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Posture determination method of star sensor

A technology of star sensor and determination method, which is applied in the direction of integrated navigator, etc., and can solve problems such as limited application

Inactive Publication Date: 2014-07-23
HARBIN ENG UNIV
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Problems solved by technology

However, the grid algorithm requires that the number of observed stars in the field of view is not less than six, which limits the application of the algorithm in small field of view and low magnitude star sensors.

Method used

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  • Posture determination method of star sensor
  • Posture determination method of star sensor
  • Posture determination method of star sensor

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Embodiment Construction

[0050] The present invention will be described in detail below in conjunction with accompanying drawing:

[0051] The present invention is a method for determining the attitude of a star sensor, comprising the following steps:

[0052] Step 1: Use the Pyramid algorithm to identify the star map at the initial moment and calculate the attitude of the carrier;

[0053] For the specific implementation of the Pyramid algorithm, please refer to the document "Lost-in-space Pyramid algorithm for robust star pattern recognition".

[0054] Step 2: Use the attitude of the carrier and the output information of the gyroscope to calculate the boresight direction of the star sensor at the current moment, and use the obtained boresight direction to select stars from the star catalog to generate a simulated star map;

[0055] Specifically, the implementation steps are:

[0056] Step A: After obtaining the initial attitude of the carrier, calculate the attitude at the current moment according...

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Abstract

The invention discloses a posture determination method of a star sensor. The posture determination method of the star sensor comprises the following steps: recognizing a star map at the initial time, and calculating the posture of a carrier; calculating the visual axis direction of the star sensor at the current time by virtue of the posture of the carrier and output information of a gyroscope, and selecting a star from a star catalogue by virtue of the obtained view axis direction so as to generate a simulated star map; combining the simulated star map and a photographed star map of the star sensor at the current time so as to form a novel star map; selecting a reference star from a real view field of the novel star map, and recognizing by a grid algorithm; and recognizing the star map successfully if the number of star points recognized successfully is greater than 2, and calculating the posture of the carrier, or running again. The method for expanding the view field is applied to the grid algorithm, so that the number of fixed stars in the view field increases, and the restriction that the grid algorithm cannot be applied to sensors of small view fields, low stars and the like is broken through, so that the star map recognition process of the star sensor has high recognition rate.

Description

technical field [0001] The invention belongs to the field of attitude determination of a star sensor, in particular to a method for determining the attitude of a star sensor based on a grid algorithm of an expanded field of view. Background technique [0002] Accurate attitude information is the basis for spacecraft to complete space missions. There are many measurement devices that can provide attitude information, but the star sensor is the most accurate and widely used. The attitude determination process of the star sensor is divided into four steps: starry sky imaging, star point extraction, star map recognition and attitude calculation. Among them, star map recognition is the decisive stage of star sensor attitude determination. [0003] With the development of star sensors, many star map recognition algorithms have emerged, which can be roughly divided into two types. The first type is the subgraph isomorphism algorithm, which regards the observed star map as a subg...

Claims

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 钱华明孙龙蔡佳楠黄蔚
Owner HARBIN ENG UNIV
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