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Mission Description: Low earth orbit science and technology demonstration mission

University Nanosat Program (NS-3): Quick-to_Orbit: Utah State University. Principal Investigator/University: Charles Swenson, (435) 797-2958, charles.swenson@usu.edu; Utah State University; Logan UT 84322-4120 Co-Investigators/Industry Partners: Rees Fullmer, rrfullmer@mae.usu.edu ;

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Mission Description: Low earth orbit science and technology demonstration mission

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  1. University Nanosat Program (NS-3): Quick-to_Orbit: Utah State University • Principal Investigator/University: • Charles Swenson, (435) 797-2958, charles.swenson@usu.edu; • Utah State University; Logan UT 84322-4120 • Co-Investigators/Industry Partners: • Rees Fullmer, rrfullmer@mae.usu.edu; • Todd Mosher tjmosher@mae.usu.edu; • Industrial Sponsor: Space Dynamics Laboratory • Student Team Leads: • Tyler Goudie, System Engineering tjg@cc.usu.edu • Joel Quincieu, Mechanical Systems, joel.quincieu@sdl.usu.edu • Jeff Ward, Communications, jward@cc.usu.edu • Education & Public Outreach (EPO) Approach: • Galye Bowen, Space Dynamics Laboratory • Mission Description: • Low earth orbit science and technology demonstration mission • Mission Objectives: • Acquire scientific data on the fundamental parameters of ionospheric density irregularities. • Provide low-cost spacecraft bus for communication test missions. • Validate a quick design-manufacture-fly approach to spacecraft production. • Investigate approaches to autonomous operations. • Technologies to be Validated: • Flight test of a PDA-level avionics package. • Integrated command and data handling system, including direct software access to the spacecraft. • Low power 3 axis momentum attitude control. • Use CMOS cameras for star and sun sensors. • Validate Utah State University ground station. • Composite thermal heat-pipe experiments • Nanosat Subsystem Key Attributes: • Combined magnetic torquing/reaction wheel system. • An integrated electronics assembly with PDA-based CPU board 80 MHz with 16Meg memory, telemetry board, power conditioning, sensor I/O, camera interface, reaction wheel and torquer controllers • Aluminum isogrid structure • Uplink 450 MHz 9600 baud, Downlink 2.2 GHz.115.2 kbits/sec • Heat-pipe thermal distribution • Deployable solar panels • On-campus ground station • Other Attributes: • Electron density plasma impedance probe • Deployment Mechanism: Lightband from Planetary Science Inc. • 370 km. Altitude, minimum 51° inclination • Previous experience: Nusat, Skipper, USUSat

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