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TDF645B Airborne Optical Gyro Inertial Navigation System with ≤20μg Bias Repeatability, ＞15000 hours MTBF, and Multi-sensor Fusion
Key Attributes
Brand Name:
NAVI OPTICS
Model Number:
TDF645B
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
TDF645B airborne optical gyro INS delivers ≤1nm/6h position accuracy with multi-sensor fusion. Features 15,000+ hours MTBF, -40℃ to 60℃ operation, and supports satellite/celestial/visual navigation integration for superior UAV performance.
Product Custom Attributes
Highlight
Airborne Optical Gyro Inertial Navigation
,Aviation imu inertial measurement unit
,Optical Gyro imu inertial measurement unit
Months Bias Repeatability:
≤20μg
Months Scale Factor Accuracy:
≤20ppm
Bias Repeatability:
≤0.008°/hr
Scale Factor Accuracy:
≤20ppm
Random Walk:
≤0.003°/√hr
Vibration:
20~2000Hz,6.06g
MTBF:
＞15000 Hours
Product Description
Aviation Navigation TDF645B Airborne Optical Gyro Inertial Navigation
The Airborne Optical Gyro Inertial Navigation System (INS) employs optical gyroscopes and quartz accelerometers as its core sensing components, utilizing either a strapdown or dithered (modulated) system architecture. Operating with advanced navigation software at high processing speeds, the system delivers real-time navigation data through its sophisticated computational core.
This product series features multi-source integration capabilities, supporting fusion of satellite navigation, celestial navigation, radio navigation, altimeter data, and visual navigation systems according to mission requirements. Offering flexible operational modes ranging from pure inertial navigation to optimized multi-sensor fusion, it provides comprehensive navigation parameters including precise position, velocity, and attitude information for airborne platforms.
Application Fields
Suitable for fixed-wing UAVs, rotary-wing UAVs, and specialized airborne vehicles.
Performance Characteristics
- Supports multi-sensor fusion, incorporating satellite, celestial, altimeter, radio, and visual navigation data
- Supports switching between self-alignment, moving-base alignment, and transfer alignment based on customer needs
- Capable of alignment on ground-based vibrating platforms and in-flight alignment
- Equipped with system fault detection and alarm functions
Technical Specifications
| Parameter Type | Specification | Value |
|---|---|---|
| Accelerometer | Months Bias Repeatability | ≤20μg |
| Months Scale Factor Accuracy | ≤20ppm | |
| Gyro | Bias Repeatability | ≤0.008°/hr |
| Scale Factor Accuracy | ≤20ppm | |
| Random walk | ≤0.003°/√hr | |
| Features | Position accuracy (Pure inertia) | ≤1nm/6h |
| Position accuracy (Inertial navigation satellite combination) | better than satellite accuracy | |
| Velocity accuracy (Pure inertia) | ≤1.0m/s | |
| Velocity accuracy (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 | |
| AHRS Applications Performance | Heading Accuracy (Pure inertia) | ≤0.1°sec(L) |
| Heading Accuracy (Satellite navigation combination) | ≤0.05°sec(L) | |
| Pitch & Roll Accuracy | Pure inertia | ≤0.05° |
| Satellite navigation combination | ≤0.02° | |
| Power consumption | ＜40W | |
| Dimensions | 193*169*160 | |
| Weight | ＜6.5kg | |
| Temperature | -40℃~60℃ | |
| Shock | 15g, Half-sine wave 11ms | |
| Input Voltage | DC24V(±25%) | |
| Cooling | Conduction to mounting plate | |
| Vibration | 20~2000Hz, 6.06g | |
| MTBF | ＞15000 hours | |
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