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Aerospace RLG INS(Dubhe-A1)
The airborne optical gyro INS utilizes FOG/RLG gyroscopes and quartz accelerometers as core sensors, adopting strapdown or modulated architecture. Its high-speed navigation computer runs advanced algorithms to provide real-time navigation solutions. The system supports multiple operational modes including pure inertial and multi-source fusion (GNSS, celestial, altimeter, radio, and vision), delivering complete navigation parameters.
Applications include fixed-wing UAVs, rotary-wing UAVs, and special aircraft.
Key features:
1) Ground sway base/airborne alignment capability;
2) Switchable alignment modes (self/transfer/moving base);
3) Multi-source navigation fusion;
4) Fault detection and alarm functions.
Series | Aerospace Inertial Navigation System(INS-A) | ||
Type | Dubhe-A1 | ||
Accelerometer | Months Bias Repeatability(1σ) | ≤30μg | |
Months Scale Factor Accuracy(1σ) | ≤30ppm | ||
Gyro | Bias Repeatability(1σ) | ≤0.008°/hr | |
Scale Factor Accuracy(1σ) | ≤10ppm | ||
Random walk(1σ) | ≤0.003°/√hr | ||
Features | Position Accuracy | Pure inertia | ≤1.0nm/1h,CEP |
INS/GNSS combination | better than GNSS | ||
Speed Accuracy | Pure inertia | ≤1.2m/s,RMS | |
INS/GNSS combination | ≤0.2m/s,RMS | ||
Angular Rate | ≥±400°/sec | ||
Angular Acceleration | 100000°/sec2 | ||
Acceleration | >25g | ||
Angular Attitude | Any Orientation | ||
Input/output | 3 RS422 full-duplex serial ports, 1 100M Ethernet port | ||
Alignment time | <5min | ||
AHRS Applications Performance | Heading Accuracy | Pure inertia | ≤0.05°sec(L),RMS |
INS/GNSS combination | ≤0.03°,RMS | ||
Pitch & Roll Accuracy | Pure inertia | ≤0.03°,RMS | |
INS/GNSS combination | ≤0.015°,RMS | ||
Characteristics | Power consumption | <20W | |
Dimensions | 195×160×108 | ||
Weight | <3.9kg | ||
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 |