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MicroMAS 2a, 2b

MicroMAS 2 [MIT]

MicroMAS 2 (Micro-sized Microwave Atmospheric Satellite), is a two three-unit CubeSat mission being developed by the Space Systems Laboratory to integrate an MIT Lincoln Laboratory microwave radiometer payload with a three-axis stabilized CubeSat bus as a follow on to the MicroMAS mission.

Each CubeSat comprises a 2U spacecraft bus with an Attitude Determination and Control System (ADCS), avionics, power, and communications, and a 1U spinning radiometer payload with highly integrated, compact microwave receiver electronics.

Each MicroMAS-2 CubeSat is a dual-spinning 3U CubeSat equipped with a 12-channel passive microwave spectrometer providing imagery near 90 and 206 GHz, temperature sounding near 118 GHz, and moisture sounding near 183 GHz.

In order to effectively collect data with the radiometer sensor, the spacecraft must simultaneously sweep the radiometer field of view perpendicular to the groundtrack while maintaining a 3-axis stabilized orientation fixed in the local vertical local horizontal frame. Analysis determined that it would not be possible to spin the entire satellite and simultaneously maintain the LVLH orientation. This attitude control problem led to a novel design solution to implement a dual-spinner design on the CubeSat architecture, in which a custom designed spinner assembly, would join the rotating payload module to the rest of the satellite.

The MicroMAS-2 demonstration mission now in development is funded by the United States Air Force and the National Oceanic and Atmospheric Administration.

MicroMAS 2b was selected in February 2016 by NASA's CubeSat Launch Initiative. It was to be launched on the ELaNa-20 mission on a dedicated LauncherOne, but was removed from this flight.

Nation: USA
Type / Application: Earth observation, technology
Operator: Massachusetts Institute of Technology - Space Systems Laboratory (MIT SSL)
Contractors: Massachusetts Institute of Technology - Space Systems Laboratory (MIT SSL)
Configuration: CubeSat (3U)
Propulsion: None
Power: 4 deployable fixed solar arrays, batteries
Mass: 5.5 kg (#2); 4.5 kg (#2b)
Orbit: 493 km × 505 km, 97.56 (#2a)
Satellite COSPAR Date LS Launch Vehicle Remarks
MicroMAS 2a 2018-004X 12.01.2018 Sr FLP PSLV-XL with Cartosat 2F, Microsat-TD, LEO Vantage 1, Carbonite 2, ICEYE X1, INS 1C, Arkyd 6A, CICERO 7, Landmapper-BC 3 v2, Lemur-2 68, ..., 71, Flock-3p' 1, ..., 4, PicSat, CANYVAL-X 1, 2, CNUSail 1, KAUSAT 5, SIGMA, DemoSat 2, GeoStare, Fox 1D, STEP Cube Lab, SpaceBEE 1, ..., 4
MicroMAS 2b - 20xx with ?
Further MicroMAS missions:

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