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Imu Inertial Guidance System , Ins Inertial Navigation System

Imu Inertial Guidance System , Ins Inertial Navigation System
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Product: INS With GPS
Heading Accuracy: 0.1°
Attitude Accuracy: 0.02°(RMS)
Gyroscope Range: ±400°/s
Zero Bias Stability: ≤100µg
Accelerometer Range: ±20g
Operating Temperature: -40℃~+60℃
Vibration: 5 ~ 2000Hz, 6.06 G (with Shock Absorber)
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Imu Inertial Guidance System


Ins Inertial Guidance System


Inertial Navigation System with GPS

Basic Infomation
Place of Origin: CHINA
Brand Name: avic
Certification: CE ROHS
Model Number: GI300F-A
Payment & Shipping Terms
Packaging Details: sponge+carton
Delivery Time: 10 days
Payment Terms: T/T
Supply Ability: 500/month
Product Description

Inertial Guidance System Inertial Guidance System Imu Inertial Navigation System Ins Inertial Navigation System


The fiber-optic integrated navigation system GI300F-INS is based on closed-loop fiber-optic gyroscope and accelerometer with high cost performance, and is realized through multi-sensor fusion and navigation calculation algorithm, which meets the requirements of precise measurement of attitude, heading and position information in the application fields of medium and high precision mobile measurement systems, medium and large UAVs, etc.


Project Test conditions Indicators
Positioning accuracy External GNSS Valid, Single Point Better than external satellite positioning accuracy
External GNSS Valid, RTK Better than external satellite positioning accuracy
Pure inertial horizontal position holding①




Airspeed combination horizontal position hold② 0.8nm/30min (CEP)
Heading accuracy Single antenna (RMS) 0.1°③
Dual Antenna (RMS) 0.2 °/L (L = baseline length) (RMS)
Course Keeping (RMS) 0.2°/30min(RMS),0.5°/h
Self-north seeking accuracy (RMS)

0.2 ° SecL, dual position alignment for 15 min

1.0 ° SecL, single position alignment 5-10 min

Attitude accuracy GNSS is valid 0.02°(RMS)
Attitude hold (GNSS failure) 0.2°/30min(RMS),0.5°/h(RMS)
Speed accuracy GNSS valid, single point L1/L2 0.1m/s(RMS)
Gyroscope Measuring range ±400°/s
Zero bias stability ≤0.3°/h
Accelerometer Measuring range ±20g
Zero bias stability ≤100µg
Physical dimensions and electrical characteristics Voltage 9-36V DC
Power consumption ≤ 12W (steady state)
Interface 2-channel RS232, 1-channel RS422, 1-channel PPS (LVTTL/422 level)
Size 92.0 mm × 92.0 mm × 81.0mm (L, W, H)
Weight ≤1.2kg
Environmental characteristics Operating temperature -40℃~+60℃
Storage temperature -45℃~+70℃
Vibration 5 ~ 2000Hz, 6.06 G (with shock absorber)
Impact 30g, 11 ms (with shock)
Life span > 15 years
Continuous working time >24h
Height limit ≤5000m
speed limit ≤500m/s


  • The alignment is valid;
  • For airborne use, there is a turning maneuver before the airspeed combination, and the test takes the flight speed of 150km/H as an example;
  • On-board conditions, need to be mobile;

Main functions​

The system has inertial/satellite integrated navigation mode and pure inertial mode.

In the inertial/satellite integrated navigation mode, the satellite positioning information received by the external GNSS receiver can be used for integrated navigation, and the pitch, roll, course, position, speed, time and other information of the carrier can be output; After the signal is lost, the position, velocity and attitude calculated by inertia are output, in which the pitch and roll are required to be accurate, the course keeping function is available in a short time, and the meter-level positioning accuracy is available in a short time.

After the pure inertial mode (that is, GPS fusion has never been performed after power-on, and if it loses lock again after fusion, it belongs to the integrated navigation mode) is started, it has the function of accurate attitude measurement, can output the pitch and roll heading, and the pure inertial mode can find the north statically.



The integrated design scheme is adopted for the inertial measurement unit, and the system outline is shown in the figure below.

The overall dimension of the system is 92.0 mm × 92.0 mm × 81.0 mm (length × width × height).

Imu Inertial Guidance System , Ins Inertial Navigation System 0d the other end is divided into a power supply red and black clip and three serial ports, which are COM1 ~ COM3, where COM1 is RS422, COM2 and COM3 are RS232. COM 1 can be used to send the working mode command;




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