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Airborne Optical Gyro Inertial Navigation System

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Miss. Yao

yao@inertial-systems.com

86--18771146215-13212796772

13212796772

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Airborne Optical Gyro Inertial Navigation System

MOQ:	1 set
Price:	100
Delivery Period:	30 work days
Payment Method:	T/T
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）:

≤0.01°/hr

Gyro/Scale Factor Accuracy（1σ）:

≤20ppm

Gyro/Random Walk（1σ）:

≤0.005°/√hr

Position Accuracy/Pure Inertia:

≤2nm/1h

Position Accuracy/Inertial Navigation Satellite Combination:

Better Than Satellite Accuracy

Speed accuracy/Pure Inertia:

≤1.5m/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:

≤0.2°sec(L)

Heading Accuracy/Satellite Navigation Combination:

≤0.1°sec(L)

Pitch & Roll Accuracy/Pure Inertia:

≤0.03°

Pitch & Roll Accuracy/Satellite Navigation Combination:

≤0.02°

Power Consumption:

＜15W

Dimensions:

130×130×110mm

Weight:

＜2.2kg

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

Product Description

The airborne optical gyro inertial navigation system is built around optical gyroscopes and quartz accelerometers as its core sensing elements. Based on strapdown inertial navigation architecture and optional modulation techniques, the system runs high-speed navigation algorithms internally to compute and output navigation data in real time.

Product Features

Optical Gyroscope and Quartz Accelerometer Architecture
Provides stable and continuous inertial measurements suitable for airborne platforms.
Strapdown Inertial Navigation Design
Compact structure with real-time attitude, velocity, and position computation.
High-Speed Navigation Processing
Embedded navigation software ensures timely calculation and output of navigation information.
Multi-Source Data Integration Capability
Supports fusion of satellite navigation, astronomical reference, altimeter, radio navigation, and vision-based information according to mission requirements.
Flexible Operating Modes
Compatible with pure inertial navigation as well as multi-source integrated navigation modes.

Key Advantages

High Autonomy
Maintains continuous navigation capability even in environments with limited or denied external signals.
Strong Adaptability
Configurable information fusion architecture allows adaptation to different airborne missions.
Reliable Real-Time Output
Provides consistent navigation parameters required for flight control and guidance systems.
Scalable System Integration
Designed for seamless integration with airborne avionics and mission systems.

Applications

Aircraft inertial navigation systems
Navigation and guidance for fixed-wing aircraft, helicopters, and unmanned aerial vehicles (UAVs)
Integrated navigation systems combining inertial and satellite data
Airborne platforms requiring continuous attitude, heading, velocity, and position information
Aviation test, research, and specialized mission platforms

Series			Aerospace Inertial Navigation System(INS-A)
Accelerometer	Months Bias Repeatability(1σ)		≤20μg
	Months Scale Factor Accuracy(1σ)		≤20ppm
Gyro	Bias Repeatability(1σ)		≤0.01°/hr
	Scale Factor Accuracy(1σ)		≤20ppm
	Random walk(1σ)		≤0.005°/√hr
Features	Position Accuracy	Pure inertia	≤2nm/1h
		Inertial navigation satellite combination	better than satellite accuracy
	Speed Accuracy	Pure inertia	≤1.5m/s
		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
Alignment time	Time		＜5min
AHRS Applications Performance	Heading Accuracy	Pure inertia	≤0.2°sec(L)
		Satellite navigation combination	≤0.1°sec(L)
	Pitch & Roll Accuracy	Pure inertia	≤0.03°
		Satellite navigation combination	≤0.02°
Characteristics	Power consumption		＜15W
	Dimensions		130×130×110
	Weight		＜2.2kg
	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

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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

Airborne Optical Gyro Inertial Navigation System

MOQ:	1 set
Price:	100
Delivery Period:	30 work days
Payment Method:	T/T
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）:

≤0.01°/hr

Gyro/Scale Factor Accuracy（1σ）:

≤20ppm

Gyro/Random Walk（1σ）:

≤0.005°/√hr

Position Accuracy/Pure Inertia:

≤2nm/1h

Position Accuracy/Inertial Navigation Satellite Combination:

Better Than Satellite Accuracy

Speed accuracy/Pure Inertia:

≤1.5m/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:

≤0.2°sec(L)

Heading Accuracy/Satellite Navigation Combination:

≤0.1°sec(L)

Pitch & Roll Accuracy/Pure Inertia:

≤0.03°

Pitch & Roll Accuracy/Satellite Navigation Combination:

≤0.02°

Power Consumption:

＜15W

Dimensions:

130×130×110mm

Weight:

＜2.2kg

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

Price:

100

Delivery Time:

30 work days

Payment Terms:

T/T

Supply Ability:

500 sets per year

Product Description

Product Description

Product Features

Optical Gyroscope and Quartz Accelerometer Architecture
Provides stable and continuous inertial measurements suitable for airborne platforms.
Strapdown Inertial Navigation Design
Compact structure with real-time attitude, velocity, and position computation.
High-Speed Navigation Processing
Embedded navigation software ensures timely calculation and output of navigation information.
Multi-Source Data Integration Capability
Supports fusion of satellite navigation, astronomical reference, altimeter, radio navigation, and vision-based information according to mission requirements.
Flexible Operating Modes
Compatible with pure inertial navigation as well as multi-source integrated navigation modes.

Key Advantages

High Autonomy
Maintains continuous navigation capability even in environments with limited or denied external signals.
Strong Adaptability
Configurable information fusion architecture allows adaptation to different airborne missions.
Reliable Real-Time Output
Provides consistent navigation parameters required for flight control and guidance systems.
Scalable System Integration
Designed for seamless integration with airborne avionics and mission systems.

Applications

Aircraft inertial navigation systems
Navigation and guidance for fixed-wing aircraft, helicopters, and unmanned aerial vehicles (UAVs)
Integrated navigation systems combining inertial and satellite data
Airborne platforms requiring continuous attitude, heading, velocity, and position information
Aviation test, research, and specialized mission platforms

Series			Aerospace Inertial Navigation System(INS-A)
Accelerometer	Months Bias Repeatability(1σ)		≤20μg
	Months Scale Factor Accuracy(1σ)		≤20ppm
Gyro	Bias Repeatability(1σ)		≤0.01°/hr
	Scale Factor Accuracy(1σ)		≤20ppm
	Random walk(1σ)		≤0.005°/√hr
Features	Position Accuracy	Pure inertia	≤2nm/1h
		Inertial navigation satellite combination	better than satellite accuracy
	Speed Accuracy	Pure inertia	≤1.5m/s
		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
Alignment time	Time		＜5min
AHRS Applications Performance	Heading Accuracy	Pure inertia	≤0.2°sec(L)
		Satellite navigation combination	≤0.1°sec(L)
	Pitch & Roll Accuracy	Pure inertia	≤0.03°
		Satellite navigation combination	≤0.02°
Characteristics	Power consumption		＜15W
	Dimensions		130×130×110
	Weight		＜2.2kg
	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

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