Solar Probe Plus Mission Update
- Paper number
IAC-11,A3,5,3,x11784
- Author
Mr. Brian Morse, The John Hopkins University Applied Physics Laboratory, United States
- Coauthor
Dr. James Kinnison, The John Hopkins University Applied Physics Laboratory, United States
- Coauthor
Dr. Mary Kae Lockwood, The John Hopkins University Applied Physics Laboratory, United States
- Coauthor
Mr. Edward Reynolds, United States
- Coauthor
Dr. Nicola Fox, JHU Applied Physics Laboratory, United States
- Year
2011
- Abstract
Solar Probe Plus (SPP) will be the first mission to fly into the low solar corona, revealing how the corona is heated and the solar wind is accelerated, solving two fundamental mysteries that have been top-priority science goals for decades. Thanks to an innovative design, emerging technology developments and a significant risk reducing engineering development program these critical goals will soon be achieved. The Johns Hopkins University Applied Physics Laboratory in Laurel, Maryland, is designing and building the Solar Probe Plus system and managing the project for NASA’s Living with a Star Program. The SPP science objectives are: 1) Trace the flow of energy that heats and accelerates the solar corona and solar wind. 2) Determine the structure and dynamics of the plasma and magnetic fields at the sources of the solar wind. 3) Explore mechanisms that accelerate and transport energetic particles. SPP will launch no later than 2018, performing 24 orbits over a 7-year duration. The mission design utilizes seven Venus gravity assists to gradually reduce perihelion (Rp) from 35 solar radii (Rs) in the first orbit to <10 Rs for the final three orbits. A 0.6m diameter high gain antenna operates at Ka-band for science data downlink. This allows 128Gbit of data to be downlinked for each of the final three solar encounters (Rp < 10Rs), thereby meeting mission requirements. SPP also provides 128Gbit/orbit for most of the earlier 21 orbits. The SPP spacecraft is 610kg wet at launch, 3m in height and 2.3m in diameter at the thermal protection system (TPS). At 9.5Rs, the solar intensity is 512 times that at 1AU. SPP is packaged behind the Carbon-Carbon TPS to protect it from this extreme solar environment and allow it to operate at standard space thermal environments while the TPS experiences temperatures of 1400degC on its sun-facing surface. SPP utilizes actively cooled solar arrays for power generation maintaining the solar cells within required temperature limits. SPP is currently in Phase A with a combined Systems Requirements Review(SRS)/Mission Definition Review (MDR) planned for September 2011. In the fall of 2010 NASA .selected the instrument suite for SPP. This paper will describe the SRR/MDR design as it has evolved to incorporate the selected instrument suite and the results of the technology development testing that has completed during Phase A.
- Abstract document
- Manuscript document
IAC-11,A3,5,3,x11784.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.