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Method for estimating pseudo rate of spacecraft based on attitude measurement information of star sensors and angular momentum measurement information of flywheels

A technology for measuring information and star sensors, which can be used in the observation of aerospace vehicles, measurement devices, linear/angular velocity measurement, etc., and can solve the problem of low accuracy of pseudo-rate estimation

Inactive Publication Date: 2010-05-12
HARBIN INST OF TECH
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Problems solved by technology

[0005] The present invention aims to solve the problem of low pseudo-velocity estimation accuracy in existing methods for estimating the pseudo-velocity of spacecraft, thereby providing a method for estimating the pseudo-velocity of spacecraft based on the attitude measurement information of the star sensor and the angular momentum measurement information of the flywheel

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  • Method for estimating pseudo rate of spacecraft based on attitude measurement information of star sensors and angular momentum measurement information of flywheels
  • Method for estimating pseudo rate of spacecraft based on attitude measurement information of star sensors and angular momentum measurement information of flywheels
  • Method for estimating pseudo rate of spacecraft based on attitude measurement information of star sensors and angular momentum measurement information of flywheels

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specific Embodiment approach 1

[0034] Specific implementation mode 1. Combination figure 1 Illustrate this specific embodiment, the method for estimating the pseudo-velocity of the spacecraft based on the attitude measurement information of the star sensor and the angular momentum measurement information of the flywheel, it is completed by the following steps:

[0035] Step 1. Use the star sensor to measure the attitude of the spacecraft, and perform angular difference on the measured attitude of the spacecraft to obtain the attitude differential angular velocity ω of the spacecraft sk ;

[0036] Step 2, collect the angular momentum information of the flywheel, and obtain the derivative of the pseudo-rate of the spacecraft according to the obtained angular momentum information in combination with the attitude dynamic equation of the spacecraft;

[0037] Step 3, according to the derivative of the pseudo-velocity of the spacecraft obtained in step 2, the pseudo-velocity of the spacecraft is predicted in one ...

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Abstract

The invention relates to a method for estimating the pseudo rate of a spacecraft based on attitude measurement information of star sensors and angular momentum measurement information of flywheels, solving the problem of low pseudo rate estimation accuracy in the prior art. The method is as follows: adopting the star sensors to measure the attitude of the spacecraft and obtaining the differential attitude angular velocity of the spacecraft after carrying out angle difference; collecting the angular momentum information of the flywheels and obtaining the differential coefficient of the pseudo rate of the spacecraft according to the obtained angular momentum information in combination with the attitude dynamics equation of the spacecraft; carrying out one-step prediction on the pseudo rate of the spacecraft; after setting the gain coefficient of the filter, using the differential attitude angular velocity as the measured value of the pseudo rate of the spacecraft and updating the filter of the pseudo rate of the spacecraft to obtain the estimation value of the pseudo rate of the spacecraft; and adjusting the gain coefficient value of the filter according to the estimation value, thereby adjusting the estimation value of the pseudo rate of the spacecraft and finishing estimation of the pseudo rate of the spacecraft. The method is suitable for the estimation occasions of the pseudo rate of the spacecraft.

Description

technical field [0001] The invention relates to a method for estimating the pseudo velocity of a spacecraft. Background technique [0002] The spacecraft pseudo-rate refers to the attitude angular velocity of the spacecraft obtained by using the information of other attitude components when there is no gyro on the spacecraft or the gyro fails. There are generally two methods for obtaining the pseudo-velocity of the spacecraft: [0003] The first type of method is to use only the measurement information of the attitude sensor to calculate the pseudo-rate, such as using the measurement information of the sun sensor to perform simple attitude filtering, and then perform attitude difference to obtain the pseudo-rate; or use the measurement information of the star sensor, Use the principle of quaternion multiplication to get the pseudo rate. There are two problems with this type of method. One is that the measurement accuracy is not high, and the other is that during the attitu...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01P3/00B64G3/00
Inventor 耿云海卢伟陈雪芹
Owner HARBIN INST OF TECH
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