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Aircraft Laser Inertial Navigation Airborne Optical Gyro–Based Inertial Navigation System

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Ring Laser Gyroscope

Miss. Yao

yao@inertial-systems.com

86--18771146215-13212796772

13212796772

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Aircraft Laser Inertial Navigation Airborne Optical Gyro–Based Inertial Navigation System

MOQ:	1 set
Delivery Period:	30 work days
Supply Capacity:	500 sets per year

Details Information

Product Description

Detail Information

Place of Origin

China

Brand Name

Star & Inertia Technology

Accelerometer/Months Bias Repeatability（1σ）:

≤20μg

Accelerometer/Months Scale Factor Accuracy（1σ）:

≤20ppm

Gyro/Bias Repeatability（1σ）:

≤0.008°/hr

Gyro/Scale Factor Accuracy（1σ）:

≤20ppm

Gyro/Random Walk（1σ）:

≤0.003°/√hr

Position Accuracy/Pure Inertia:

≤0.8nm/1h

Position Accuracy/Inertial Navigation Satellite Combination:

Better Than Satellite Accuracy

Speed accuracy/Pure Inertia:

≤1.0m/s

Speed accuracy/Inertial Navigation Satellite Combination:

≤0.2m/s

Angular Rate:

≥±400°/sec

Angular Acceleration:

100000°/sec2

Acceleration:

＞25g

Angular Attitude:

Any Orientation

Alignment Time:

≤8min

Input/output:

3 RS422 Full-duplex Serial Ports, 1 100M Ethernet Port

Heading Accuracy/Pure Inertia:

≤0.1°sec(L)

Heading Accuracy/Satellite Navigation Combination:

≤0.05°sec(L)

Pitch & Roll Accuracy/Pure Inertia:

≤0.03°

Pitch & Roll Accuracy/Satellite Navigation Combination:

≤0.015°

Power Consumption:

＜20W

Dimensions:

195×160×108mm

Weight:

＜3.9kg

Temperature:

-40℃~60℃

Shock:

15g，Half-sine Wave 11ms

Input Voltage:

DC24V(±25%)

Cooling:

Conduction To Mounting Plate

Vibration:

20~2000Hz,6.06g

MTBF:

＞20000 Hours

Product Description

This airborne inertial navigation system is developed using optical gyroscopes and quartz accelerometers as the fundamental sensing elements. The system adopts a strapdown inertial configuration, with optional modulation-based processing, enabling continuous internal navigation computation and real-time output of navigation data.

Technical Features

Optical Gyroscope and Quartz Accelerometer Sensors
Designed to meet the stability and reliability requirements of airborne platforms.
Strapdown Inertial Navigation Architecture
Integrated structure suitable for compact airborne installation and high-rate navigation calculation.
High-Speed Navigation Algorithms
Embedded software processes inertial data efficiently to generate real-time navigation outputs.
Multi-Source Navigation Data Fusion
Supports optional integration of satellite navigation, astronomical reference, altitude data, radio navigation aids, and vision-based information based on operational needs.
Flexible Operation Modes
Capable of operating in standalone inertial navigation mode or multi-source integrated navigation mode.

System Advantages

High Navigation Autonomy
Provides continuous navigation capability independent of external signal availability.
Adaptable Integration Capability
Allows configuration according to mission requirements and sensor availability.
Stable and Real-Time Output
Supplies essential navigation parameters for airborne guidance and control systems.
Compatibility with Avionics Systems
Designed for integration into a wide range of airborne platforms and onboard systems.

Typical Applications

Aircraft inertial navigation systems
Navigation and guidance for fixed-wing aircraft, rotary-wing aircraft, and unmanned aerial vehicles (UAVs)
Integrated navigation solutions combining inertial and external reference data
Airborne platforms requiring continuous attitude, heading, velocity, and position information
Flight testing, aviation research, and specialized airborne missions

Tags:

fog inertial navigation system,

inertial navigation system drone,

integrated navigation system

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PRODUCTS DETAILS

Products

Laser Inertial Navigation System

Fiber Optic Inertial Navigation System

Aircraft Inertial Navigation System

Marine Inertial Navigation System

Automotive Inertial Navigation System

AHRS System

IMU Inertial Measurement Unit

Fiber Optic Gyroscope

Ring Laser Gyroscope

Aircraft Laser Inertial Navigation Airborne Optical Gyro–Based Inertial Navigation System

MOQ:	1 set
Delivery Period:	30 work days
Supply Capacity:	500 sets per year

Detail Information

Product Description

Detail Information

Place of Origin

China

Brand Name

Star & Inertia Technology

Accelerometer/Months Bias Repeatability（1σ）:

≤20μg

Accelerometer/Months Scale Factor Accuracy（1σ）:

≤20ppm

Gyro/Bias Repeatability（1σ）:

≤0.008°/hr

Gyro/Scale Factor Accuracy（1σ）:

≤20ppm

Gyro/Random Walk（1σ）:

≤0.003°/√hr

Position Accuracy/Pure Inertia:

≤0.8nm/1h

Position Accuracy/Inertial Navigation Satellite Combination:

Better Than Satellite Accuracy

Speed accuracy/Pure Inertia:

≤1.0m/s

Speed accuracy/Inertial Navigation Satellite Combination:

≤0.2m/s

Angular Rate:

≥±400°/sec

Angular Acceleration:

100000°/sec2

Acceleration:

＞25g

Angular Attitude:

Any Orientation

Alignment Time:

≤8min

Input/output:

3 RS422 Full-duplex Serial Ports, 1 100M Ethernet Port

Heading Accuracy/Pure Inertia:

≤0.1°sec(L)

Heading Accuracy/Satellite Navigation Combination:

≤0.05°sec(L)

Pitch & Roll Accuracy/Pure Inertia:

≤0.03°

Pitch & Roll Accuracy/Satellite Navigation Combination:

≤0.015°

Power Consumption:

＜20W

Dimensions:

195×160×108mm

Weight:

＜3.9kg

Temperature:

-40℃~60℃

Shock:

15g，Half-sine Wave 11ms

Input Voltage:

DC24V(±25%)

Cooling:

Conduction To Mounting Plate

Vibration:

20~2000Hz,6.06g

MTBF:

＞20000 Hours

Minimum Order Quantity:

1 set

Delivery Time:

30 work days

Supply Ability:

500 sets per year

Product Description

Technical Features

Optical Gyroscope and Quartz Accelerometer Sensors
Designed to meet the stability and reliability requirements of airborne platforms.
Strapdown Inertial Navigation Architecture
Integrated structure suitable for compact airborne installation and high-rate navigation calculation.
High-Speed Navigation Algorithms
Embedded software processes inertial data efficiently to generate real-time navigation outputs.
Multi-Source Navigation Data Fusion
Supports optional integration of satellite navigation, astronomical reference, altitude data, radio navigation aids, and vision-based information based on operational needs.
Flexible Operation Modes
Capable of operating in standalone inertial navigation mode or multi-source integrated navigation mode.

System Advantages

High Navigation Autonomy
Provides continuous navigation capability independent of external signal availability.
Adaptable Integration Capability
Allows configuration according to mission requirements and sensor availability.
Stable and Real-Time Output
Supplies essential navigation parameters for airborne guidance and control systems.
Compatibility with Avionics Systems
Designed for integration into a wide range of airborne platforms and onboard systems.

Typical Applications

Aircraft inertial navigation systems
Navigation and guidance for fixed-wing aircraft, rotary-wing aircraft, and unmanned aerial vehicles (UAVs)
Integrated navigation solutions combining inertial and external reference data
Airborne platforms requiring continuous attitude, heading, velocity, and position information
Flight testing, aviation research, and specialized airborne missions

Tags: