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