Description:
In order to meet the needs of unmanned aerial vehicles and military applications, our engineers design IMU-003 Inertial Navigation System to provide a full range of autopilot and mission management functions, including automatic landing and navigation routes. The autopilot uses highly automated control synthesis techniques that are designed to ensure robustness and robustness throughout the flight envelope, primarily to meet the most stringent environmental requirements, to ensure long trouble-free use and high performancein the entire temperature and altitude within the system. Its small size allows it to be installed on tactical UAVs to achieve the desired control system solution.
Advantages:
1. Own Kalman filter algorithm provides a full INS attitude solution
2. Providing accurate rolling, pitching data, and sustained rotationin the dynamic environment
3. Supporingt all atmospheric data measurements, including AOA and side-slip
4. Supporting autonomous vehicle control, integrated sensor components
Specifications：
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SPECIFICATIONS |
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INS/GPS performance |
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Update rate |
50 Hz |
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Start-up time |
10 sec (initial attitude); > 1 min (full alignment) |
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Heading range |
+/- 180° |
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Attitude range pitch |
+/- 90° |
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Attitude range roll |
+/- 180° |
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Altitude range |
-2,000 ft to 50,000 ft> |
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Baroinertial altitude accuracy |
45 ft at S.L., 40,000 ft altitude> |
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GPS range |
Worldwide |
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Lat/long position accuracy |
GPS C/A Code; differential ready, WAAS-enabled> |
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Max airspeed |
165 knots standard, > up to 650 knots optional |
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IMU performance |
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Maximum angular rates |
+/- 200°/s |
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Maximum g range |
+/- 8 g |
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Environmental Specifications |
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Operating Temperature |
-40 to 70 ℃ |
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Operating vibration |
-Provisioned for passive isolation, MIL-STD-810 |
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Serial input/output |
RS-422 |
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Humidity |
95%, non-condensing sealed enclosure |
