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Multi-list redundant strapdown inertial measuring device for laser gyroscope

A laser gyro and measuring device technology, applied in the field of inertial guidance, can solve the problems of high cost, large volume, and failure to meet the requirements of the system, and achieve the effects of low cost, high precision, and high reliability

Active Publication Date: 2014-03-19
BEIJING AEROSPACE ERA LASER NAVIGATION TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Two or more sets of inertial measurement device schemes are large in size and high in cost, which cannot meet the requirements of the system

Method used

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  • Multi-list redundant strapdown inertial measuring device for laser gyroscope
  • Multi-list redundant strapdown inertial measuring device for laser gyroscope
  • Multi-list redundant strapdown inertial measuring device for laser gyroscope

Examples

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Embodiment Construction

[0018] like figure 1 As shown, the present invention includes: 5 sets of laser gyroscope systems, 5 sets of accelerometer systems, device power supply systems and 2 sets of calculation computers; each set of laser gyroscope systems includes 1 RLG laser gyroscope, laser gyroscope power supply system and gyro function Circuit, each accelerometer system includes 1 QA quartz accelerometer, accelerometer power supply system and I / F conversion circuit, each system works independently; 3 RLG laser gyroscopes and 3 QA quartz accelerometers are installed orthogonally on the instrument On the main body, 2 redundant RLG laser gyroscopes and 2 redundant QA quartz accelerometers are installed obliquely on the main body, 2 redundant RLG laser gyroscopes and 2 redundant QA quartz accelerometers and 3 quadrature sensitive The angle of the axis is 30° to 75°; the power supply system provides independent power supply for 5 laser gyro systems and 5 accelerometer systems, and provides independent...

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PUM

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Abstract

The invention provides a multi-list redundant strapdown inertial measuring device for a laser gyroscope. According to the multi-list redundant strapdown inertial measuring device, three orthogonally-arranged gyroscopes Gx, Gy and Gz and two obliquely-arranged gyroscopes Gs and Gt can be used for sensing an angle speed of a carrier moving in an inertial space; three orthogonally-arranged accelerometers Ax, Ay and Az and two obliquely-arranged accelerometers As and At can be used for sensing a specific force of the carrier moving in the inertial space; a resolving computer of the device can be used for collecting inertial information in real time and at a high speed and the inertial information is sent to a navigational computer in real time by a high-speed bus; after the navigational computer obtains inertia type instrument information transmitted by the strapdown inertial measuring device for the laser gyroscope, information including a course, a posture, a speed, a position and the like of the carrier can be calculated and output in real time and is supplied to a guidance and posture control system for use.

Description

technical field [0001] The invention belongs to the field of inertial guidance, and relates to a multi-meter redundant laser gyro strapdown inertial device. Background technique [0002] In the field of autonomous guidance, inertial measurement devices are generally required to complete attitude and guidance control, and inertial measurement devices are the core components of autonomous guidance systems. In the history of the development of inertial measurement devices, there are two corresponding measurement devices: one is a platform-type inertial navigation device, and the other is a strap-down inertial navigation device. The platform inertial navigation device has a three (or four) axis frame structure, which isolates the inertial element from the motion of the carrier, so that the body on which the inertial element is installed is physically maintained in the inertial space without angular movement, thereby measuring the relative inertial space of the carrier. attitude...

Claims

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Application Information

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IPC IPC(8): G01C21/16
CPCG01C21/16
Inventor 王跃鹏
Owner BEIJING AEROSPACE ERA LASER NAVIGATION TECH CO LTD
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