National Aeronautics and Space Administration National Aeronautics and Space Administration The U.S. Government's Official Web Portal National Aeronautics and Space Administration National Aeronautics and Space Administration
NASA Banner spacer Banner Spacer spacer spacer
Advanced Search
Go button
spacer About NASA About NASA Glenn Exploration Systems Mission Directorate
ISS Research Project MAMS banner
ISS Research Project @ ARC
ISS Research Project @ GRC
ISS Fluids & Combustion Facility
FCF Investigations
Microgravity Science Glovebox
Announcement Background spacer
Microgravity Acceleration Measurement System (MAMS)


September 29, 2010 –
MAMS supported the Soyuz TMA-18 undocking from the International Space Station on September 24, 2010.  The ISS crew members were on the International Space Station for six months and returned on Soyuz; the crew included Tracy Caldwell, Mikhail Kornienko, and Alexander Skvortsov, all three returned safely on September 25, 2010.  The MAMS acceleration sensor measured the undocking event vibrations imparted to the ISS.

The MAMS is a complimentary acceleration measurement system to SAMS.  While the SAMS system measures acceleration disturbances from 0.01 to 400 Hz, the MAMS measures accelerations from DC to a maximum of 0.01 Hz.  MAMS provides this complimentary function by measuring accelerations caused by the aerodynamic drag of the ISS as it orbits the earth.  In addition, MAMS measures accelerations caused by small ISS attitude adjustments and ISS gravity gradient effects. These quasi-steady accelerations are confined in the frequency range below 1 Hz. MAMS consists of a low-frequency triaxial accelerometer, the Miniature Electro-Static Accelerometer (MESA), and associated computer, power, and signal processing subsystems contained within a Double Middeck Locker enclosure.

The MAMS 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 enclosed in a protective case. Static electricity forces the sensor proofmass to remain centered between the electrodes. The "sensed" acceleration is proportional to the voltage needed to keep the sensor centered.  The MAMS MESA is mounted on a Bias Calibration Table Assembly (BCTA) with a dual-gimbal rotation system.  The BCTA and dual-gimbal systems allow the MAMS MESA to perform on-orbit bias calibrations.  With the MAMS electronic bias measured, the extremely small quasi-steady accelerations can be accurately sensed and transmitted to the ground to the Glenn Research Center Telescience Support Center for analysis and archive.

Related Web Sites

* Principal Investigator Microgravity Services (PIMS) Results Home Page
* NASA Glenn Research Center - SAMS
* NASA Glenn Research Center - MAMS




Contacts at NASA Glenn Research Center
Project Manager: Robert W. Hawersaat

Acceleration Measurements
Principal Investigator Microgravity Services
Express Racks
Maintentance Work Area
Expendable Launch Venicle Investigations
Telescience Support Center
ISS Research Project @ JSC
ISS Research Project @ JPL
ISS Research Project @ KSC
ISS Research Project @ MSFC

ISS Research Project Links
Space Station Research & Technology  
Space Station Project Links
  Space Acceleration Measurements System - II (SAMS-II)  
  Microgravity Acceleration Measurement System (MAMS)  
Acceleration Links
pdf icon Publications & Presentations
Space Flight Systems Links
  Space Flight Systems @ GRC
  Human Research Program  
This Month in Exploration  
GRC Microgravity and Technology Flight Experiments
Acceleration Related Documents
small acrobat icon  SAMS Overview Chart  
small acrobat icon  MAMS Overview Chart  
small acrobat icon  PIMS Overview Chart  

Adobe Acrobat

Footer seperator
FirstGov Logo

+ Freedom of Information Act
+ Privacy Policy and Important Notices
+ Applications and Plugins for Viewing Documents and Media

Tim Reckart
NASA Official: Thomas St. Onge
Last Updated: February 8, 2011
Footer spacer
Footer spacer