MMS
Mission Life
Conformation July 2009
Planned Launch Fourth Quarter of 2014 (August 14, 2010)
2 Years and 6 Months in Orbit
Launch Vehicle Atlas V 421
Estimated Cost $135.75 Million
2 Phase Orbit Strategy
Main Mission (SMART- Solving Magnetoshperic, Acceleration, Reconnection, and Turbulence) Overview Unmanned space mission intended to study the microphysics of magnetic reconnection using the Earth' magnetosphere as the test ground. The mission also intends to investigate how energy conversion that occurs in reconnection accelerates particles to high energies, and what role plasma turbulence plays in the process, and how they all affect the phenomena known as "space weather". Basically: Explore the plasma processes that govern the interaction of the Earth's magnetic field with the solar wind. Magnetic Reconnection- plasma-physical process that converts magnetic energy into heat.
The mms spacecraft will employ an atlas v expendable launch vehicle to get the mms into orbit of about 1.2earth radii
Orbit: It will orbit the earth at 1.2 earth radii by 12earth (dayside); 1.2 Earth radii by 25 earth radii on the night side
Science payload:
The MMS mission calls for four identical spacecraft in order to gather the measurements needed by NASA. Each spacecraft will have identical scientific payloads. The MMS spacecraft were designed for simplicity and ease of packaging to simplify launch procedures. the type of scientific instrumentation the mms employs is: Fast Plasma Instrument; FIELDS; Hot Plasma Composition Analyzer; Energetic Particles; Active Spacecraft Potential Control; Central Instrument Data Processor Also, the spacecraft has a cylinder structure in the center of the octagon. When stacked on top of each other, this forms a very strong structure capable of withstanding the pressure of takeoff. The spacecraft are powered by solar energy. Eight solar array panels allow the spacecraft to capture the suns' energy. The spacecrafts have a very "open" configuration which allows easy access to instruments inside the spacecraft. The propulsion system consists of four hydrazine propellant tanks located within the thrust tube and four axial and eight radial thrusters. The MMS spacecraft are spin-stabilized, with a nominal spin rate of 3 rpm. Attitude knowledge is provided by 4 star cameras, 2 three-axis accelerometers, and 2 sun sensors, with the thrusters being used for attitude and orbit adjustment maneuvers. A GPS receiver on board each spacecraft provides absolute position information. In addition, each spacecraft employs an interspacecraft ranging and alarm system (IRAS) to determine its location relative to the other three spacecraft.