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TDF71A Airborne Optical Gyro Inertial Navigation System with ≤20μg Bias Repeatability, ＞20000 hours MTBF, and ≤0.005°/√hr Random Walk
Key Attributes
Brand Name:
NAVI OPTICS
Model Number:
TDF71A
Place of Origin:
China
Certification:
CCS
Minimum Order Quantity:
one set
Supply Ability:
10 sets per month
Delivery Time:
5-8 work days
Payment Terms:
L/C,T/T
Standard Packaging:
Carton box
Product Summary
TDF71A airborne optical gyro INS delivers ≤2nm/h position accuracy with >20,000 hours MTBF. Features multi-sensor fusion, ≤8min alignment, and robust performance in extreme conditions (-40°C~60°C, 15g shock).
Product Custom Attributes
Highlight
inertial guidance system
,Airborne Optical Gyro Inertial Navigation
Months Bias Repeatability:
≤20μg
Months Scale Factor Accuracy:
≤20ppm
Bias Repeatability:
≤0.01°/hr
Scale Factor Accuracy:
≤20ppm
Random Walk:
≤0.005°/√hr
Vibration:
20~2000Hz,6.06g
MTBF:
＞20000 Hours
Product Description
Aviation Navigation TDF71A Airborne Optical Gyro Inertial Navigation
The TDF71A airborne optical gyro inertial navigation system employs optical gyroscopes and quartz accelerometers as core sensing components, utilizing strapdown or modulated system architecture. With high-speed embedded navigation algorithms, it delivers real-time positioning and orientation data. This system integrates satellite-based (GNSS), celestial, barometric altimeter, radio navigation, and visual perception inputs through configurable fusion architectures tailored to mission requirements.
Application Fields
Suitable for fixed-wing UAVs, rotary-wing UAVs, and specialized airborne vehicles.
Performance Characteristics
- Supports switching between self-alignment, moving-base alignment, and transfer alignment
- 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
Technical Specifications
| Parameter | Specification |
|---|---|
| Type | TDF71A |
| Accelerometer Bias Repeatability | ≤20μg |
| Accelerometer Scale Factor Accuracy | ≤20ppm |
| Gyro Bias Repeatability | ≤0.01°/hr |
| Gyro Scale Factor Accuracy | ≤20ppm |
| Gyro Random Walk | ≤0.005°/√hr |
| Position Accuracy (Pure Inertia) | ≤2nm/1h |
| Position Accuracy (INS+Satellite) | Better than satellite accuracy |
| Velocity Accuracy (Pure Inertia) | ≤1.5m/s |
| Velocity Accuracy (INS+Satellite) | ≤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 |
| AHRS Heading Accuracy (Pure Inertia) | ≤0.2°sec(L) |
| AHRS Heading Accuracy (Satellite Navigation) | ≤0.1°sec(L) |
| Pitch & Roll Accuracy (Pure Inertia) | ≤0.03° |
| Pitch & Roll Accuracy (Satellite Navigation) | ≤0.02° |
| Power Consumption | ＜15W |
| Dimensions | 130*130*100 mm |
| Weight | ＜2.2kg |
| Operating Temperature | -40℃~60℃ |
| Shock Resistance | 15g, Half-sine wave 11ms |
| Input Voltage | DC24V(±25%) |
| Cooling Method | Conduction to mounting plate |
| Vibration Resistance | 20~2000Hz, 6.06g |
| MTBF | ＞20000 hours |
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