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Aircraft Fiber-optic Inertial Navigation System Airborne Optical Gyro Inertial Navigation System

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Miss. Yao

yao@inertial-systems.com

86--18771146215-13212796772

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Aircraft Fiber-optic Inertial Navigation System Airborne Optical Gyro 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）:

≤500μg

Accelerometer/Months Scale Factor Accuracy（1σ）:

≤500ppm

Gyro/Bias Repeatability（1σ）:

≤0.1°/hr

Gyro/Scale Factor Accuracy（1σ）:

≤300ppm

Gyro/Random Walk（1σ）:

≤0.03°/√hr

Position Accuracy/Pure Inertia:

≤1nm/10min

Position Accuracy/Inertial Navigation Satellite Combination:

Better Than Satellite Accuracy

Speed accuracy/Pure Inertia:

Speed accuracy/Inertial Navigation Satellite Combination:

≤0.2m/s

Angular Rate:

≥±400°/sec

Angular Acceleration:

100000°/sec2

Acceleration:

＞40g

Angular Attitude:

Any Orientation

Alignment Time:

≤5min

Input/output:

2 RS422 Serial Ports

Heading Accuracy/Pure Inertia:

Heading Accuracy/Satellite Navigation Combination:

≤1°sec(L)

Pitch & Roll Accuracy/Pure Inertia:

Pitch & Roll Accuracy/Satellite Navigation Combination:

≤0.2°

Power Consumption:

＜10W

Dimensions:

70×70×53mm

Weight:

＜500g

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

Highlight:

fiber-optic inertial navigation system

airborne optical gyro system

aircraft inertial navigation system with gyro

Product Description

The airborne optical gyro inertial navigation system is designed with optical gyroscopes and quartz accelerometers as its primary sensing components. Using a strapdown inertial navigation architecture, with optional modulation-based techniques, the system performs high-speed internal navigation computation and delivers navigation data continuously in real time.

System Characteristics

Optical Gyro and Quartz Accelerometer Configuration
Provides stable inertial sensing suitable for airborne operating conditions.
Strapdown Inertial Navigation Structure
Compact and integrated design for real-time attitude, velocity, and position calculation.
High-Speed Navigation Processing
Embedded navigation algorithms ensure timely computation and output of navigation parameters.
Multi-Source Navigation Integration
Capable of incorporating external navigation information such as satellite navigation, astronomical reference, altimeters, radio navigation aids, and vision-based data, based on user configuration.
Multiple Operating Modes
Supports pure inertial navigation as well as multi-source integrated navigation and information fusion modes.

Key Advantages

Continuous Navigation Capability
Maintains stable navigation output independent of external signal availability.
Flexible Configuration
Information sources and fusion strategies can be adapted to different mission requirements.
Reliable Real-Time Output
Provides consistent navigation data required by airborne guidance and control systems.
Strong System Compatibility
Designed for integration with aircraft avionics and mission management systems.

Applications

Aircraft inertial navigation systems
Navigation and guidance for fixed-wing aircraft, helicopters, and UAVs
Integrated navigation systems combining inertial and satellite data
Airborne platforms requiring attitude, heading, velocity, and position information
Aviation research, testing, and specialized airborne missions

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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

Doppler Velocity Log

Aircraft Fiber-optic Inertial Navigation System Airborne Optical Gyro 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）:

≤500μg

Accelerometer/Months Scale Factor Accuracy（1σ）:

≤500ppm

Gyro/Bias Repeatability（1σ）:

≤0.1°/hr

Gyro/Scale Factor Accuracy（1σ）:

≤300ppm

Gyro/Random Walk（1σ）:

≤0.03°/√hr

Position Accuracy/Pure Inertia:

≤1nm/10min

Position Accuracy/Inertial Navigation Satellite Combination:

Better Than Satellite Accuracy

Speed accuracy/Pure Inertia:

Speed accuracy/Inertial Navigation Satellite Combination:

≤0.2m/s

Angular Rate:

≥±400°/sec

Angular Acceleration:

100000°/sec2

Acceleration:

＞40g

Angular Attitude:

Any Orientation

Alignment Time:

≤5min

Input/output:

2 RS422 Serial Ports

Heading Accuracy/Pure Inertia:

Heading Accuracy/Satellite Navigation Combination:

≤1°sec(L)

Pitch & Roll Accuracy/Pure Inertia:

Pitch & Roll Accuracy/Satellite Navigation Combination:

≤0.2°

Power Consumption:

＜10W

Dimensions:

70×70×53mm

Weight:

＜500g

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

Highlight

fiber-optic inertial navigation system

airborne optical gyro system

aircraft inertial navigation system with gyro

Product Description

System Characteristics

Optical Gyro and Quartz Accelerometer Configuration
Provides stable inertial sensing suitable for airborne operating conditions.
Strapdown Inertial Navigation Structure
Compact and integrated design for real-time attitude, velocity, and position calculation.
High-Speed Navigation Processing
Embedded navigation algorithms ensure timely computation and output of navigation parameters.
Multi-Source Navigation Integration
Capable of incorporating external navigation information such as satellite navigation, astronomical reference, altimeters, radio navigation aids, and vision-based data, based on user configuration.
Multiple Operating Modes
Supports pure inertial navigation as well as multi-source integrated navigation and information fusion modes.

Key Advantages

Continuous Navigation Capability
Maintains stable navigation output independent of external signal availability.
Flexible Configuration
Information sources and fusion strategies can be adapted to different mission requirements.
Reliable Real-Time Output
Provides consistent navigation data required by airborne guidance and control systems.
Strong System Compatibility
Designed for integration with aircraft avionics and mission management systems.

Applications

Aircraft inertial navigation systems
Navigation and guidance for fixed-wing aircraft, helicopters, and UAVs
Integrated navigation systems combining inertial and satellite data
Airborne platforms requiring attitude, heading, velocity, and position information
Aviation research, testing, and specialized airborne missions

Tags: