Fiber Optic Gyro for Aerospace Applications

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PRODUCTS DETAILS

Basic Info.

Model NO.
F98
Customized
Customized
Non-Linearity Scale Factor
<50ppm (1sigma;)
Scale Factor Asymmetry
<50ppm
Scale Factor Repeatability
<50ppm
Dynamic Range
300 Deg;/S
Zero Bias Stability
<0.05 Deg;/H (1sigma;)
Bandwidth
>200Hz
Transport Package
Sponge and Box
Specification
70mm× 70mm× 32mm
HS Code
9031809090
Production Capacity
500/Month

Product Description

Fiber optic gyro for aerospace applications

Overview
This document specifies the requirements and methods for use and maintenance of F98B fiber optic gyroscope (product for short).
  1. Product introduction
    1. Working principle, function and scope of application of the product
      1. How it works
This product is an inertial angular rate sensor based on the optical Sagnac effect, which is used to measure the angular rate of the carrier along the sensitive axis of the product. An angular rate sensing unit of the product is an optical fiber ring, a digital closed-loop detection circuit is used for extracting the optical path difference of clockwise and counterclockwise propagation light caused by external physical angular rate and sensed by the optical fiber ring, and meanwhile, the optical path difference signal is converted into a voltage signal for closed-loop feedback and control, so that the modulation and demodulation of the signal are realized, and the purpose of high-precision angular rate signal detection is achieved.
      1. Function
This product is composed of an optical angular velocity sensing unit and a signal detection unit, providing single-axis angular increment information and internal temperature information.
      1. Scope of application
The products are mainly suitable for high-precision inertial navigation systems, positioning and orientation systems and other applications.
    1. Composition
The main components of the product are as follows:
  1. The optical path unit comprise a light source, an optical fiber re, an integrated optical phase modulator, an optical fiber coupler and an optical detector;
  2. The circuit unit comprises a light source driving circuit and a detection and control signal circuit board;
  3. Gyroscope structural parts.
    1. Appearance and installation dimension
Overall dimension (mm): (98 ± 0.1) × (98 ± 0.1) × (35 ± 0.1) (L × W × H);
Installation dimension (mm): (80 ± 0.1) × (80 ± 0.1) (L × W), Φ5.4mm × 4, such as below
Fiber Optic Gyro for Aerospace Applications


Main performance
parameters See the main performance parameters of the product for details.
Table 1 Main performance parameters
 
No. Test item Unit Technical requirements
1 Overall dimensions mm 98×98×35
2 Start time min ≤3
3 Zero bias stability
(10 s smoothing, 1σ)		 º/h ≤0.02
4 Zero-bias repeatability º/h ≤0.02
5 Random walk coefficient º/h1/2 ≤0.001
6 Scale factor nonlinearity ppm ≤20
7 Scale factor repeatability ppm ≤20
8 Operating temperature ºC -40~+60
9 Storage temperature ºC -50~+70
10 Dynamic range (°)/s ±300
11 Supply voltage V +5V
12 Steady-state power consumption W <4

Power requirements
Serial number Name Request
1 Power supply accuracy ±5%
2 Power ripple (Vpp) 20mV
3 Supply current >1.5A

Electrical connection interface
Point number Definition Comment
1,9 +5V Power supply input
2,10 GND Power ground
5 RXD+ Gyro differential sorting and correcting
13 RXD- Gyro differential gating negative
6 TXD+ Gyro differential output positive
14 TXD+ Gyro differential output negative
3,4,7,8,11,12,15 -- Reserved

Fiber Optic Gyro for Aerospace Applications Fiber Optic Gyro for Aerospace Applications
 
 

 

 

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