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Aircraft Laser Inertial Navigation Airborne Optical Gyro–Strategic/Tactical/Commercial Grade INS

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Aircraft Laser Inertial Navigation Airborne Optical Gyro–Strategic/Tactical/Commercial Grade INS

Brand Name : Star & Inertia Technology

Model Number : F3AAA

Place of Origin : China

MOQ : 1 set

Supply Ability : 500 sets per year

Delivery Time : 7work days

Certification : GJN485963217

Payment Terms : T/T

Packaging Details : 30cm*30cm*28cm

Price : 200000RMB+

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℃~70℃

Shock : 15g,Half-sine wave 11ms

Input Voltage : DC24V(±25%)

cooling : Conduction to mounting plate

Vibration : 20~2000Hz,6.06g

MTBF : >25000 hours

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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


Product Tags:

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