A star sensor autonomous navigation method based on satellite identification

Abstract

The invention provides a star sensor autonomous navigation method based on satellite identification, and belongs to the technical field of star sensor autonomous navigation methods. The method achieves star-sensor-based fully-autonomous navigation, and provides a carrier with attitude and position information that is high in precision and not emanative along with time. The method includes creating a satellite star map and an integrated star map, and acquires all information and attitude information of fixed stars and satellites according to match of all heavenly bodies with the star maps. According to the acquired fixed star and planet information, high-precision positioning is performed by an improved starlight angular distance process, thus completing transformation into carrier attitude information, and achieving the star-sensor-based fully-autonomous navigation method base in its true sense. The method is advantageous in that 1) the satellite information is adopted in the method so that adaptability and flexibility are good, 2) satellite positioning is adopted in the method so that stability and precision are good, 3) redundancy multi-star resolving is adopted in the method and is anti-interference, and 4) integrated star map matching is adopted in the method, thus increasing information reliability.

Description

technical field

[0001] The invention relates to a star sensor autonomous navigation method based on satellite identification, and belongs to the technical field of star sensor autonomous navigation methods. Background technique

[0002] The star sensors are able to work independently and provide extremely high-precision inertial attitude information that has no cumulative error and does not diverge over time. The inertial attitude information output by the star sensor includes the implicated motion component introduced by the earth's rotation and the error components such as precession, nutation, and pole shift caused by the earth's perturbation, so the inertial attitude output of the star sensor cannot be directly used as a navigation parameter. to solve. In order to eliminate the influence of the above factors, the inertial attitude information output by the star sensor needs to be transformed into attitude information in the navigation coordinate system through coordinat...

Examples

Embodiment Construction

[0027] The present invention will be described in further detail below: the present embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation is provided, but the protection scope of the present invention is not limited to the following examples.

[0028] A kind of star sensor autonomous navigation method based on satellite identification involved in the present embodiment, comprises the following steps:

[0029] Step 1. Inertial attitude determination: the star sensor captures the star S in the field of view i Information, and the created full-sky map Map star Perform matching to obtain the attitude information Att of the current star sensor relative to the inertial coordinate system;

[0030] Step 2. Star information identification: According to the matching attitude information, identify all the star information in the current field of view, obtain the right ascension and declination information, and calculate ...

technical field

[0001] The invention relates to a star sensor autonomous navigation method based on satellite identification, and belongs to the technical field of star sensor autonomous navigation methods. Background technique

[0002] The star sensors are able to work independently and provide extremely high-precision inertial attitude information that has no cumulative error and does not diverge over time. The inertial attitude information output by the star sensor includes the implicated motion component introduced by the earth's rotation and the error components such as precession, nutation, and pole shift caused by the earth's perturbation, so the inertial attitude output of the star sensor cannot be directly used as a navigation parameter. to solve. In order to eliminate the influence of the above factors, the inertial attitude information output by the star sensor needs to be transformed into attitude information in the navigation coordinate system through coordinat...

Examples

Embodiment Construction

[0027] The present invention will be described in further detail below: the present embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation is provided, but the protection scope of the present invention is not limited to the following examples.

[0028] A kind of star sensor autonomous navigation method based on satellite identification involved in the present embodiment, comprises the following steps:

[0029] Step 1. Inertial attitude determination: the star sensor captures the star S in the field of view i Information, and the created full-sky map Map star Perform matching to obtain the attitude information Att of the current star sensor relative to the inertial coordinate system;

[0030] Step 2. Star information identification: According to the matching attitude information, identify all the star information in the current field of view, obtain the right ascension and declination information, and calculate ...