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Solar Probe Technology Challenges

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dc.contributor.author Randolph, James E. en_US
dc.date.accessioned 2004-10-04T20:37:59Z
dc.date.available 2004-10-04T20:37:59Z
dc.date.issued 1995-10 en_US
dc.identifier.citation Albuquerque, New Mexico en_US
dc.identifier.clearanceno 95-1463 en_US
dc.identifier.uri http://hdl.handle.net/2014/32061
dc.description.abstract A mission close to the sun is only possible if new spacecraft technologies can be developed and incorporated into a state-of-the-art spacecraft concept. The perihelion goal of 4 solar radii requires a shielded spacecraft that can tolerate the 3000 suns solar flux while maintaining the electronics components at room temperature. In addition, the shield surface should sublimate at a rate of less than 3 mg/s at perihelion. Many shield configuration designs have been studied and the most promising is a parabolic shape that functions as both a shield and a large high gain antenna. The shield material chosen for this design is a carbon-carbon material with highly emissive surface properties. A mission requirement for a high telecommunications power stems from the expected interference when attempting to transmit data through the solar corona. It is expected that the large carbon-carbon shield/antenna will have a large power gain even at high temperatures and will return adequate telemetry at the X-band radio frequency chosen for the Solar Probe mission. Other key technology needs include a non-nuclear power subsystem that can function in the extreme environments of the mission from Earth to Jupiter and onward to a 4 solar radii perihelion. en_US
dc.format.extent 392382 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other Solar Challenges en_US
dc.title Solar Probe Technology Challenges en_US


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