Lightweight and miniaturized 3s configuration triaxial integrated fiber-mems inertial measurement unit

By integrating optical sensing modules and MEMS sensing modules, and adopting a "one-to-three" optical path design and flexible connection lines, the problems of volume redundancy and loose module coupling of the inertial measurement unit are solved, realizing a lightweight, miniaturized and highly reliable inertial measurement unit.

CN122329296APending Publication Date: 2026-07-03BEIJING INST OF CONTROL ENG
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
BEIJING INST OF CONTROL ENG
Filing Date
2026-05-11
Publication Date
2026-07-03

AI Technical Summary

Technical Problem

Existing inertial measurement units are bulky and loosely coupled, making it difficult to meet the requirements of spaceborne platforms for compactness, power consumption, and long-term reliability.

Method used

The lightweight and miniaturized 3S configuration triaxial integrated fiber-MEMS inertial measurement unit integrates an optical sensing module, a MEMS sensing module, and a signal processing module. It adopts a "one-to-three" integrated optical path design, where the light source component shares the light source with three fiber optic ring components. The MEMS gyroscope circuit board adopts a 3S configuration design, and the leads between the circuit boards are flexible connections.

Benefits of technology

This technology enables the inertial measurement unit to be lightweight and miniaturized, improving manufacturability and overall reliability, reducing overall size, enhancing optical path consistency and system stability, improving installation flexibility and platform adaptability, avoiding interference caused by long-distance leads, and enhancing product reliability.

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Abstract

This invention relates to a lightweight, miniaturized 3S configuration triaxial integrated fiber-MEMS inertial measurement unit, belonging to the field of measurement devices. It includes a base cover, a power supply and detection board assembly located on the top of the base cover, a light source assembly located above the power supply and detection board assembly, a MEMS assembly mounted above the light source assembly, a base fixed to the base cover, fiber optic ring assemblies fixed to the base, and a reference mirror fixed to the top of the base. The power supply and detection board assembly, the light source assembly, and the MEMS assembly are all arranged inside the base. The three fiber optic ring assemblies are evenly distributed on a conical surface with an outer half-cone angle of 54.74° and a bottom projection of 120°. The light source assembly shares a light source with the three fiber optic ring assemblies via a 1*3 coupler. This invention eliminates the unnecessary space occupied by the traditional three independent light source configuration, reduces the overall volume, and improves optical path consistency and system stability. It can meet the engineering requirements of commercial satellite platforms for the miniaturization and mass production of inertial measurement components.
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