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Six-redundancy-type optical fiber strapdown inertial navigation system (SINS)

An inertial navigation system and optical fiber strapdown technology, applied in the field of inertial navigation, can solve the problems of high cost, achieve stable performance, improve accuracy and reliability, and have strong anti-interference effects

Inactive Publication Date: 2013-11-13
BEIHANG UNIV
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Problems solved by technology

There are two main ways to improve the reliability and accuracy of the inertial navigation system: one is to improve the reliability and accuracy of a single instrument, which puts forward higher requirements for the processing technology and various technical indicators of the inertial instrument, and the cost of implementation is relatively high ;Another method is to use redundancy schemes to improve system reliability and accuracy, which is an ideal method and relatively easy to implement

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  • Six-redundancy-type optical fiber strapdown inertial navigation system (SINS)
  • Six-redundancy-type optical fiber strapdown inertial navigation system (SINS)
  • Six-redundancy-type optical fiber strapdown inertial navigation system (SINS)

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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the accompanying drawings and embodiments. The embodiment of the present invention takes a certain type of flight vehicle as an example.

[0027] The invention is a six-redundant optical fiber strapdown inertial navigation system, which consists of three parts: a structural part, an inertial device part and a peripheral circuit part. The position connection relationship between them is: the inertial device is installed on the dodecahedron IMU bracket of the structural part, and the peripheral circuit part is mainly distributed on the body side of the structural part.

[0028] The structural part mainly includes a dodecahedron IMU bracket, a fiber optic gyroscope skeleton and a system body.

[0029] The dodecahedron IMU bracket is: It is necessary to explain the structure of the dodecahedron. The dodecahedron is one of the five Platonic solids and belongs to the quasi-crystal structure. It has 20 v...

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Abstract

The invention discloses a six-redundancy-type optical fiber strapdown inertial navigation system (SINS). The system is composed of a structural component part, an inertial device part and a peripheral circuit part, wherein the inertial device part is installed on a regular dodecahedron IMU (inertial measurement unit) support of the structural component part, and the peripheral circuit part is distributed on the system body brink of the structural component part. In the invention, the regular dodecahedron is designed to be of a hollow structure, so that high stiffness and light weight of a system IMU table body are realized; redundant configuration is adopted, so that the accuracy and reliability of the inertial navigation system are improved; the separation of the optical path and circuit of an optical fiber gyroscope is basically realized in structure for a system optical fiber gyroscope, so that varying degrees of influences of temperature and temperature gradient change brought by circuit heating on the optical path are avoided; the system has stable performance and good adaptive capacity to environment, can bear a variety of environment test requirements similar to that born by the inertial navigation system, and has good real-time performance.

Description

technical field [0001] The invention relates to a six-redundant optical fiber strapdown inertial navigation system based on six optical fiber gyroscopes and six accelerometers, and belongs to the technical field of inertial navigation. Background technique [0002] Inertial technology is a comprehensive technology involving multiple disciplines. It is a general term for inertial navigation and inertial guidance technology, inertial instrument technology, inertial measurement technology, and related systems and device technologies. The inertial navigation system relies on its own inertial sensitive components and does not rely on any external information to measure navigation parameters. Therefore, it is not subject to natural or artificial interference and has good concealment. It is a completely autonomous navigation system. [0003] Modern missiles, satellites, spacecraft and other carriers have put forward higher and higher requirements for the reliability and accuracy of...

Claims

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Application Information

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IPC IPC(8): G01C21/16
Inventor 张春熹宋来亮晁代宏赵新强
Owner BEIHANG UNIV
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