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Structures PDR 1 Team Boiler Xpress Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal VanMeter October 12, 2000.

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Presentation on theme: "Structures PDR 1 Team Boiler Xpress Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal VanMeter October 12, 2000."— Presentation transcript:

1 Structures PDR 1 Team Boiler Xpress Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal VanMeter October 12, 2000

2 Topics of Discussion  Aircraft Weight  Wing Weight Estimation  Structural Material Properties  Wing, fuselage, pods  Wing layout  Spars  Load Analysis  Theoretical Model  Maximum Bending Moment and Deflections and Diagrams  Test of Actual Wing

3 Topics of Discussion  Weight Estimation  Center of Gravity  Parts Location  Landing gear system

4 Aircraft Weight

5 Wing Weight Estimation

6 Structural Materials: Wing Balsa Light weight/very strong in compression and tension with the grain Density = 11lb/ft 3 E= 625 ksi Yield Stress = 1725 psi (Actual Test Result; Whiskey Tango Team, Spring 1999) Styrene Foam Easily worked with hotwire or cutting tools Gives true airfoil shape Works well in compression when load is well distributed-serves as shear member Not strong enough for bending loads Density = 1.42 lb/ft 3

7 Fiberglass Good for complex shapes Strong Skills needed 3 layers of 1.5 oz cloth with resin = 9 oz/sq. yd. Carbon Fiber Booms Light weight & Strong Structural Materials: Fuselage and Pods

8 Wing Spar Box Structure Rear spar for control surface hinges Styrene wing core Balsa spars carry bending load 0.375 in x 0.25 in L.E. Reinforcement Assumptions: Box beam (ease of analysis) Moment of Inertia (Stringers) Spars carry loads & positioned at max camber

9 Analysis of Loads Model as cosine lift distribution Structural weights distributed along span Method of Analysis (Theoretical Model)

10 Bending Moments Maximum Moment = 25.86 lb/ft Safety Factor = 2.5g * 1.5

11 Wing Deflection Max Deflection = 1.93 inches

12 Stress in the Wing Sigma max = 1241 psi Sigma critical = 1725 psi Reasons:  Light Weight Structure (not Bulky)  Safety Factor (worst case scenario)  Wing Test Sand Bags

13 Geometry and Configuration Wing: Sref = 13.5 sq.ft. Span = 11 ft. Aspect Ratio = 9 Taper Ratio = 0.6 tip section Airfoil: S1220 Horizontal Stabilizer: Area = 2.1 sq ft. Span = 3.0 ft. Vertical Stabilizer: Total Area: 2.0 sq.ft. 11.1’ 5.8’ Boiler Xpress


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