Fiber optic integrated navigation system FS300-70 is based on cost-effective closed-loop fiber optic gyroscope, accelerometer and high-end GNSS receiving board, and is realized by multi-sensor fusion and navigation solution algorithm. It can meet the requirements for accurate measurement of attitude, heading and position information in medium and high precision mobile measurement systems, large unmanned aerial vehicles and other applications.
| Parameter | Technical index | ||
| Position accuracy | Single point (RMS) | 1.2m | |
| RTK（RMS） | 2cm+1ppm | ||
| Post-processing (RMS) | 1cm+1ppm | ||
| Loss of lock accuracy (CEP) | 10m, lose lock 30s (Alignment efficiency) | ||
| Course (RMS) | Single antenna | 0.1° (Vehicle conditions, need to maneuver) | |
| Double antenna | 0.1° (baseline ≥2m) | ||
| post-processing | 0.02° | ||
| Loss of lock hold accuracy | 0.5°, lose lock for 30 minutes | ||
| Self-seeking north accuracy | At 1°SecL, align for 15min (Double position alignment, course difference between the two positions is greater than 90 degrees) | ||
| Attitude (RMS) | Single antenna | 0.02° | |
| Double antenna | 0.02° | ||
| post-processing | 0.015° | ||
| Loss of lock hold accuracy | 0.5°, lose lock for 30 minutes | ||
| Horizontal velocity accuracy (RMS) | 0.05m/s | ||
| Timing accuracy | 20ns | ||
| Data output frequency | 200Hz (Single output 200Hz) | ||
| Gyroscope | Range | 400°/s | |
| Zero bias stability | 0.3°/h (10s average) | ||
| Scale factor
Nonlinearity |
100ppm | ||
| Angular random walk | 0.05°/√hr | ||
| Accelerometer | Range | 16g | |
| Zero bias stability | 50ug (10s average) | ||
| Scale factor
Nonlinearity |
100ppm | ||
| Velocity random walk | 0.01m/s/√hr | ||
| Physical dimensions and electrical characteristics | Overall dimension | 138.5 mm×136.5 mm×102mm | |
| Weight | <2.7kg (excluding cable) | ||
| Input voltage | 12～36VDC | ||
| Power consumption | <24W (steady state) | ||
| Storage | Rreserve | ||
| Environmental index | Operating temperature | -40℃~+60℃ | |
| Storage temperature | -45℃～+70℃ | ||
| Random vibration | 6.06g，20Hz~2000Hz | ||
| MTBF | 30000h | ||
| Interface characteristic | PPS, EVENT, RS232, RS422, CAN (Optional) | ||
| Network port (Reserved) | |||
| Antenna interface | |||
| Wheel speed sensor interface | |||
The inertial measurement unit and satellite receiver adopt an integrated design scheme, both of which are integrated in the inertial navigation system. The appearance of the system is shown in the figure below.
System dimensions: 138.5mm × 136.5mm ×102mm.
The system has a combined inertial/satellite navigation mode and a pure inertial mode.
In the inertial/satellite integrated navigation mode, the satellite positioning information received by the GNSS receiver can be used for integrated navigation, and the information of pitch, roll, heading, position, speed and time of the carrier can be output. After the signal is lost, the position velocity attitude calculated by inertia is output, in which the pitch roll is required to keep accurate, with a certain course holding function in a short time, and with meter-level positioning accuracy in a short time.
Pure inertial mode (that is, GPS fusion has never been carried out after power-on, and if it loses lock again after fusion, it belongs to integrated navigation mode) has accurate attitude measurement function, can output pitch roll heading, pure inertia can static north searching.
The inertial measurement unit and satellite receiver adopt an integrated design scheme, both of which are integrated in the inertial navigation system. The appearance of the system is shown in the figure below.
System dimensions: 138.5mm × 136.5mm ×102mm.
The system has a combined inertial/satellite navigation mode and a pure inertial mode.
In the inertial/satellite integrated navigation mode, the satellite positioning information received by the GNSS receiver can be used for integrated navigation, and the information of pitch, roll, heading, position, speed and time of the carrier can be output. After the signal is lost, the position velocity attitude calculated by inertia is output, in which the pitch roll is required to keep accurate, with a certain course holding function in a short time, and with meter-level positioning accuracy in a short time.
Pure inertial mode (that is, GPS fusion has never been carried out after power-on, and if it loses lock again after fusion, it belongs to integrated navigation mode) has accurate attitude measurement function, can output pitch roll heading, pure inertia can static north searching.
English
Afrikaans
Arabic
Chinese (Simplified)
Dutch
French
German
Italian
Japanese
Persian
Portuguese
Russian
Spanish
Turkish
