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FOG Inertial Navigation System

ER-70X FOG Inertial Navigation System

ER-70X FOG Inertial Navigation System

ER-70X I NS The ER-70X miniaturized fiber inertia assembly is a miniature fiber optic gyro strapdown inertial measurement set developed for the prototype of the Northrop Grumman (formerly Litton) LN200. It consists of an all-solid triaxial fiber optic gyroscope and triaxial quartz flexibility.......
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The ER-70X miniaturized fiber inertia assembly is a miniature fiber optic gyro strapdown inertial measurement set developed for the prototype of the Northrop Grumman (formerly Litton) LN200. It consists of an all-solid triaxial fiber optic gyroscope and triaxial quartz flexibility. Accelerometer, body structure, data interface board and other components. It has fast start-up and fast response; full attitude measurement; low power consumption and miniaturization; fully sealed, non-active part and gas protection compartment, and reliable frame structure, thus featuring high reliability and long life. The sensor has low noise and small offset, and can be directly integrated with navigation computer, satellite receiver and related software to form GNSS/INS integrated navigation. It can be directly applied to inertial navigation of surface-to-air missiles, air-to-air missiles and navigation missiles. It can be widely used. In space stabilization systems, mapping systems, attitude reference systems, motion compensation systems, imaging stabilization systems, flight control systems and air combat maneuvering instruments / navigation test equipment.

The ER-70X miniaturized fiber inertia combination is used to detect the angular velocity and linear acceleration of the carrier. The navigation software provides information for the attitude and navigation control of the carrier. The software can be operated in two ways: AHTS (Attitude and Heading Reference System) Output heading angle, pitch angle, roll angle) or Inertial Measurement Unit (IMU). Different types of products such as IMU, AHRS and integrated navigation system can be realized according to different users and application requirements to meet various special targets. Application requirements for aircraft, tactical drones, tactical missiles, and guided torpedoes are easy to retrofit. At present, this model has been successfully applied in a certain type of missile. The main functions are as follows:

uMeasuring three angular rates of the carrier and three accelerations of centroid motion;

uRelevant compensation for three angular rates and three linear accelerations, including temperature     compensation,installation misalignment angle compensation, nonlinea compensation, zero compensation,etc.,the       performance after compensation should meet all technical requirements, and output in the form of data;

uExternal serial communication function;

uSoftware binding, upgrade and test, calibration through serial port;

uSelf-test function.

 INS

Main Specifications

IMU indicator


Main precision index



Angular velocity channel



Zero stability


0.2°/h - 1.0 °/h (1σ)


Scale factor nonlinearity


≤ 300 ppm (1σ)


Maximum measured angular velocity


≥ 500°/s


Random walk


≤ 0.05 °/√h


Acceleration channel



Zero  stability



≤ 2×10-4  g (1σ)


Scale factor error



≤ 300 ppm (1σ)


Line acceleration resolution



≤ 1×10-4  g (1σ)


Line acceleration measurement range



± 30 g

 

If interested, pls contact us info@ericcointernational.com


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    1. Linkedin :www.linkedin.com/in/amy-guo-8877a354/

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