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dc.contributor.authorBoyd, Austin W.
dc.contributor.authorFuhs, Allen E.
dc.date.accessioned2015-09-10T22:07:51Z
dc.date.available2015-09-10T22:07:51Z
dc.date.issued1997-01
dc.identifier.urihttp://hdl.handle.net/10945/46451
dc.description.abstractA general purpose satellite has been designed which will be launched from the Space Shuttle using a NASA Get-Away-Special (GAS) canister. The design is based upon the use of a new extended GAS canister and a low profile launch mechanism. The satellite is cylindrical. measuring 19 inches in diameter and 35 inches long. The maximum vehicle weight is 250 pounds, of which 50 pounds is dedicated to user payloads. The remaining 200 pounds encompasses the satellite structure and support components. which include a hydrazine propulsion system. a 75 watt solar power system an s-band telemetry transmitter and receiver, a 12 megabyte data storage unit and a 16 bit system microprocessor. Active nutation control techniques are employed for spin stabilization about the longitudinal axis. Using the hydrazine propulsion system. circular orbits as high as 835 nm or elliptic orbits with an apogee of 2200 nm are attainable. departing a nominal Shuttle orbit of 135 nm. Pointing accuracies of + /- two degrees are possible Total cost for the satellite and a GAS launch will be approximately $1 million dollars.en_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.titleGeneral Purpose Satellites: a concept for affordable low earth orbit vehiclesen_US
dc.typeArticleen_US
dc.contributor.departmentSpace Systems Academic Groupen_US


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