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Self boundary marking method based on forecast filtering and UPF spacecraft shading device

A technology for predictive filtering and spacecraft, applied in the field of aerospace navigation, can solve the problems of inability to meet high-precision spacecraft, simple algorithm and low accuracy, and inability to improve the accuracy of spacecraft attitude determination, and achieve high filtering accuracy and fast filtering convergence. Effect

Active Publication Date: 2007-12-05
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

The two methods do not establish an accurate gyro model, and the algorithm is simple and the accuracy is low. Therefore, the existing technology cannot meet the requirements of high-precision spacecraft self-calibration, and cannot improve the accuracy of spacecraft attitude determination.

Method used

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  • Self boundary marking method based on forecast filtering and UPF spacecraft shading device

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Embodiment Construction

[0016] As shown in Figure 1, the specific implementation steps of the present invention are as follows:

[0017] 1. Establish the state equation of spacecraft self-calibration based on attitude kinematics:

[0018] (1) Gyro measurement model

[0019] Considering the influence of the gyro error source on the gyro drift error, an accurate gyro model is established, and gyro error sources (such as scale factor error, misalignment error, gyro constant drift, gyro output noise) are built into the gyro model:

[0020] ω g =ω+b+g sf +g ma +n a (1)

[0021] In the formula, ω g is the measured value of the gyro, ω is the true value of the gyro, b is the constant drift of the gyro, g sf is the gyro scale factor error, g ma Gyro misalignment error, n a is the gyro output noise.

[0022] g sf =diag([g sfx g sfy g sfz ]) ω (2)

[0023] g ma = g ...

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Abstract

There are a sort of predictive filtering and the self-demarcation of the UPF spaceflight, it relates to the spaceflight airmanship field. It applies to the self-demarcation of the spaceflight peg-top, especially it relates to a sort of spaceflight self-demarcation method of the inertia / starlight which bases the predictive filtering and the UPF (Unscented Particle Filter) information coalescence, thereby it applies to the navigation determining gesture of the spaceflight. First it establishes the self-demarcation state equations of the spaceflight, and then it makes the gesture information which is observed by the star sensing device to become the measuring equations, finally it adopts the self-demarcation arithmetic which bases the predictive filtering and the UPF spaceflight to estimate and amend the drift error of the peg-top, thereby it obtain the high exact gesture of the spaceflight.

Description

technical field [0001] The invention relates to the technical field of aerospace navigation, and can be applied to self-calibration of spacecraft gyroscopes, in particular to an inertial / starlight combined spacecraft self-calibration method based on prediction filtering and UPF (Unscented Particle Filter, Chinese name is given) information fusion, and further suitable for Attitude determination for spacecraft navigation. Background technique [0002] With the development of the national economy, it is urgent to use wide-scale and large-scale satellites to conduct high-resolution earth observation and monitoring of ocean, environment, agriculture, forestry and other resources. . In order to effectively realize this task, it is necessary to break through the high-precision spacecraft attitude determination technology. [0003] The spacecraft has been flying in space for a long time, and its autonomous attitude determination is very important. Therefore, in addition to variou...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/00G01C21/02G01C21/18
Inventor 房建成徐帆韩晓英全伟宫晓琳钟慧敏
Owner BEIHANG UNIV
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