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 IMUAn IMU or Inertial Measurement Unit is an electronic device that measures the heading and orientation and velocity of a vehicle. It contains both an accelerometer and a gyroscope to provide necessary data to maneuver an aircraft or spacecraft, especially when GPS signals are not available. – produces a three dimensional measurement of the acceleration and angular rate.  They 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 Nav System (INSAn INS or Inertial Navigation System - sometimes used synonomously with IMU is a device used to measure a vehicle's speed, position, velocity, heading and orientation by using an accelerometer and a gyroscope.).

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.

MEMSMicroElectroMechanical System. See also 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 RLGRing Laser Gyroscope. Uses interference of laser light within an optical ring to detect changes in orientation and spin. See also, FOGFiber Optic Gyroscope. Uses the interference of light to detect mechanical rotation. See also, 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 AHRSAttitude Heading Reference System. 3-axis sensors that provide heading, attitude and yaw information for aircraft. Replaces traditional mechanical gyroscopic flight instruments. See also.

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