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| Micro-Electromechanical Systems |
| In-Cabin |
| Prime: Steven Hawley |
| Backup: Cady Coleman |
| Overview |
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The Micro-Electromechanical Systems experiment examines the performance of a suite of devices under launch, microgravity, and reentry conditions. These devices include accelerometers, gyros, and environmental and chemical sensors. The MEMS payload is self-contained and requires activation and deactivation only. All experiment operations are monitored and recorded by integrated components. Power, however, is required from just before ascent through deorbit. The MEMS payload uses one middeck locker with a modified door (front panels removed). An accelerometer and mounting plate will be attached to the inside back of the middeck locker before the payload is installed. A power cable will be connected to the MEMS locker during installation. Micro-electromechanical systems have already found their way into our lives (air bag triggers, combustion control sensors, ink-jet printer heads, etc.). Electronic fabrication technology, micromolding, and laser processing are being used to carve miniature machines out of silicon and integrate them with electronics to create MEMS. Because of their low weight, low power consumption, and low volume, MEMS devices are extremely attractive for potential spacecraft applications. They are also very reliable, low cost, and somewhat autonomous from other systems. This program, sponsored by the Air Force Research Lab, Kirtland AFB, N.M., is the first systematic flight testing of MEMS to confirm their advantages for space applications. The experiment is basically a testbed for microdevices that have specific uses in space. Several types of microaccelerometers and microgyros that can be used to monitor large spacecraft or navigate miniature spacecraft will be tested during the launch phase and on orbit to see if such conditions affect their performance. Chemical microsensors will monitor the middeck environment for traces of potentially harmful gases such as carbon dioxide, methane, and hydrogen. Subminiature arrays of solid rocket motors being developed for attitude control will be tested for configuration stability during launch and material stability in orbit. Very high density nanoelectronic devices will be tested for operational stability in the enhanced radiation environment of space, and the performance of a microarray of thermal control elements will be evaluated. These devices represent functions (navigation and control, sensing, propulsion, computation, thermal control) that are required for spacecraft of any size. They were chosen for this experiment because the near-term goal is to exploit the advantages offered by MEMS for all spacecraft. |
| History/Background |
| The MEMS payload is integrated and flown under the direction of the DOD Space Test Program Office at Johnson Space Center in Houston, Tex. This is its first flight. |
| Benefits |
| Micro-electromechanical systems offer great potential benefits for spacecraft application: low weight, low power consumption, low volume, high reliability, low cost, and a certain degree of autonomy. |
Editorial/Technical Comments: ShuttlePresskit
