Computer Science – Performance
Scientific paper
Jan 2001
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001iaop.work...91w&link_type=abstract
Forum on Innovative Approaches to Outer Planetary Exploration 2001-2020, p. 91
Computer Science
Performance
Microelectromechanical Systems, Gyroscopes, Miniaturization, Space Missions, Automatic Control, Space Exploration, Technology Utilization
Scientific paper
The evolution of inertial grade gyroscopes for space applications represents well over 50 years of technology development and an investment of hundreds of millions of dollars. The workhorse product which represents the current state-of-the art for commercially available high performance devices is the Litton-Hemishperical Resonator Gyro (HRG) Inertial Measurement Unit (IMU). This product has a performance figure of merit of 0.003 deg/hr bias drift, a volume of 567 cubic inches, weighs 19 pounds, draws about 30 watts and costs over 1 million each. Clearly devices of this magnitude are not conducive to the minimized mass, volume, power, and cost constraints of outer planet missions. An approach to breaking these potential barriers is the use of Microelectromechanical Systems (MEMS) based inertial devices. Although substantially reduced in size, mass power and cost, this approach has produced devices in the tactical performance range of greater than 1 deg/hour bias drift. This level of performance satisfies the preponderance of high market volume requirements such as automotive and tactical munitions but does not meet the limited market quantity requirements for the high precision space based market. Because of the very limited size of the space based market, there is little economic incentive for commercial fabricators of tactical grade devices to address the necessary performance improvements. The Jet Propulsion Laboratory (JPL) in conjunction with Boeing Space Systems (BSS) is addressing this void to satisfy our mutual requirements in this area. The project objective to is to achieve 0.01 deg/hr performance in an IMU which is less than 10 cubic inches in volume, weighs less than 0.5 pounds, draws less than 1 watt and is available in volume production for less than 2500. Reductions of this magnitude will be mission enabling capabilities for a variety of anticipated outer planet mission attributes such as autonomous control and docking, formation flying and robotic outposts. The improved performance will be realized using improved relative precision fabrication, enhanced vibratory drive and sense designs, and statistical data analysis.
Bae Sukang
Blaes B.
Challoner A. D.
D'Agostino S.
Hayworth K.
No associations
LandOfFree
A Highly Miniaturized Inertial Grade Gyroscope for Space Applications does not yet have a rating. At this time, there are no reviews or comments for this scientific paper.
If you have personal experience with A Highly Miniaturized Inertial Grade Gyroscope for Space Applications, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and A Highly Miniaturized Inertial Grade Gyroscope for Space Applications will most certainly appreciate the feedback.
Profile ID: LFWR-SCP-O-1361728