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Aerospace FOG INS(Merak-A05)
The airborne optical gyro inertial navigation system uses optical gyroscopes and quartz accelerometers as core sensors, employing strapdown or modulation technology systems. It operates advanced navigation software at high speeds internally, calculating and outputting navigation information in real-time. This series of products can integrate navigation information from satellites, astronomy, altimeters, radio, vision, etc., according to user needs, supporting pure inertial and multi-source information fusion working modes, providing users with comprehensive navigation information for the carrier.
Applications: UAVs and special aircraft.
Capabilities:
1) Ground/air alignment;
2) Alignment mode switching;
3) Sensor fusion;
4) Fault detection.
Series | Aerospace Inertial Navigation System(INS-A) | ||
Type | Merak-A05 | ||
Accelerometer | Months Bias Repeatability(1σ) | ≤30μg | |
Months Scale Factor Accuracy(1σ) | ≤30ppm | ||
Gyro | Bias Repeatability(1σ) | ≤0.01°/hr | |
Scale Factor Accuracy(1σ) | ≤30ppm | ||
Random walk(1σ) | ≤0.005°/√hr | ||
Features | Position Accuracy | Pure inertia | ≤2nm/1h,CEP |
INS/GNSS combination | better than GNSS | ||
Speed Accuracy | Pure inertia | ≤1.5m/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 | ≤0.1°sec(L),RMS |
INS/GNSS combination | ≤0.05°,RMS | ||
Pitch & Roll Accuracy | Pure inertia | ≤0.03°,RMS | |
INS/GNSS combination | ≤0.02°,RMS | ||
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 |