Aviation Navigation TDF71A Airborne Optical Gyro Inertial Navigation
Brand Name:NAVI OPTICS
Certification:CCS
Model Number:TDF71A
Minimum Order Quantity:one set
Delivery Time:5-8 work days
Payment Terms:L/C,T/T
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Aviation Navigation TDF71A Airborne Optical Gyro Inertial Navigation
1 Introduction
The airborne optical gyro inertial navigation system (INS) employs optical gyroscopes and quartz accelerometers as its core sensing components, utilizing either a strapdown or modulated (dithered) system architecture. With high-speed embedded navigation algorithms, it delivers real-time positioning and orientation data. This product series integrates satellite-based (GNSS), celestial, barometric altimeter, radio navigation, and visual perception inputs through configurable fusion architectures, tailored to mission-specific requirements. Supporting diverse operational modes ranging from standalone inertial navigation to hybrid multi-sensor solutions, it provides comprehensive platform navigation parameters including 3D position, velocity, attitude, and angular rates.
2 Application Fields
Suitable for fixed-wing UAVs, rotary-wing UAVs, and specialized airborne vehicles.
3 Performance Characteristics
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.
Capable of alignment on ground-based vibrating platforms and in-flight alignment.
Equipped with system fault detection and alarm functions.
4 Main parameters
| Type | TDF71A | ||
| Accelerometer | Months Bias Repeatability | ≤20μg | |
| Months Scale Factor Accuracy | ≤20ppm | ||
| Gyro | Bias Repeatability | ≤0.01°/hr | |
| Scale Factor Accuracy | ≤20ppm | ||
| Random walk | ≤0.005°/√hr | ||
| Features | Position accuracy | Pure inertia | ≤2nm/1h |
| Inertial navigation satellite combination | better than satellite accuracy | ||
| Velocity accuracy | Pure inertia | ≤1.5m/s | |
| Inertial navigation satellite combination | ≤0.2m/s | ||
| Angular Rate | ≥±400°/sec | ||
| Angular Acceleration | 100000°/sec2 | ||
| Acceleration | ＞25g | ||
| Angular Attitude | Any Orientation | ||
| Alignment time | ≤8min | ||
| Input/output | 3 RS422 full-duplex serial ports, 1 100M Ethernet port | ||
| Alignment Time | Time | ＜5min | |
| AHRS Applications Performance | Heading Accuracy | Pure inertia | ≤0.2°sec(L) |
| Satellite navigation combination | ≤0.1°sec(L) | ||
| Pitch & Roll Accuracy | Pure inertia | ≤0.03° | |
| Satellite navigation combination | ≤0.02° | ||
| Power consumption | ＜15W | ||
| Characteristics | Dimensions | 130×130×100 | |
| Weight | ＜2.2kg | ||
| 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 | ||
Aviation Navigation TDF71A Airborne Optical Gyro Inertial Navigation
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