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Measuring method for attitude angular velocity of spacecraft based on star sensor

A star sensor, speed measurement technology, applied in the direction of the device using the optical method, etc., can solve the problems of time delay, accuracy error, etc.

Active Publication Date: 2012-05-02
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0004] The technical problem to be solved by the present invention is: in view of the problem that the measurement method of the spacecraft attitude angular velocity described in the document "Angular velocity determination directly from star tracker measurements" has a delay and the accuracy is greatly affected by the error of the star sensor measurement, a method is proposed. A Measuring Method of Attitude Angular Velocity of Spacecraft Based on Star Sensor

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  • Measuring method for attitude angular velocity of spacecraft based on star sensor
  • Measuring method for attitude angular velocity of spacecraft based on star sensor
  • Measuring method for attitude angular velocity of spacecraft based on star sensor

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Embodiment Construction

[0055] Adopt the present invention to estimate spacecraft attitude angular velocity, concrete steps are as follows:

[0056] The first step is to read the initial time t 0 After the star map is extracted, use the star map recognition algorithm of the full celestial recognition mode to obtain the initial time t 0 The star sensor measurement vector and the corresponding navigation star information.

[0057] In the second step, let t=t 0 +δt, read in the star map at time t, perform star point extraction, sequence star map recognition, number the navigation stars that appear in the star map of the previous frame and the star map of the current frame at the same time, and obtain the star map that appears at time t-δt and t at the same time The total number n of navigation stars in the star map of , and the set Ω1 of corresponding star sensor measurement vector pairs.

[0058] The third step is to initialize the Kalman filter.

[0059] The fourth step is to estimate the attitude...

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Abstract

The invention discloses a measuring method for an attitude angular velocity of a spacecraft based on a star sensor. The invention aims to solve the problem that the precision of a traditional method is seriously influenced by a measurement error of the star sensor. According to the technical scheme, the measuring method comprises the following steps of: reading a star map at an initial moment t0,thereby obtaining a measuring vector of the star sensor at t0 and navigating star information; supposing t=t0+deltat; reading the star map at the moment t; performing star point extraction and sequence star map identification, and numbering navigating stars simultaneously appearing in a previous frame map and a present frame map, thereby obtaining the total number n of the navigating stars simultaneously appearing at the moment of t minus deltat and t and a corresponding set omega1 of measuring vector pairs of the star sensor; initializing a Kalman filter, estimating the attitude angular velocity of the spacecraft and resetting an initial value of the filter; and supposing t=t+deltat, and repeating the steps of reading the star map at the moment t, performing star point extraction and sequence star map identification, numbering navigating stars and obtaining n and omega1. According to the measuring method, the influence of random noise of the measurement of the star sensor on the estimation of the attitude angular velocity can be eliminated and the measuring precision can be increased.

Description

technical field [0001] The invention relates to a method for measuring the attitude angular velocity of a spacecraft in the field of aerospace measurement, in particular to a method for measuring the attitude angular velocity of a spacecraft based on a star sensor. Background technique [0002] Spacecraft attitude control and determination requires known attitude angular velocity information. Usually, gyroscopes are often used as measurement devices for spacecraft angular velocity. However, in recent years, the technology of small satellites has developed rapidly, and due to limitations in weight and power, gyroscope components are often not installed, and the technology of satellite attitude determination using attitude angle sensors has attracted extensive attention. In addition, when the gyroscope fails, it is also necessary to use other means to obtain attitude angular velocity information. [0003] Usually, the attitude angular velocity under the condition of no gyros...

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Application Information

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IPC IPC(8): G01P3/36
Inventor 刘海波杨孟飞杨建坤杨俊才李修建谭吉春贾辉吴子敏王炯琦
Owner NAT UNIV OF DEFENSE TECH
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