Inertial Navigation System Accelerometer
Problem We Solve
A key challenge for navigation systems is making them smaller, less expensive and more robust while preserving high-end performances grade.
A sensor unit of 3 accelerometers and 3 gyroscopes – an IMU – produces a three dimensional measurement of the acceleration and angular rate. IMUs may feature a processor, a memory and a temperature sensor to deliver digital interfaces and sensor’s calibration model. An IMU is the basic block delivering information on the position, velocity and orientation of an object relative to a starting point, to a higher system, an Inertial Navigation System (INS).
Why it is Important
Navigation systems providing flight control on aircraft have to count on autonomous, accurate and proven sensors – accelerometers and gyroscopes – to ensure safe and comfortable flights.
MEMS accelerometers, based on batch manufacturing, offer a very attractive SWaP. MEMS sturdy design and rugged assembly ensure performances repeatability even under high shock and vibration.
How We Solve it
The innovative MS1000 Accelerometer responds to tactical grade performance requirements due to the excellent bias and scale factor performances (+/-10 g) :
- Bias residual modeling error: 0.7 mg
- Long term bias repeatability: 1.2 mg
- SF residual modeling error: 120 ppm
- Long term SF repeatability: 400 ppm
Why Choose Us
Coupled with RLG, FOG, HRG gyros MEMS accelerometer MS1000 may be integrated in tactical grade navigation systems with the bias class error of 1°/hour. Thus MS1000 is perfectly fit with the specifications of such aeronautical systems as hybrid INS for small civil/military transportation aircrafts, drone autopilot systems, helicopter AHRS.
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