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 [email protected].

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: [email protected]               #
# Fax: (818) 393-6871              [email protected]                   #
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