A joint JPL/Stanford University project is seeking out new technologies to be used on the next generation of small satellites. These microspacecraft have an overall weight of 20 kg. and require miniaturized sensors and instrumentation. One necessary component of a propulsion system is a pressure regulator. This device would require a pressure transducer, microvalve and feedback loop incorporated into a small package using MEMS technology. I am looking for any pointers to research in this area and to purchase this device if it is currently available. The device need not be mil spec. Student projects, new designs, and prototypes are encouraged. Please send any information to erin@storm.jpl.nasa.gov. As a start, here is the first cut at specs for a micro pressure transducer: Cost: < 8K USD Operating Range: 0 to 40 psia 0 to 100 psia 0 to 500 psia Proof Pressure: 1.5 x MOP Burst Pressure: 2.0 x MOP External Leakage: 1EE-6 scc/s Output Voltage: typically 0-3 Vdc or 0-5 Vdc Input voltage: typically 28 vdc, but really up to Gary Linearity +/- 0.5% Hysteresis < 0.2 % of F.S. Repeatability +/- 0.2% of F.S. Operating Temp. Range 15 - 30 deg.C Compensated Temp Range 0.3% of F.S over Operating Temp Range Life Cycles: 50,000 Mass: as small as we can get it - a couple of grams? flow media: nitrogen and helium Internal Cleanliness Level D2 or better of Table I of JPL Spec FS504574 ESD sensitivity prefer that the device is NOT sensitive to ESD Definitions: Linearity: the xducer shall be within x percent of F.S. (full scale) from a straight line between the endpoints, using as output the average value of the two data points obtained at a given pressure when that pressure is approached in the increasing direction from zero and the decreasing direction from full scale. Hysteresis: the difference in outputs at a given pressure, when that pressure is approached in the increasing direction from zero and the decreasing direction from full scale. Repeatability: the difference in transducer output obtained in two successive calibrations at the same pressure, when approached in the same direction. Thanks, #****************************************************************************# # # # Erin M. Defosse Advanced Flight Systems Group # # M/S 301-490 Mission and Systems Architecture Section (311) # # 4800 Oak Grove Dr. NASA/Jet Propulsion Laboratory # # Pasadena, CA 91109 # # # # Tel: (818) 354-2050 E-Mail: Erin.M.Defosse@Jpl.Nasa.Gov # # Fax: (818) 393-6871 erin@storm.jpl.nasa.gov # # # *****************************************************************************#