Star light refraction satellite autonomous navigation method based on single star sensor

A star sensor, star light refraction technology, applied in the field of star light refraction satellite autonomous navigation, can solve problems such as affecting navigation accuracy

Active Publication Date: 2014-03-05
HARBIN ENG UNIV
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Problems solved by technology

The installation angle of the star sensor determines the number of refracting stars observed by the satellite in one period, which affects the accuracy of navigation.

Method used

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  • Star light refraction satellite autonomous navigation method based on single star sensor
  • Star light refraction satellite autonomous navigation method based on single star sensor
  • Star light refraction satellite autonomous navigation method based on single star sensor

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Embodiment Construction

[0046] The present invention will be further described in detail with reference to the accompanying drawings and embodiments. The invention is a self-navigation method for a starlight refraction satellite of a single star sensor, comprising the following steps:

[0047] Step 1: Install the star sensor on the satellite according to the best installation angle;

[0048] In satellite autonomous navigation, the refraction height is generally selected from 20km to 50km according to the thickness of the stratosphere, that is, figure 1 In ha=20km, hb=50km; assuming that the star sensor is installed in the satellite orbit plane, the vector of starlight is s, then by figure 1 The starlight that meets the equation (1) can be received by the satellite after being refracted. A star whose light has not been refracted is a normal star, and a star whose light has been refracted is a refracting star.

[0049] α - θ R ...

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Abstract

The invention discloses a star light refraction satellite autonomous navigation method based on a single star sensor. The star light refraction satellite autonomous navigation method comprises the following steps: 1, installing the star sensor on a satellite according to an optimal installation angle; 2, after the star sensor shoots a star map, identifying normal stars in the star map by using a triangle algorithm; 3, calculating an optical axis direction and a satellite gesture of the star sensor by using the identified star sensors; 4, selecting a star from the star map according to the optical axis direction of the star sensor to generate a stimulation refraction star map; 5, identifying a refraction star by using the stimulation refraction star map, and calculating a star light refraction angle according to an identification result; and 6, substituting the star light refraction angle into a system model, and obtaining navigation information of the satellite by using an optimum estimation method by a spaceborne computer. According to the star light refraction satellite autonomous navigation method, the precision of autonomous navigation of a star light refraction satellite is improved, and the design cost is lowered.

Description

technical field [0001] The invention relates to an autonomous navigation method for a starlight refraction satellite based on a single-star sensor, and belongs to the technical field of satellite autonomous navigation and star map recognition. Background technique [0002] The method of indirect sensitivity to the horizon due to starlight refraction is a low-cost, high-precision autonomous navigation method. The United States can trace back to the 1960s the research work on the autonomous navigation of the starlight refraction method. In the process of implementing the Apollo program, researches were carried out on the scheme of realizing autonomous navigation by using celestial occultation, refraction of starlight in the atmosphere, and attenuation of starlight when passing through the atmosphere. Jointly invested by the Research Projects Agency, the Draper Laboratory of the Massachusetts Institute of Technology conducted research and demonstration on the starlight refract...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
CPCG01C21/20G01C21/24
Inventor 钱华明孙龙蔡佳楠黄蔚王大伟徐健雄
Owner HARBIN ENG UNIV
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