1 Krzysztof Pennar Moshe Zilversmit Jon Winkler John Pignetti Ariane Mortazavi Takeshi Fuchiwaki Josh Fromm Structures Team Fall 2004 Final Report

2 Baseline Mission Current Work: Pin Pullers and Hinges Updated Solidworks files Preliminary FEA New bus configuration Individual Component Radiation Hardening Trade: –Showed increase in mass of 1.12 kg.

3 New Bus Configuration A preliminary FEA showed that a solid panel bus should be redesigned Designed a X-panel bus which weights 3.055kg Key design issue: Induced moment from being a piggyback satellite.

4 Upscope Mission Maintain mass savings with a new bus design vis-à-vis FEA A hexagonal bus design was chosen for more stability. It weights kg.

5 Descope Mission With no propulsion tank bus size was reduced to a 30x30x15 cm box. Panels were kept solid due to radiation hardening trade. Bus mass is 5.85 kg.

6 Mass Savings and Updated Moments Previous Mass (kg) New Mass (kg) Savings (kg) Baseline Descope Upscope Baseline Moments of Inertia (kg * m^2): Ix = Iy = Iz = Descope Moments of Inertia (kg * m^2): Ix = Iy = Iz = Upscope Moments of Inertia (kg* m^2); Ix = Iy = Iz = 1.117