The MESA sensor used in MAMS is a flight spare from the OARE program. The MESA consists of a hollow, cylindrical flanged proofmass, two X-axis forcing electrodes , an outer cylindrical proofmass carrier with Y and Z-axis electrodes and control electronics contained in a protective case. The sensor proofmass is constrained via electro-static force feedback to remain centered between the cylindrical axis forcing electrodes and the radial axes carrier electrodes. The resulting 'sensed' acceleration is proportional to the voltage required to generate the centering force.

The MESA is mounted on a Bias Calibration Table Assembly (BCTA). The BCTA is a dual-gimbal mechanism, which allows the MESA sensor to be calibrated on-orbit. Calibration is used to remove electronic bias from acceleration data. Signal processing algorithms will be applied to the MESA bias calibration data to achieve absolute quasi-steady acceleration data with very high accuracy. Multiple calibrations taken over long operations periods will be used to further improve accuracy.

During early increments, MAMS will require a minimum operational period of 4 days (96 hours) in order to characterize the performance of the sensor and calculate sensor bias. During later increments, MAMS can be activated for time periods sufficient to satisfy payload or vehicle needs for acceleration data.