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Spaceborne image assisted navigation method

A technology for assisting navigation and images, applied in directions such as navigation computing tools, can solve the problems of large data volume, hardware resource consumption, slow processing speed, etc., and achieve the effect of low hardware resource consumption, easy implementation, and simple method.

Active Publication Date: 2018-01-26
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The present invention aims to solve the problems of slow processing speed and large consumption of hardware resources due to the large amount of data in the existing image processing-assisted attitude determination method, and now provides a satellite-borne image-assisted navigation method

Method used

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Experimental program
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specific Embodiment approach 1

[0015] Specific implementation mode one: refer to image 3 Describe this embodiment in detail, and a kind of satellite-borne image-assisted navigation method provided in this embodiment is specifically prepared according to the following steps:

[0016] Step 1. First, perform image compression on the on-orbit image, and calculate the image gradient value during the compression process;

[0017] Step 2. Load the pre-saved template image, and perform multi-scale Hessian matrix eigenvalue calculation and multi-scale pyramid calculation according to the Hessian matrix of image gradient values ​​at different scales obtained during the compression process, and pass the maximum value Criteria (that is, the acquisition of feature points is obtained according to the maximum value of some points between different layers) to obtain feature points;

[0018] Step 3. According to the feature points of the in-orbit image and the feature points of the template image, the random sampling cons...

specific Embodiment approach 2

[0019] Specific implementation mode two: refer to figure 1 Describe this implementation mode, the difference between this implementation mode and specific implementation mode 1 is: the specific process of step 1 is as follows:

[0020] In the FPGA on-orbit image processing platform, when the image is electronically processed and sent to the platform for compression, the 5 / 3 lifting wavelet transform is performed, and the gradient value of the image is calculated during the wavelet transform; in order to further reduce image noise. The influence of the gradient value improves the stability of the gradient value, and uses the center point and the 5 values ​​​​of its upper, lower, left, and right neighbors to calculate the image gradient value. The one-dimensional transformation formula is as follows:

[0021]

[0022]

[0023]

[0024]

[0025]

[0026] Where y(n) represents the compressed image pixel value of the next level, x(n) refers to the current level image...

specific Embodiment approach 3

[0027] Specific implementation mode three: refer to figure 2 Describe this implementation mode, the difference between this implementation mode and specific implementation mode 2 is:

[0028] In step 2, the specific steps for extracting multi-scale feature points from the compressed image are as follows:

[0029] According to the obtained image gradient value, according to the eigenvalue principle, the feature point judgment is carried out by calculating the gradient eigenvalue; calculate the Hessian matrix of the pixel point I on the orbit image in the mth layer of the compressed image as:

[0030]

[0031] Among them, D x (I,m) is the gradient value of the pixel point I on the track image in the horizontal direction of the mth layer of the compressed image, D y (I,m) is the vertical gradient value D of the pixel point I on the track image in the mth layer of the compressed image xy (I, m) is the gradient value of the pixel point I on the track image in the mth layer o...

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Abstract

A spaceborne image assisted navigation method belongs to the technical field of spacecraft attitude determination. The purpose of the invention is to solve the problems of slow processing speed and large hardware resource consumption, caused by large data bulk, in existing image processing assisted attitude determination methods. The method comprises the following steps: compressing an on-orbit image, and calculating the image gradient value; loading a template image, carrying out multi-scale Hessian matrix feature value calculation and multi-scale pyramid operation according to a Hessian matrix obtained in the compression process, and obtaining feature points according to the maximum value rule; carrying out feature point matching by using a random sampling consistency algorithm accordingto the feature points of the on-orbit image and the feature points of the template image in order to obtain an affine transformation matrix between the two images; and establishing a camera motion model, and transiting the image offset amount into an attitude angle variable quantity. The method can be applied to a microsatellite earth observation system.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude determination, in particular to a satellite-borne image-assisted navigation method. Background technique [0002] As the resolution of remote sensing satellites is getting higher and higher, carrying high-resolution optical payloads on micro-satellites can effectively reduce satellite launch costs, and further realize satellite networking, component replacement, and commercial operation. Compared with existing traditional satellites, micro remote sensing satellites have some new problems, such as low pointing accuracy of satellites in orbit and poor attitude stability. These problems will reduce the resolution of remote sensing images, and even affect the normal work of satellites. The current solutions to these problems are: [0003] 1) Utilize high-precision attitude sensors, such as angular velocity sensors based on magnetic fluid effects and angular displacement sensors based on ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/20
Inventor 徐国栋张兆祥刘明邢雷王梓霖张光宇朱晏辰
Owner HARBIN INST OF TECH