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Micro-satellite platform multi-sensor data dynamic fusing system and method

A microsatellite, data dynamic technology, applied in the field of aerospace attitude control, can solve the problem of not being able to give full play to the advantages of dynamic fusion of multi-sensor data and information, and achieve the effect of good engineering application prospects, promotion value, and improved reliability.

Active Publication Date: 2014-10-29
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology

Therefore, the existing technology cannot give full play to the advantages of dynamic fusion of multi-sensor data information

Method used

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  • Micro-satellite platform multi-sensor data dynamic fusing system and method
  • Micro-satellite platform multi-sensor data dynamic fusing system and method
  • Micro-satellite platform multi-sensor data dynamic fusing system and method

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Embodiment Construction

[0019] The specific implementation of a system and method for dynamic data fusion of multiple sensors of a micro-satellite platform provided by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0020] see figure 1 As shown, the present invention provides a plurality of sensors data dynamic fusion system of micro-satellite platform, comprising: a gyroscope 101, a star sensor 102, a sun sensor 103, a magnetometer 104, a 101 is connected to the first sub-filter 112 of the star sensor 102, a second sub-filter 113 connected to the gyroscope 101 and the sun sensor 103 respectively, a second sub-filter 113 connected to the gyroscope 101 and the magnetometer 104 respectively The third sub-filter 114, an information distribution module 111 connected to the first sub-filter 112, the second sub-filter 113 and the third sub-filter 114 respectively, an attitude estimation module 121 connected to the gyroscope 101 , a data fusion modul...

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Abstract

The invention discloses a micro-satellite platform multi-sensor data dynamic fusing system which comprises a spinning top, a star sensor, a sun sensor, a magnetometer and a posture modifying module. The spinning top is connected to a posture predicting module. The posture angle which is outputted by the star sensor, the posture parameter error value which is outputted by the spinning top and a first error state variable estimated value which is outputted by a first information distribution system through a first sub-filter are transmitted to a data fusing module. The sun vector which is outputted by the sun sensor, the posture parameter error value which is outputted by the spinning top and a second error state variable estimated value which is outputted by a second information distribution system through a second sub-filter are transmitted to the data fusing module. The geomagnetism vector which is outputted by the magnetometer, the posture parameter error value which is outputted by the spinning top and a third error state variable estimated value which is outputted by a third information distribution system through a third sub-filter are transmitted to the data fusing module. The data fusing module is connected with the first sub-filter, the second sub-filter and third sub-filter. The posture modifying module is connected with the posture predicting module and the data fusing module.

Description

technical field [0001] The invention relates to the technical field of aerospace attitude control, in particular to a system and method for dynamic fusion of multiple sensor data of a micro-satellite platform. Background technique [0002] The attitude information of the satellite is an important basis for the satellite to complete the mission correctly. With the development of aerospace technology, higher and higher requirements are put forward for the accuracy and reliability of satellite attitude determination. Due to the different benchmarks of various sensors and the different mechanisms of error generation, it is necessary to use multi-sensor data fusion technology to improve the accuracy and reliability of attitude determination. The existing multi-sensor data information fusion technology only fuses the input data information of each sensor, but does not consider the failure of the sensor. Different sensors are available for different mission segments of the satell...

Claims

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Application Information

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IPC IPC(8): B64G1/28
Inventor 万松李东李晓红刘爽吴子轶阳应权
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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