Nanosat-5

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Nanosat-5

Project Proposal12 February 2008

Chuck Hisamoto (Team Lead)

Jonah WhiteMike LegattChris MatthewsDavid Hauth

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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.

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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

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

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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

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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

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Major Tasks1. Selection of satellite structure geometry, materials,

coating and isogrid patterns.2. Familiarization of software environment for analysis.3. Structural/Vibrational analysis.4. Thermal analysis.5. Complete reports for Nanosat CDR summarizing results.

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Team Organization

D a v id H a u th

C h u ck H isa m o to

M ike L eg a tt

G rou p AT h e rm a l T e am

C h ris M a tth e w s

Jo n ah W h ite

G rou p BS tru ctu ra l/V ib ra tio n a l T e am

T e am Le adC h u ck H isa m o to

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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

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

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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

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Schedule• Gantt Chart: Overview

Schedule, cont’d.

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Schedule, cont’d.

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Schedule, Cont’d.

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Questions