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Star tracking method of star sensor under high dynamic state

A star sensor and star tracking technology, applied in the field of measurement, can solve the problems of increasing the calculation amount of the processor and reducing the data update rate.

Inactive Publication Date: 2009-05-20
HARBIN INST OF TECH
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Problems solved by technology

This increases the calculation load of the processor, thereby reducing the data update rate

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  • Star tracking method of star sensor under high dynamic state
  • Star tracking method of star sensor under high dynamic state
  • Star tracking method of star sensor under high dynamic state

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Embodiment Construction

[0029] The present invention will be further described below in conjunction with accompanying drawing and specific embodiment:

[0030]The star sensor system in this embodiment consists of a probe part and a data processor part. The probe part includes a hood, an optical lens, an image sensor, a supporting circuit, and an interface with a data processor; the data processor includes a computer, a memory, and an external interface.

[0031] combine Figure 6 and Figure 7 , the working principle of the star sensor is: the star is imaged on the image plane of the star sensor (such as CCD or APS) through the optical lens of the star sensor, and the imaging circuit converts the electrical signal of the star in the image plane into a complete star map, And save it in the memory; the star image extraction software reads the star map data in the memory, and extracts the star image coordinates from the star map; , these star image coordinates are identified (if the star sensor has p...

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Abstract

The invention provides a method for tracking a highly dynamic star with a star sensor. Firstly, according to ideal star image coordinate information predicted by a former frame of the star sensor, the corresponding star image coordinates are picked up from the present frame star chart, and by utilizing the star image coordinates picked up from the present frame star chart and celestial coordinates corresponding to the star images, the posture information of the present frame of the star sensor is worked out. The invention provides a method only adopting the autonomous posture of the star sensor to work out the actual output posture of the star sensor according to the predicted posture so as to meet the control requirements of high precision and non-spinning top when an aircraft maneuvers at big angular speed. With a star tracking algorithm provided by the method, before picking up the star image coordinates, the ideal star image centers are predicted according to the former frame, and the actual star image positions are picked up by referring to the ideal star image centers; the ideal star image coordinates of the next frame of the known star in the visual field are predicted and used as a basis for picking up the star image coordinates from the next frame star chart, so the requirements on real time and reliability when the aircraft maneuvering at the big angular speed only adopts the star sensor to navigate are met.

Description

(1) Technical field [0001] The invention relates to a measurement technique, in particular to a technique for measuring the attitude by only using a star sensor when a detection aircraft maneuvers at a high angular velocity. (2) Background technology [0002] The star sensor is a high-precision aircraft attitude sensitive measuring instrument. It determines the attitude of the aircraft by detecting stars in different positions on the celestial sphere, and provides the three-axis attitude of the spacecraft relative to the inertial coordinate system. At present, many scholars have proposed or improved various global star map recognition algorithms to improve the star sensor data update rate. Although these algorithms have improved the attitude update rate to some extent, but before the recognition of the global star map, the star image coordinates must be extracted from the entire star map, and the extracted star image coordinates account for the entire global star map recogni...

Claims

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Application Information

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IPC IPC(8): G01C21/02B64G3/00B64G1/36
Inventor 李葆华王常虹刘国梁刘睿
Owner HARBIN INST OF TECH
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