2015 SAE Aero East Design Team

2015 SAE Aero Design East TeamMid-Term Status Report(3/5/2015)2015 SAE Aero East Design Team2015 SAE Aero East Design TeamJN1SAE Aero East 2015 Team2Project Advisor Dr. Drew Landman

Team MembersAndrew TonkovicChris ThurmanGreg ShivelyKevin RhamyLucas Mills

Mason HunerkochMichael LauruskaRyan LaporteSara MendelsohnWilliam FisherTeam LeaderJeremy Newman2015 SAE Aero East Design Team2015 SAE Aero East Design TeamJN2OverviewProject ScheduleCompetition ObjectivesDesign SummaryAnalysisManufacturingResults & DiscussionProject BudgetRecent WorkFuture Work

32015 SAE Aero East Design Team2015 SAE Aero East Design Team3Project Schedule4

2015 SAE Aero East Design Team2015 SAE Aero East Design Team4Competition ObjectivesOverall length, height and span of the aircraft cannot exceed 175 inchesThe maximum weight cannot exceed 55 poundsThe use of fiber-reinforced plastic is prohibitedPayload bay dimensions of 10 x 4 x 4Unload and reload payload in one minute1000 watt power limiter Take off in 200 feet, fly a 360 degree circuit, and land in 400 feet

52015 SAE Aero East Design Team2015 SAE Aero East Design TeamDesign Summary6

2015 SAE Aero East Design Team2015 SAE Aero East Design Teampreliminary design featuring lowered ride height to increase ground effect Triple tail to increase surface area while lowering overall height of the tailRepositioned motor 6Design SummaryUtilized Modified Pratt Truss to minimize weightOptimize cargo weight capacity Produce high lift coefficientMaximize ground effect

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2015 SAE Aero East Design Team2015 SAE Aero East Design TeamAnalysisEppler 423 AirfoilDrag vs. Angle of AttackLift vs. Angle of Attack8

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamAnalysisMotor mount vibrationPropeller evaluationeCalc for motor/prop matching Thrust vs. Freestream velocity

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2015 SAE Aero East Design Team2015 SAE Aero East Design TeamTo determine the optimum motor a computer program for motor/propeller matching called eCalc (Mller, Modellflg, Germany) was used (Fig. 17). Using the 1000 W limit and combinations of different motors, batteries and propellers, it was found that the Eflight Power 52 would be the best match for the current aircraft. The analysis showed that as the voltage on the system increased, the KV (RPM/volt) rating needed to decrease to get the same power when compared to a lower voltage system and higher KV motor. Simultaneously, the propeller choices were also investigated leading to a propeller choice of 12 x 4.5. Using the ODU wind tunnel and thrust stand, a factorial experiment was created using prop diameter, prop pitch, and free stream velocity as factors. Results show a 12 x 4.5 prop would give optimum thrust. A second experiment was created to characterize the 12 x 4.5 prop

9Structural analysisVon Mises Stress =1.43 ksiMax. vert. displacement = 0.017 inchesPayload predictionUp to 29.5 lbf

10Analysis

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamManufacturing11

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamPrototype (test plane) Aero ply heavy, strong, meant to test fly to optimize wing, tail, landing gear, motor, and CG configurations

11Manufacturing12

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamDiscuss wing build up using lightweight ribs as well as balsa/spruce for spar etc.Tail section construction ----- updated to feature larger rudders w/tabMore structurally sound verticals, better placed servosLanding gear A228 music wire axel, Aluminum wheels and brackets to reduce wieght, lightly pressed bearings to allow rotation on fixed axle12Manufacturing13

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamWing, tail and fuselage monokoted to create lightweight surfaces across the planeCG stand13Results and Discussion14

Weight (lbf): 2.406

Span (in): 94

Chord (in): 17

Planform area (in2): 15982015 WingWeight (lbf): 2.750

Span (in): 84

Chord (in): 15

Planform area (in2): 12602014 Wing2015 SAE Aero East Design Team2015 SAE Aero East Design TeamInitial Test FlightVibrations induced by the motor did not excite natural frequencies of the motor mountTriple tail tested successfullyDistance between tail and wing section tested successfullySecondary Test FlightRudder control surface proved insufficient Telemetry unit collected flight dataAdequate Take-off distance (< 200ft)Sustained flight in high wind conditions (10 -15 mph)Tertiary Test Flight18 lbf payload lifted

Results and Discussion152015 SAE Aero East Design Team2015 SAE Aero East Design TeamResults and Discussion16

Take-Off Speed 16 mphMax. Speed 46 mphMax. Elevation 276 ftPredicted: 18.4 mph @ 7lbf payload2015 SAE Aero East Design Team2015 SAE Aero East Design Team17Project Budget Parts CostBudgeted Parts Cost = $1995.23Actual parts cost $1600Able to reuse some parts and materials from 2014 projectTravel CostAvailable Travel Budget: $4500Projected Travel Costs: Renting vehicles: $900Gas Estimate: $600Hotel reservations: $1200Meals & Incidentals: $1400Total: $ 4100

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamJN17Recent Work

18New Payload Box:Steel and Aero Ply ConstructionSteel section to act as ballastModified Verticals, Elevators, and RuddersIncrease in control surface areaIncreased structural integrityCounter-balanced rudder design

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamFuture Work19Test flight(s) final aircraftFlight data collectionCompetition logisticsCompetition PowerPointDocument:Competition resultsLessons learned

2015 SAE Aero East Design Team2015 SAE Aero East Design TeamJN19Questions?2015 SAE Aero East Design Team2015 SAE Aero East Design TeamJN20