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High-precision satellite attitude determination method based on star sensor and gyroscope

A satellite attitude and star sensor technology, which is applied to instruments, measuring angles, measuring devices, etc., can solve problems such as slow filtering convergence speed, inaccurate model errors, filtering convergence and accuracy effects, and achieve a wide range of applications.

Inactive Publication Date: 2010-09-29
BEIHANG UNIV
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Problems solved by technology

However, the convergence speed of predictive filtering is relatively slow, and the inaccuracy of the estimated model error during convergence will affect the convergence and accuracy of filtering.

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  • High-precision satellite attitude determination method based on star sensor and gyroscope
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  • High-precision satellite attitude determination method based on star sensor and gyroscope

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Embodiment Construction

[0021] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0022] The present invention is a high-precision satellite attitude determination method based on starlight and gyroscope. The gyroscope and star sensor are used as attitude sensors, and the idea of ​​predictive filtering is used to estimate the model error of the satellite attitude determination system in real time and compensate in real time. The second-order interpolation filter with higher precision estimates the attitude quaternion of the satellite body coordinate system relative to the inertial coordinate system, and then obtains the satellite attitude through calculation. The process is as follows figure 1 shown, including the following steps:

[0023] Step 1: Establish the state equation of the satellite attitude determination system;

[0024] The attitude dynamics equation and the kinematics equation are used together to describe the attitud...

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Abstract

The present invention discloses a high-precision satellite attitude determination method based on star sensor and gyroscope, which comprises the following steps: step 1. establishing a status equation of a satellite attitude determination system; step 2. establishing a measurement equation of the satellite attitude determination system; step 3. performing an online real-time model error estimation through predictive filtering; and step 4. performing a status estimation on a compensated model through 2-order interpolation filtering to obtain the attitude of a satellite. By applying predictive filtering to performing an online real-time model error estimation and correcting the system model, the invention overcomes the shortcoming existing in the conventional estimation process that error is processed into zero-mean white noise; and in addition, the invention can process any nonlinear system and noise conditions to obtain an estimation result of higher precision and is applicable to thefield of high-precision attitude determination.

Description

technical field [0001] The invention relates to a high-precision satellite attitude determination method based on a star sensor and a gyroscope, and belongs to the technical field of space vehicle high-precision attitude determination. Background technique [0002] The aircraft attitude determination system is an important part of the aircraft attitude control system, and its accuracy and reliability are important guarantees and prerequisites for the long-term normal operation of the aircraft. The system is mainly composed of attitude sensors and corresponding attitude determination algorithms. In order to overcome the influence of the uncertainty of the reference vector on the accuracy of attitude determination, the method of state estimation has been widely used in high-precision attitude determination occasions. [0003] At present, the commonly used method is Extended Kalman Filter (EKF), which has the advantages of fast convergence speed, simple algorithm, and real-time...

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Application Information

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IPC IPC(8): G01C1/00G01C21/00
Inventor 杨静魏明坤
Owner BEIHANG UNIV
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