Introduction
LKF-F3X80 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.
The LKF-F3X80 plays a key role in navigation and positioning due to its highly accurate rotational measurement capabilities. It is widely used in aircraft, satellites and drones to ensure they maintain accurate positioning and navigation in the sky. This is critical for air rescue, weather forecasting and the stability of communications satellites.
Table 1 Performance parameters of LKF-F3X80 Three-axis FOG IMU
| Fiber Optic Gyroscope | A | B | C |
| Bias Repeatability at Room Temperature (By times, by days) (º/h) | ≤0.5 | ≤0.3 | ≤0.20 |
| Bias stability at Constant Temperature (º/ h) | ≤0.5 | ≤0.3 | ≤0.20 |
| Scale Factor Repeatability at Room Temperature (ppm) | ≤50 | ≤30 | ≤20 |
| Scale Factor Asymmetry at Constant Temperature (ppm) | ≤30 | ≤20 | ≤20 |
| Scale Factor Nonlinearity at Constant Temperature (ppm) | ≤30 | ≤20 | ≤20 |
| Threshold (º/h) | ≤0.5º/h |
| Angular Rate Range (º/s) | -500 to +500 º/s |
| Bandwidth (Hz) | 100 |
| Dimensions (mm) | Ф80*70 |
| Weight (g) | 780±20 (with accelerometer) |
| Operating Temperature (°C) | -40 to +65 |
| Quartz Accelerometer |
| No. | Item | Technical Requirement |
| 1 | Range (g) | ≥±40 |
| 2 | Scale Factor Temperature Coefficient (ppm /°C) | ≤100 |
| 3 | Scale Factor Monthly Stability (ppm) | ≤100 |
| 4 | Bias (mg) | ≤±7 |
| 5 | Bias Temperature Coefficient (μg /°C) | ≤100 |
| 6 | Bias Monthly Stability (μg) | ≤100 |
| 7 | Second-order Nonlinear Coefficient (μg /g2) | ≤20 |
| 8 | Mounting angle (") | ≤200 |
| 9 | Outlook | No scratches, cracks, or corrosion |
| 10 | Isolate | ≥20MΩ; (100V),25℃±5℃, humidity≤80% |
Table 2 The electrical interface of the gyroscope uses J30-15ZK connector
| LKF-F3X80-IMU/INS Output Definition |
| J30J-15ZK | Define | Note |
| 5, 13 | +24V | Inertia Combination Power Supply |
| 6, 7 | +24V (ground) |
| 1 | T3+ | Serial Port |
| 2 | T3- |
| 3 | R3+ |
| 4 | R3- |
| 11 | T2+ | IMU Data Output Serial Port |
| 12 | T2- |
| 14 | T1+ | Debugging Serial Ports |
| 15 | T1- |
| 9 | R1+ |
| 10 | R1- |
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
