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