Structures and Thermal Locomotion Phase

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Presentation transcript:

Structures and Thermal Locomotion Phase Caitlyn McKay Structures and Thermal Locomotion Phase 1

Mass Total Mass of Rover = 29.1259 kg Component Mass in Kg Solar Panels 2.5000 Gearhead (x4) 0.0075 Battery 0.3000 Cooler 11.0000 Antenna 0.0800 Aluminum Body 2.3000 Transmitter 0.4200 Space Blanket-Teflon 0.7000 CPU 1.7000 Space Blanket-Kapton 0.8200 Camera 3.1200 Wheel (x4) 1.2207 Motor (x4) 0.0230 Power (Extra) 1.0000 Mounts (x8) Total Mass of Rover = 29.1259 kg Dimensions of Rover = .407 m x .497 m x .456 m 2 Caitlyn McKay Structures and Thermal

Stress of Rover on Motor Shaft Stage Maximum Mass w/o Further Support Earth 10.2kg Launch 1.3 kg Landing 1.0kg Moon 61.4 kg 3 Caitlyn McKay Structures and Thermal

Stress of Rover on Shaft 4 Caitlyn McKay Structures and Thermal

Stress of Rover on Shaft Maximum mass for the shaft of .01 m diameter while on the moon: 61.4 kg 5 Caitlyn McKay Structures and Thermal

Structures and Thermal Diameter of Shaft Needed to Support Rover on Earth Assumption: gravitational force=9.80665 m/s^2 6 Caitlyn McKay Structures and Thermal

Structures and Thermal Diameter of Shaft Needed to Support Rover during Launch Assumption: gravitational force = 9.80665 m/s^2 gravitational force = 7.5 7 Caitlyn McKay Structures and Thermal

Structures and Thermal Diameter of Shaft Needed to Support Rover during Soft Landing Assumption: gravitational force = 9.80665 m/s^2 gravitational force = 10 8 Caitlyn McKay Structures and Thermal

Structures and Thermal Diameter of Shaft Needed to Support Rover on Moon Assumption: gravitational force=9.80665/6 m/s^2 9 Caitlyn McKay Structures and Thermal

Buckling of Aluminum Body Buckling Stress: 82,300 kg/m^2 10 Caitlyn McKay Structures and Thermal

Structures and Thermal Energy Usage Component Energy Solar Panels 35 Wh Gearhead N/A Battery 40 Wh Cooler 20.00 W Antenna 0.20 W Aluminum Body Transmitter 6.25 W Space Blanket-Teflon CPU 5.00 W Space Blanket-Kapton Camera 18.00 W Wheels Motor 5.40 W Power (Extra) Mount 11 Caitlyn McKay Structures and Thermal

Operating Temperatures Component Operating Temp in K Solar Panels N/A Gearhead 398.15 Battery 233.15-333.15 Cooler Antenna 253.15-323.15 Aluminum Body 218.15-383.15 Transmitter Space Blanket-Teflon 533.1500 CPU Space Blanket-Kapton 4.15-673.15 Camera 273.15-313.15 Wheels Motor Power (Extra) Mount 12 Caitlyn McKay Structures and Thermal

Structures and Thermal References: 2008. CES EduPack2008. Citrix Client. Purdue University, West Lafayette, IN. Grandt, Alten F. Fundamentals of Structural Integrity. Hoboken, NJ: John Wiley & Sons, Inc., 2004. 13 Caitlyn McKay Structures and Thermal