Purdue_CubeSat_PDR_Presentation

Purdue_CubeSat_PDR_P - A&AE490Satellite PurdueCubeSat December8,2004 8December2004 FacultyAdvisorProf.DavidFilmer 8December2004 8December2004

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Preliminary Design Review 8 December 2004 Purdue CubeSat Preliminary Design Review December 8, 2004
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Preliminary Design Review 8 December 2004 Project Engineer – George Pollock  Faculty Advisor – Prof. David Filmer
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Preliminary Design Review 8 December 2004
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Preliminary Design Review 8 December 2004 Poly Picosat Orbital Deployer (P-Pod) Interface between CubeSat and LV Reliable on-orbit deployment Separation and low spin rate
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Preliminary Design Review 8 December 2004 CubeSat Guidelines: No interference Space debris Clean deployment Power off for integration and launch Mass ≤1kg C.M. within 2cm of geometric center Structure: P-Pod interfacing requirements P-Pod cannot be used to constrain  deployables Operations requirements System Level Requirements
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Preliminary Design Review 8 December 2004 System Level Requirements PURDUE CubeSat MISSION OBJECTIVES SCIENCE: Measure radiation environment on orbit Record and transmit radiation data ENGINEERING: Achieve passive attitude stabilization in nadir orientation Demonstrate limited active attitude control (can be open  loop)
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Preliminary Design Review 8 December 2004 Subsystems Structures  Payload  Attitude Dynamics and Control  Systems Communications Computer  Power
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Preliminary Design Review 8 December 2004 Structures Overall Goal Model general structure, and components Coordinate with other subsystems Adjust structure, and           components to meet  design requirements
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Preliminary Design Review 8 December 2004 Structures Modeling Create a CATIA  model of the  structure Create models of  subsystem  components
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Preliminary Design Review 8 December 2004 Structures Coordination with other subsystems Component sizes and masses Location of components Met with members of each subsystem to  determine where components could and  couldn’t be placed
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Preliminary Design Review 8 December 2004 Structures Meet Requirements Satellite center of mass, total mass, and  volume requirement Determined the best location and size of the  different components All structural frequencies must be greater than  20 Hz
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Preliminary Design Review 8 December 2004 Structures General Layout General sizes and shapes of  components Location of components
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Preliminary Design Review 8 December 2004 Mass Budget Subsystem Component Percentage of Total Allocated Mass (g) Structure Structure 20% 200 GG boom GG deployment mech. 2 sun sensors 3 Electromagnet(s) power computer 70 detector/com computer TNC 20 tranceiver 50 antennae 30 solar cells batteries (2) 160 capacitors (2) 120 Electrical Interfaces voltage converter 3% camera 110 radiation detector 90 Total Mass 743 Budgeted Attitude Dynamics and Control System 15% 12% Science Payload Power Communications Central Computer 20% 20% 10%
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This note was uploaded on 01/15/2012 for the course AAE 490 taught by Professor Andrisani during the Fall '09 term at Purdue University-West Lafayette.

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Purdue_CubeSat_PDR_P - A&AE490Satellite PurdueCubeSat December8,2004 8December2004 FacultyAdvisorProf.DavidFilmer 8December2004 8December2004

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