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Product Details:
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| Months Bias Repeatability: | ≤50μg | Months Scale Factor Accuracy: | ≤500ppm |
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| Bias Repeatability: | ≤0.3°/hr | Scale Factor Accuracy: | ≤500ppm |
| Random Walk: | ≤0.01°/√hr | Vibration: | 20~2000Hz,6.06g |
| MTBF: | ＞20000 Hours |
Aviation Navigation TDF61A Airborne Optical Gyro Inertial Navigation
1 Introduction
The airborne optical gyro inertial navigation system (INS) employs optical gyros and quartz accelerometers as its core sensing components, operating under either a strapdown or dither-modulated inertial navigation architecture. High-speed embedded navigation software processes sensor data in real time to deliver continuous positioning and orientation outputs. This product series integrates multi-source navigation inputs including satellite signals (GNSS), celestial observations, barometric altimetry, radio navigation aids, and visual odometry based on mission-specific configurations. It offers operational flexibility through selectable modes ranging from standalone inertial navigation to adaptive multi-sensor fusion, delivering comprehensive platform states (position, velocity, attitude) across dynamic environments.
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 | TDF61A | ||
| Accelerometer | Months Bias Repeatability | ≤50μg | |
| Months Scale Factor Accuracy | ≤500ppm | ||
| Gyro | Bias Repeatability | ≤0.3°/hr | |
| Scale Factor Accuracy | ≤500ppm | ||
| Random walk | ≤0.01°/√hr | ||
| Features | Position accuracy | Pure inertia | ≤4nm/1h |
| Inertial navigation satellite combination | better than satellite accuracy | ||
| Velocity accuracy | Pure inertia | ≤3.0m/s | |
| Inertial navigation satellite combination | ≤0.2m/s | ||
| Angular Rate | ≥±400°/sec | ||
| Angular Acceleration | 100000°/sec2 | ||
| Acceleration | ＞25g | ||
| Angular Attitude | Any Orientation | ||
| Alignment time | ≤5min | ||
| Input/output | 3 RS422 full-duplex serial ports, 1 100M Ethernet port | ||
| Alignment Time | Time | ＜5min | |
| AHRS Applications Performance | Heading Accuracy | Pure inertia | ≤0.4°sec(L) |
| Satellite navigation combination | ≤0.2°sec(L) | ||
| Pitch & Roll Accuracy | Pure inertia | ≤0.08° | |
| Satellite navigation combination | ≤0.03° | ||
| Characteristics | Power consumption | ＜15W | |
| Dimensions | 110×110×100 | ||
| Weight | ＜1.7kg | ||
| 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 | ||
Contact Person: Yu.Jing
Tel: +8613045000776
Fax: 86-532-68977475
