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A Dynamic Alignment Method for Strapdown Inertial Navigation Coordinate System Based on Celestial Navigation Principle

A strapdown inertial navigation and astronomical navigation technology, applied in the field of inertial navigation, can solve the problem that economic effects and time effects cannot meet the need for alignment of strapdown inertial navigation coordinates, and achieve the effect of economical use and flexible use.

Active Publication Date: 2022-05-03
PLA NO 63686 CORPS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Coordinate alignment under static docking conditions cannot meet the alignment requirements of SINS coordinate systems in terms of both economic effects and time effects

Method used

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  • A Dynamic Alignment Method for Strapdown Inertial Navigation Coordinate System Based on Celestial Navigation Principle
  • A Dynamic Alignment Method for Strapdown Inertial Navigation Coordinate System Based on Celestial Navigation Principle
  • A Dynamic Alignment Method for Strapdown Inertial Navigation Coordinate System Based on Celestial Navigation Principle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0050] 1. The implementation uses a set of strapdown inertial navigation (SINS), which is fixedly connected to the base of the photoelectric theodolite.

[0051] Perform dynamic alignment on the basis of standard alignment values ​​in the dock: [-0.4758°, -0.0299°, 180.2523°] (pitch, roll, heading) to obtain the fine-tuning of pitch, roll, and heading. Realize precise alignment of the dynamic coordinate system.

[0052] The coordinates are accurately aligned with the original star measurement results as shown in Table 1.

[0053] In Table 1, the attitude error obtained by each group of satellite measurement solutions is The solution value of .

[0054] In order to further improve the accuracy, when the coordinates are aligned, take 11 times of star measurement The average is the final correction. It can be obtained from Table 1 that the average errors of the photoelectric theodolite and the strapdown inertial navigation pitch (ΔΨ), roll (Δθ) and heading (ΔK) are -6.14", ...

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Abstract

The invention relates to a method for evaluating the attitude dynamic accuracy of strapdown inertial navigation equipment based on the principle of celestial navigation. The method includes the following steps: one is to use the theodolite to obtain the measured star pointing; the other is to calculate the theoretical star pointing by extracting star library data; The coordinate transformation obtains the error between the star's measured pointing and theoretical pointing; the fourth is to correct the error to achieve the alignment of the coordinates of the strapdown inertial navigation. The present invention establishes a method for dynamically aligning strapdown inertial navigation coordinate systems based on the principle of celestial navigation, which breaks the limitation that the alignment of strapdown inertial navigation coordinates needs to be static, and solves the problem of long period and high cost of strapdown inertial navigation coordinate alignment. difficult problem, this method can realize alignment of strapdown inertial navigation coordinates under dynamic conditions, and is flexible and economical.

Description

technical field [0001] The invention relates to a method for dynamically aligning a strapdown inertial navigation coordinate system based on the principle of celestial navigation. The invention belongs to the technical field of inertial navigation. Background technique [0002] Strapdown inertial navigation provides accurate attitude information for aerospace survey ships and coordinate reference data for hulls. As a coordinate reference, the device must be aligned before it can be used. However, the current method of aligning coordinates is extremely inconvenient. [0003] The traditional approach is to combine hull maintenance, which can only be carried out when the ship enters the static situation of the dock stand. On the one hand, it costs a lot of money for a ship to enter the dock, and on the other hand, it takes a long period of time, and it takes a few years to have a chance. The alignment of coordinates under the static condition of docking cannot meet the align...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02G01C21/16
CPCG01C21/025G01C21/165
Inventor 刘新明赵李健周海渊徐如祥周建吴红兵孔祥龙李可
Owner PLA NO 63686 CORPS