to the payload
The aircraft shall provide a secure anchoring connection for the photographic instrument payloadThe 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
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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 motorThe aircraft shall be able to be transported in a motor vehicle when disassembledThe 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
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Objective Evaluation of Project
All applicable customer needs have been addressed.Most engineering specs were met or exceededExceptions:Airplane weight is 3 pounds over expectedFlight ceiling is limited by law to 400ftDue to time and weather constraints the aircraft was not tested with payload on boardWing 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.
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Objective Evaluation of ProjectThe 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.12Slide13
Suggested Design ChangesWing
Keeping the wing root uniform with the wing and re-shaping the wing boxFiberglassing the entire wingCarbon strips on the underside stringersEnd-grained (shear webbing) in the wing and tailTailIncrease horizontal tail area (and elevator area)Servo connection in the tail
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Suggested Design ChangesLanding Gear
Reduce landing gear weightAddition of landing gear damping (to prevent rebound)Creation of carbon fiber landing gearProp ClearanceUse of a smaller diameter prop to increase ground clearance (recommend a 22 in. propeller)Possible increase in front landing gear heightDo not recommend shortening the plane body
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P10232: UAV Airframe CProject Review
Alex Funiciello Dan Graves Mike Hardbarger Jim Reepmeyer Brian SmaszczMay 14, 2010