Introduction
LKF-F3X50 inertial measurement unit is an inertial product developed for navigation guidance, attitude measurement and control systems of small missiles and guided bombs. The angular velocity and linear acceleration of the carrier motion provide information for the attitude and navigation control of the carrier, and the measurement results are output through the RS422 serial port.
By reducing the outer diameter of fiber to 135μm,Thin PM fiber solution decreases extremely the size of fiber coils and delivers outstanding precision performance in fiber coils, which is applied for miniaturization of FOGs. And, the coils are wound precisely through quadrupole symmetry method.
Earthquakes are a devastating natural disaster, so early warning and accurate seismic measurements are crucial. The high accuracy and sensitivity of the LKF-F3X50 fiber optic gyroscope make it an indispensable part of the earthquake monitoring network.
Table 1 Performance parameters of LKF-F3X50 Three-axis FOG IMU
| No. | Item | Data | Unit | Requirements |
| 1 | Gyroscope | Bias Stability(1σ,10s) | °/h | ≤0.15 |
| 2 | Bias Repeatability(1σ,10s) | °/h | ≤0.15 |
| 3 | Bias Stability at Changing Temperature(1σ,10s) | °/h | ≤0.5 |
| 4 | Random Walk Coefficient | °/√h | ≤0.02 |
| 5 | Scale Factor Non-linearity | ppm | ≤50 |
| 6 | Scale Factor Asymmetry | ppm | ≤30 |
| 7 | Scale Factor Repeatability | ppm | ≤100 |
| 8 | Scale Factor Changing at Full Temperature | ppm | ≤500 |
| 9 | Range | °/s | -500 ~ +500 |
| 10 | Accelerometer | Bias Stability(1σ,10s) | μg | ≤40 |
| 11 | Bias Repeatability(1σ,10s) | μg | ≤100 |
| 12 | Scale Factor Non-linearity | ppm | ≤100 |
| 13 | Zero-g Offset vs. Temperature (all axis) | mg/°C | 0.75(MAX) |
| 14 | Noise (all axis) | μg/√Hz | 80 |
| 15 | Measurement Range | g | ±10/±20/±40(Choosable) |
| 16 | Main Body | Bandwidth | Hz | ≥500 |
| 17 | Steady Power Consumption | W | ≤5.0 |
| 18 | Insulation Resistance | MΩ | ˃100 |
| 19 | Weight | g | ≤275 |
| 20 | Dimension | mm | 67*73*49 |
Table 2 The electrical interface of the gyroscope uses J30-15ZK connector
| Pin | Pin Mark | Definition | Direction |
| 1, 9 | +5v | Power + | IN |
| 2, 10 | GND | Power GROUND | IN |
| 4 | R+ | RS422 Receive + | IN |
| 12 | R- | RS422 Receive - | IN |
| 3 | T+ | RS422 Transmit + | OUT |
| 11 | T- | RS422 Transmit - | OUT |
| 5 | COM_GND | 422 Communication Ground | OUT |
| 13 | PPSin | Second Pulse Input | IN |
| 6 | Synclkin | Clock Input | IN |
| 14 | Pulse1in | Camera Pulse 1 | IN |
| 7 | Pulse2in | Camera Pulse 1 | IN |
| 15 | Synclkout | Clock Output | OUT |
| 8 | PPSout | Second Pulse Output | OUT |
Main Features
High Degree of Engineering, Highly Cost-Effective
Pure Solid-State Design with Strong Environmental Adaptability
Full Digital RS-422 Electrical Interface Output
Application
Navigation guidance
Attitude measurement and control systems for small missiles and guided bombs
Fig. 1 Dimensions of the external structure
