Form 9.B Project Summary
Chron:
970428
Proposal
Number:
22.01-4422
Project Title:
Spacecraft Microaccelerometer
Microsystem
Technical Abstract (Limit 200 words)
Canopus Systems proposes to perform both
conceptual design and prototype test of a
spacecraft inertial sensing microsystem based upon
a unique MEMS high resolution, novel design
microaccelerometer. The innovative microsystem
design represents technologies sought by
integrating acceleration data sensors, and data
processing with high performance, low power, low
cost subsystem interfaces on a multi-chip module
using advanced packaging techniques. A conceptual
design for a real time in-situ sensor calibration and
test feature is also provided. The project objectives
are to: carry out the microaccelerometer
performance analyses and compare predicted
parameters with prototype test data; develop a
near-optimal sensor design configuration; and
perform an overall microsystem conceptual design
including control, interface and calibration
functions.
The proposed effort includes modeling, simulation,
analyses, prototype sensor test and evaluation,
preliminary system design and environmental
qualification planning. The results anticipated are
development of a recommended microsystem
design with optimized sensor subsystem features to
be implemented in a Phase II flight development
and demonstration program. Space microelectronics
systems applications will include acceleration
measurements for IMU's, structural analyses,
microgravity science, in-space propulsion and
related inertial sensing functions to significantly
reduce the spacecraft's power, mass, volume and
cost requirements via MEMS and microsystem
utilization.
Potential Commercial Applications (Limit 200 words)
The microaccelerometer microsystem can be
utilized for acceleration environment
characterization (structural modeling verification,
microgravity science process disturbances) on
commercial payloads flying on Shuttle, Space
Station and free flyer platforms. The design can
also be utilized in inertial measurement units
installed in commercial spacecraft, in military
avionics, in commercial and civilian avionics and in
personal or mobile navigation sensor microsystems.
The system can also be utilized in seismometry for
commercial oil exploration.
Name and Address of Principal Investigator (Name,
Organization Name, Mail Address, City/State/Zip)
James C. Fox
Canopus Systems Inc.
2010 Hogback, Suite 3; PO Box 130319
Ann Arbor , MI 48113-0319
Name and Address of Offeror (Firm Name, Mail Address,
City/State/Zip)
James E. Rice
Canopus Systems Inc
2010 Hogback, Suite 3; PO Box 130319
Ann Arbor , MI 48113-0319