Satellite attitude determination method, device and terminal equipment

A satellite attitude and determination method technology, applied in the space field, can solve the problem of low satellite attitude accuracy, and achieve the effect of improving accuracy and reducing errors

Active Publication Date: 2021-06-29
ARMY ENG UNIV OF PLA
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0004] In view of this, the embodiment of the present invention provides a satellite attitude determination method, device and terminal equipment to solve the problem of low accuracy of satellite attitude detection in the prior art

Method used

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  • Satellite attitude determination method, device and terminal equipment
  • Satellite attitude determination method, device and terminal equipment
  • Satellite attitude determination method, device and terminal equipment

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0056] see figure 1 A schematic diagram of the implementation flow of an embodiment of the method for determining the satellite attitude is provided, and the details are as follows:

[0057] Step S101, acquiring the background image of the starry sky at the first moment and the background image of the starry sky at the second moment collected by the spaceborne camera.

[0058] The on-board camera on the satellite can collect background images of the starry sky at different times. Exemplary, see Figure 7 , Figure 7 (a) is the background image of the starry sky at the first moment, and (b) is the background image of the starry sky at the second moment. According to the star points in the background image of the starry sky, the attitude change of the satellite can be quickly estimated. Among them, the first moment and the second moment in this embodiment represent the time before and after the image is collected, and are not specifically limited to a specific time point. The...

Embodiment 2

[0126] Corresponding to the satellite attitude determination method described in Embodiment 1 above, Figure 9 shows the structural block diagram of the device for determining the satellite attitude in the second embodiment of the present invention. For ease of description, only the parts related to this embodiment are shown.

[0127] The device includes: an image acquisition module 110 , a satellite attitude change determination module 120 and a satellite attitude determination module 130 .

[0128] The image acquisition module 110 is used to acquire the background image of the starry sky at the first moment and the background image of the starry sky at the second moment collected by the spaceborne camera.

[0129] The satellite attitude change determination module 120 is used to perform image matching on the starry sky background image at the first moment and the starry sky background image at the second moment, and determine satellites in the time period between the first ...

Embodiment 3

[0133] Figure 10 It is a schematic diagram of the terminal device 100 provided in Embodiment 3 of the present invention. Such as Figure 10 As shown, the terminal device 100 of this embodiment includes: a processor 140, a memory 150, and a computer program 151 stored in the memory 150 and operable on the processor 140, such as a program of a satellite attitude determination method. When the processor 140 executes the computer program 151, it implements the steps in the above embodiment of the satellite attitude determination method, for example figure 1 Steps 101 to 103 are shown. Alternatively, when the processor 140 executes the computer program 151, it realizes the functions of the modules / units in the above-mentioned device embodiments, for example Figure 9 The functions of modules 110 to 130 are shown.

[0134] Exemplarily, the computer program 151 can be divided into one or more modules / units, and the one or more modules / units are stored in the memory 150 and execu...

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Abstract

The invention is applicable to the field of space technology, and provides a satellite attitude determination method, device and terminal equipment. The method includes: acquiring the starry sky background image at the first moment and the starry sky background image at the second moment collected by the spaceborne camera; performing image matching on the starry sky background image at the first moment and the starry sky background image at the second moment , according to the matching result, determine the satellite attitude change value in the time period between the first moment and the second moment; obtain the satellite initial attitude one at the first moment obtained by the navigation system and the satellite initial attitude two at the second moment, according to the satellite The initial attitude 1, the satellite initial attitude 2 and the satellite attitude change value determine the satellite attitude at the second moment. The invention can determine the precise value of the satellite attitude with small error and high precision.

Description

technical field [0001] The invention belongs to the field of space technology, and in particular relates to a satellite attitude determination method, device and terminal equipment. Background technique [0002] In recent years, with the development of space technology, microsatellites (mass in the order of 100kg), nano-satellites (mass in the order of 10kg), pico-satellites or cube satellites (mass in the order of 1kg), flying satellites (mass in the order of 1kg) 100g level) and other micro-satellites are also developing rapidly, and are gradually being applied in various industries to undertake the tasks of large satellites, such as micro-satellite communication constellations, remote sensing constellations, formation satellites, etc., and their huge application value and potential are highly valued by the aerospace industry . The premise of the application and development of microsatellites is high-precision attitude measurement and control. For example, the typical mic...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06T7/73G06K9/46G06K9/62
Inventor 翟优韩东郭希维何鹏谢建华赵慎许葆华刘德亮王红云周海俊
Owner ARMY ENG UNIV OF PLA
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