Silicon optical coupling assembly, silicon optical integrated module and integrated resonant fiber-optic gyroscope

An integrated module, fiber coupling technology, applied in Sagnac effect gyroscopes, gyroscopes/steering sensing devices, instruments, etc., can solve the limitations of miniaturization of fiber resonators, large loss of fiber resonators, and large minimum bending radius. and other problems, achieving the effect of small-volume packaging is beneficial, reducing the loss of the resonator cavity, and improving the signal-to-noise ratio

Active Publication Date: 2020-11-17
XIAN FLIGHT SELF CONTROL INST OF AVIC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004]In order to improve the integration of gyroscopes, researchers usually choose smaller fiber optic devices, but affected by the manufacturing process and fusion points of fiber optic devices, resonant fiber optic gyroscopes Cannot be further miniaturized
In terms of new optical fiber applications, researchers have fused the photonic crystal fiber and the existing coupler tail fiber to obtain a fiber resonator that not only has a large loss, but also

Method used

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  • Silicon optical coupling assembly, silicon optical integrated module and integrated resonant fiber-optic gyroscope
  • Silicon optical coupling assembly, silicon optical integrated module and integrated resonant fiber-optic gyroscope
  • Silicon optical coupling assembly, silicon optical integrated module and integrated resonant fiber-optic gyroscope

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Embodiment 1

[0027] Example 1: See figure 1 , Which is a schematic view of a preferred structure of the present invention is an integrated resonator fiber optic gyro. The present invention is an integrated resonator fiber optic gyro comprising a silicon integrated optical module 101 and photonic crystal fiber 102. The integrated optical module comprises a silicon integrated light source 1, an integrated waveguide Y 2, a first integrated optical modulator 3, a second integrated optical modulator 4, a silicon optical coupling assembly 103, a first integrated detector 11, the second integrated detector 12. PCF PCF 10 and the upper end of the lower end 11 connected to upper and lower ends of the silicon light coupling assembly 103. Preparation of all devices on silicon using silicon photonics technology, to complete the silicon chip integrated light.

[0028]The silicon integrated optical module is the optical path propagation channel: generating a laser integrated light source 1, the integrated t...

Embodiment 2

[0043] Example 2, this embodiment of the present invention is integrated with the resonator fiber optic gyro is similar to the structure of Example 1 of the embodiment, also refer Figure 5 , Image 6 , Silicon in this embodiment the light coupling assembly embodiment differ from the embodiment in Example 1. In this embodiment, each mating through engagement between said optical fiber forms an optical fiber fixing block and a control arm, and an optical fiber and the optical fiber fixing block control arm. And the optical fiber and the optical fiber fixing block control arm, and an optical fiber and the optical fiber fixing block is provided with a control surface of the arm piece 40 for dot type thermostat, using a thermally induced expansion effects control optical fiber fixing block and temperature control by a control arm piece, the telescoping fiber optic and optical fiber fixing block and the control arm, in order to achieve the locking function and regulation. While each of t...

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Abstract

The invention relates to a silicon optical coupling assembly, a silicon optical integrated module and an integrated resonant fiber-optic gyroscope. The integrated resonant fiber-optic gyroscope comprises a silicon light integration module and a photonic crystal fiber. An integrated light source in the silicon optical integration module emits light, the light is divided into two paths from the waveguide to the integrated Y waveguide, and then the light reaches the silicon optical coupling assembly after passing through the integrated optical modulator; a part of light enters the detector through the silicon optical coupling assembly, and the other light is coupled into the photonic crystal fiber and then enters the fiber from the other end through the silicon optical coupling assembly to form circulating light, and part of the circulating light is reflected into the detector. After the integrated optical modulator receives feedback of the detector, optical frequency shift is locked on aforward and reverse resonance peak, a frequency shift difference value is a gyro output signal, and a position error is compensated through the lens and the optical fiber control assembly so as to reduce cavity loss. The silicon optical coupling assembly has the characteristics of no melting point and integration, miniaturization of the gyroscope is facilitated, the signal-to-noise ratio of the gyroscope is high, and the gyroscope has high practical application value.

Description

Technical field [0001] The present invention pertains to a silicon photonics technique, to a silicon optical coupling assembly, integrated silicon optical modules and integrated resonator fiber optic gyro. Background technique [0002] Vibration resonator fiber optic gyro (Resonator Fiber Optic Gyro, RFOG) is an angular velocity sensor using the Sagnac effect optical resonant cavity frequency difference measured clockwise and counterclockwise light beams to obtain angular velocity information. The gyro operating principle of combining high sensitivity resonator laser gyroscope on the interferometric fiber optic gyro and a multi-turn optical paths of these two advantages, high-precision measurement can be realized in a small volume, small size has the potential next-level navigation gyro. [0003] Resonator fiber optic gyro main device has a light source, a coupler, optical modulators, optical detectors, optical fibers, now commonly used way of connecting each welded fiber devices...

Claims

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Application Information

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IPC IPC(8): G01C19/72
CPCG01C19/721G01C19/725
Inventor 蓝士祺李俊胡强王珂雷兴曹耀辉吴凡蒋樱子
Owner XIAN FLIGHT SELF CONTROL INST OF AVIC
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