1. Eric Weber (1/14)1 Configuration and Structural Design Eric Weber Tasks –Preliminary hardware research –Preliminary transmission research –Materials Research –Solid Modeling –Satellite Configuration –Kept Mass Budget Total Hours: 75

2. Eric Weber (2/14)2 Configuration and Structural Design Design Requirements –University Nanosat Must be less than 50x60x60 cm Must be less massive than 50 kg –Mission specific Must withstand mission of 24 hours

3. Eric Weber (3/14)3 Configuration and Structural Design Derived Requirements and Goals –Center of mass to be within 1.5 cm of geometric center (ADC) –Camera and Star Tracker looking at 90º angle from each other (ADC) –4 Thrusters (ADC/Orbit) Thrust line on the same plane Through center of mass At 90 º angles from the camera

4. Eric Weber (4/14)4 Configuration and Structural Design Derived Requirements and Goals (cont.) –Solar cell panels on all faces except camera face (Power) –Attempt to keep components away from satellite walls (Thermal)

5. Eric Weber (5/14)5 Configuration and Structural Design Must be less than 50x60x60 cm 50 cm

6. Eric Weber (6/14)6 Configuration and Structural Design PieceDimensions (cm)Mass (g)Volume(cm^3) Thruster x41.5D x 3.0232.8 N2 Tank12.0D x 28.940002251.5 Camera15.0 x 15.0 x 4.0960900.0 Lens16.0D x 35.012704889.2 Battery x215.0 x 7.0 x 7.01400735.0 Electronics Controller30.0 x 30.0 x 7.035006300 CPU9.6 x 9.1 x 2.096174.7 Star Tracker5.4 x 5.4 x 15.66001011.5 Reaction Wheel11.8 x 11.8 x 11.519861272.6 Gyro9.9 x 11.7 x 3.1439359.0 GPS Comp x214.0 x 8.9 x 11.74501458.0 GPS antennas x23.8 x 2.9 x 1.12011.6 Solar Cell Panels x548.0 x 48.0 x 0.533651152.0 Aluminum Panel48.0 x 48.0 x 0.631101152.0 Satellite Structure50.0 x 50.0 x 50.07434125000.0 Mass of Hardware44.0kg Extra Parts (conservative estimate)5kg Total49.0kg

7. Eric Weber (7/14)7 Configuration and Structural Design Must withstand mission of 24 hours –Short satellite mission time –Satellite is to be carried up with shuttle Greatest force < 50 N –Material Selection Aluminum 6061 T6 –Availability –Cheap –Adequate

8. Eric Weber (8/14)8 Configuration and Structural Design Center of mass calculation SolidWorks can calculate these numbers –Iterative process to find an adequate center of mass Center of mass location offset from geometric center –X = 0.29 cm –Y = 0.15 cm –Z = 0.01 cm

9. Eric Weber (9/14)9 Configuration and Structural Design

10. Eric Weber (10/14)10 Configuration and Structural Design Camera and Star Tracker looking at 90º angles from each other 4 Thrusters facing each other with thrust line through the center of mass at 90 º angles from the camera Thrusters

11. Eric Weber (11/14)11 Configuration and Structural Design Solar cell panels on all sides except camera side

12. Eric Weber (12/14)12 Configuration and Structural Design Attempt to keep components away from satellite walls (Thermal)

13. Eric Weber (13/14)13 Configuration and Structural Design All requirements and goals were met Must be less than 50x60x60 cm Must be less massive than 50 kg Must withstand mission of 24 hours Center of mass is to be within 1.5 cm of geometric center Camera and Star Tracker looking at 90º angle from each other 4 Thrusters facing each other with thrust line through the center of mass at 90 º angles from the camera Solar cell panels on all sides except camera side Attempt to keep components away from satellite walls

14. Eric Weber (14/14)14 Configuration and Structural Design Recommendations for Future Work –Thin out aluminum frame and supports For lower mass –Model small parts For more accurate model