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Krzysztof PennarMoshe ZilversmitJon WinklerJohn PignettiAriane MortazaviTakeshi FuchiwakiJosh Fromm

Structures Team

Fall 2004 Final Report

22

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.

33

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.

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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 5.487 kg.

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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.

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Mass Savings and Updated MomentsPrevious

Mass (kg)

New Mass (kg)

Savings (kg)

Baseline 7.865 3.055 3.69

Descope 7.865 5.85 2.015

Upscope 7.865 5.486 1.212

Baseline Moments of Inertia (kg * m^2):Ix = 0.6915Iy = 0.7981 Iz = 1.2180

Descope Moments of Inertia (kg * m^2):Ix = 0.644 Iy = 0.661 Iz = 0.160

Upscope Moments of Inertia (kg* m^2);Ix = 0.581Iy = 0.734Iz = 1.117