Group 3 Heavy Lift Cargo Plane William Gerboth, Jonathan Landis, Scott Munro, Harold Pahlck February 18, 2010

Presentation Outline Project Objectives Q&A From Phase III Revised Payload Prediction Flight Controls Prototype Fabrication Plan Fabrication Schedule Updated Budget Plan for Phase V Nugget Chart

Project Objectives Design and build an airplane that meets the requirements of the SAE Aero East competition Plane must successfully take off from a runway of 200 feet and land on a runway 400 feet Constraints of 55 pounds total weight, and the combined height, length, and width of 200 inches Plane must make one complete 360° circuit of the field per attempt

Phase III Questions How is Induced Drag accounted for? – Drag as a result of lift created by a finite wing – Induced drag coefficient is added to overall drag Landing Gear Analysis – Used deflection to gain an understanding of the bending that can be expected during landing Stability – The center of gravity is located in a neutral point – With increasing payloads the plane maintains a positive static margin

Phase III Questions (cont.) Explanation of Graphs – Takeoff calculations done in excel – Using takeoff velocity, stall velocity, and ground roll distance One Pound Force used in Analysis – Using a force of 15mph wind perpendicular to the tail creates a force of 1.3 pounds Ease of Assembly and Manufacturing – Difference in thickness of trailing edge – Ability to make changes in internal workings

Revised Payload Prediction Grass runway instead of concrete Higher coefficient of rolling friction Grass takeoff requires long takeoff distance, reducing payload that can be lifted in 200 ft. Calculations showed reduction of 2 lbs’ Expecting more reduction due to unforeseen factors such as terrain and length of grass

Payload Prediction Graph

Flight Controls 8 Servos Used 1 servo per aileron and flap located in wing 1 for each elevator located at rear of the fuselage 1 for the throttle 1 for the rudder and front wheel

Flight Control Sizing Two approaches Used largest value from following calculation and table

Fabrication – Wing Structure Constructed using 38 ribs Ribs cut using Eppler 423 template with a X-Acto knife Ribs connected using a system of spars One spar at the leading edge, one at 25% of the cord and five separate spars along the trailing edge Flaps and ailerons will be attached to the trailing edge with hinges Holes will be drilled for bolting to fuselage Entire wing structure covered in Monokote using heat gun

Fabrication - Wing Structure

Fabrication - Fuselage Front cowl made of balsa Firewall behind cowl made of plywood Center section of fuselage constructed with a cargo opening, balsa walls, and plywood floor for structural rigidity Supports added to the center section for rigidity and to allow mounting of the wing Rear of fuselage built from ribs tapering in size Fuselage covered in Monokote

Fabrication - Fuselage

Fabrication – Tail Plane Two main components vertical and horizontal tail Vertical tail cut from balsa wood Rudder attached to rear with hinges Horizontal tail made from 12 ribs cut from NACA 0012 template Three spars will connect ribs Vertical stabilizers will be connected to the rear using hinges

Fabrication – Tail Plane

Fabrication – Landing Gear Salvaged from previous years Front Landing Gear – commercially purchased strut with spring to absorb impact Rear Landing Gear – Aluminum stamped into horseshoe shape Steel cable attached between two rear wheels Rear landing gear bolted to fuselage Front landing gear attached to allow rotation for steering

Fabrication – Landing Gear

Fabrication Schedule

Updated Budget ItemEstimated CostAvailableFinal Cost SAE Membership$40No$40 R/C Controller$200Yes$0 Engine w/ muffler$180Yes$0 Propeller$20Yes$0 Tires/Axle$10Yes$0 Batteries$20Yes$0 Servos$266No$266 Push Rods$10Yes$0 Fuel Tank$5Yes$0 Balsa$150No$150 Epoxy$30No$30 Monokote$80Yes$30 Misc.$100No$100 Total$1,111 $616

Plan for Phase V Parts have been ordered Fabricate aluminum templates to cut the balsa wood ribs Use materials currently in the storeroom Contact RC pilot to test model when finished Complete aircraft by beginning of April

Title: Heavy Cargo Lift Plane Team Members: William Gerboth, Scott Munro, Jonathan Landis, Harold Pahlck Advisor: Professor Siva Thangam Project #: 3 Date: 2/18/10 Project Objectives Design and build an airplane that conforms to the SAE competition rules and regulations. Plane must navigate a 360 degree after taking off from within a 200 foot runway, and then land successfully on a runway of 400 feet. Constraints of 55 total pounds and a height, width, and length of 200 inches must be followed. Results Obtained in the Semester Height of 12 inches, Length of 68 inches Wingspan of 120 inches, Chord length of 12 inches Eppler 423 airfoil for main wing NACA 0012 airfoil for tail wing Coefficient of lift max = 1.4 Propeller of 14” diameter x 4.5” pitch Takeoff distance = 190 at 46.5 ft/s and 25 pounds Prototype Performance Testing Each component of the assembly will be constructed individually of the others rather than doing several in succession. Changes can be made to one component rather than needing entire sections to be rebuilt. Final Drawing and Illustration Design Improvement Sample airfoils will be constructed to asses lift force and stability by using the wind tunnel. Revising takeoff runway location to grass reduces our payload. Inner support structures will be added for rigidity. Rubber tires will be used to help absorb some of the impact of landing. ME 424 Phase IV Nugget Chart – Performance Testing & Design Improvement