Aviation Navigation TDF41A Airborne Optical Gyro-Inertial Navigation
1 Introduction
The airborne optical gyro inertial navigation system (INS) utilizes optical gyros and quartz accelerometers as its core sensors, employing either a strapdown or dithered (modulated) inertial navigation system architecture. It runs advanced navigation software internally at high speed to provide real-time navigation information. This series of products can integrate satellite, celestial, altimeter, radio, and visual navigation information, based on user requirements. It supports multiple operating modes, including purely inertial and multi-sensor fusion, providing users with complete navigation parameters for their platforms.
2 Application Fields
Suitable for fixed-wing UAVs, rotary-wing UAVs, and specialized airborne vehicles.
3 Performance Characteristics
Capable of alignment on ground-based vibrating platforms and in-flight alignment.
Supports switching between self-alignment, moving-base alignment, and transfer alignment based on customer needs.
Supports multi-sensor fusion, incorporating satellite, celestial, altimeter, radio, and visual navigation data.
Equipped with system fault detection and alarm functions.
4 Main parameters
| Type |
TDF41A |
| Accelerometer |
Months Bias Repeatability |
≤500μg |
| Months Scale Factor Accuracy |
≤500ppm |
| Gyro |
Bias Repeatability |
≤0.1°/hr |
| Scale Factor Accuracy |
≤300ppm |
| Random walk |
≤0.03°/√hr |
| Features |
Position accuracy |
Pure inertia |
≤1nm/10min |
| Inertial navigation satellite combination |
better than satellite accuracy |
| Velocity accuracy |
Pure inertia |
—— |
| Inertial navigation satellite combination |
≤0.2m/s |
| Angular Rate |
≥±400°/sec |
| Angular Acceleration |
100000°/sec2 |
| Acceleration |
＞40g |
| Angular Attitude |
Any Orientation |
| Alignment time |
≤5min |
| Input/output |
2 RS422 serial ports |
| Alignment Time |
Time |
＜5min |
| AHRS Applications Performance |
Heading Accuracy |
Pure inertia |
—— |
| Satellite navigation combination |
≤1°sec(L) |
| Pitch & Roll Accuracy |
Pure inertia |
—— |
| Satellite navigation combination |
≤0.2° |
| Characteristics |
Power consumption |
＜10W |
| Dimensions |
70×70×53 |
| Weight |
＜500g |
| 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 |
Product Tags:
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Aviation Navigation TDF41A Airborne Optical Gyro Inertial Navigation Images
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