Aviation Navigation TDF41A Airborne Optical Gyro Inertial Navigation

Brand Name:NAVI OPTICS
Certification:CCS
Model Number:TDF41A
Minimum Order Quantity:one set
Delivery Time:5-8 work days
Payment Terms:L/C,T/T
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Address: 1F,Raching Bld, No.3 Seoul Rd,
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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


TypeTDF41A
AccelerometerMonths Bias Repeatability≤500μg
Months Scale Factor Accuracy≤500ppm
GyroBias Repeatability≤0.1°/hr
Scale Factor Accuracy≤300ppm
Random walk≤0.03°/√hr
FeaturesPosition accuracyPure inertia≤1nm/10min
Inertial navigation satellite combinationbetter than satellite accuracy
Velocity accuracyPure inertia——
Inertial navigation satellite combination≤0.2m/s
Angular Rate≥±400°/sec
Angular Acceleration100000°/sec2
Acceleration>40g
Angular AttitudeAny Orientation
Alignment time≤5min
Input/output2 RS422 serial ports
Alignment TimeTime<5min
AHRS Applications PerformanceHeading AccuracyPure inertia——
Satellite navigation combination≤1°sec(L)
Pitch & Roll AccuracyPure inertia——
Satellite navigation combination≤0.2°
CharacteristicsPower consumption<10W
Dimensions70×70×53
Weight<500g
Temperature-40℃~60℃
Shock15g,Half-sine wave 11ms
Input VoltageDC24V(±25%)
CoolingConduction to mounting plate
Vibration20~2000Hz,6.06g
MTBF>20000 hours


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Aviation Navigation TDF41A Airborne Optical Gyro Inertial Navigation

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