Nanosat-5

1. Nanosat-5 Project Proposal 12 February 2008 Chuck Hisamoto (Team Lead) Jonah White Mike Legatt Chris Matthews David Hauth

2. Objective The aim of this project is to perform and validate thermal, structural and vibrational analyses on the Nanosat-5 satellite. The tests will ensure that the vehicle is capable of withstanding loads, vibrations and temperatures, as specified by the University Nanosat Program.

3. Requirements • Adhere to limiting factors outlined by the University Nanosat Program: • Structural/Vibrational • Withstand limit load factors of +/- 20g’s of force in all directions (nX, nY, and nZ) at SIP, resist yielding • Maintain fundamental frequency above 100Hz • Maintain safety factors of 2.0 for yield and 2.6 for ultimate for structural design and analysis • Undergo sine sweep test, sine burst test, Random vibration test, Shock test • Interior of the battery box has a non-electrically conductive coating

4. Requirements, cont’d. • Thermal • Provide thermal models of Goldeneye with nodes for each of the temperature critical components onboard • Provide complete list of heat sources and their profiles • For each component and at each node of the thermal models determine: • Operating temperature: Temperature at which the component will function and meet all requirements • Non-operating temperature: Component specifications are not required to be met. Component can be exposed in a power off mode. If turned to power on mode, damage must not occur • Survival temperature: Permanent damage to the component • Safety temperature : Potential for catastrophic damage

5. Requirements, cont’d. • Thermal, cont’d. • Provide properties of external surfaces on satellite including material size, absorptivity (alpha), and emissivity (epsilon) • Continuously maintain thermal environment at component operating temperatures

6. Expectations • Complete thermal, structural and vibrational analyses on the Nanosat-5 design and validate that results adhere to University Nanosat Guidelines • Include satellite structure schematics, component lists with analysis results • Compile complete reports on each analysis for Nanosat CDR

7. Major Tasks • Selection of satellite structure geometry, materials, coating and isogrid patterns. • Familiarization of software environment for analysis. • Structural/Vibrational analysis. • Thermal analysis. • Complete reports for Nanosat CDR summarizing results.

8. Team Organization

9. Task Breakdown • Selection of satellite structure geometry, materials, coating and isogrid patterns. • Design/modifications of body geometry • Design component locations/mounting • Design torque coil mounting • Body and housing material selection • Selection of thermal coating • Implement isogrid patterns • Familiarization of software environment for analysis. • ProE • Ansys • Import methods

10. Task Breakdown, cont’d. • Structural/Vibrational analysis. • Structural • Receive completed structural design • Import into analysis software • Establish boundary conditions • Apply load/acceleration limits • Mesh application • Run simulations/Verify results • Vibrational • Import into analysis software • Apply cyclic loading at varying frequencies • Run simulations/Verify results

11. Task Breakdown, cont’d. • Thermal analysis. • Receive determined component locations • Obtain relevant thermal constants • Determine boundary conditions • Generate thermal model for component heat sources • Determine need/design for heat dissipation • Reports • Write Structural & Vibrational Analysis Report • Write Thermal Analysis Report • Prepare all CDR slides

12. Schedule • Gantt Chart: Overview

13. Schedule, cont’d.

14. Schedule, cont’d.

15. Schedule, Cont’d.

16. Questions