Spacecraft attitude stability judgement method utilizing RCS (radar cross section)

A discriminative method and a stable technology, applied in the direction of re-radiation, equipment, radio wave reflection/re-radiation, etc., can solve the problems of low recognition rate, fuzzy recognition rate, low operating efficiency, etc., and achieve fast operating speed Effect

Inactive Publication Date: 2012-09-19
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

Using high-order statistics to identify space targets by Ma Junguo et al. , using multiple hypothesis testing as a classifier to identify three types of typical space objects: three-axis stabilized satellites, spin-stabilized satellites and debris, but this method is based on simulation data, and the measured data proves that its recognition rate is low
Xu Xin et al. used wavelet transform to extract features such as RCS mean value, effective rank, and maximum singular valu

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  • Spacecraft attitude stability judgement method utilizing RCS (radar cross section)
  • Spacecraft attitude stability judgement method utilizing RCS (radar cross section)
  • Spacecraft attitude stability judgement method utilizing RCS (radar cross section)

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[0070] First, a discrete wavelet transform is performed on a measurement arc of the spacecraft RCS time series, and then the seven statistical features after the wavelet transform listed above are extracted, including the ratio feature of the maximum value and the mean value, the maximum singular value feature, the variance feature and the four centers Then the seven statistical features are normalized, and finally the attitude stability of the spacecraft is judged by the BP neural network according to the processed feature values.

[0071] Firstly, the RCS wavelet transform features are extracted. Table 1 and Table 2 list the wavelet transform feature values ​​before and after a certain satellite fails.

[0072] Table 1 Eigenvalues ​​of wavelet transform of satellite three-axis stable attitude (reflection angle 70°~80°)

[0073]

[0074] Table 2 Eigenvalues ​​of satellite roll attitude wavelet transform (reflection angle 70°~80°)

[0075]

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Abstract

The invention relates to a spacecraft attitude stability judgement method utilizing RCS. The method is characterized in that the steps are as follows: when the format of a RCS sequence is correct, the RCS sequence is segmented, discrete wavelet transform is then carried out, so that a discrete wavelet transform coefficient is obtained, and wavelet transform characteristics are extracted; the transform characteristics are normalized and then inputted into a three-layer BP (back-propagation) neural network, and when a BP neural network error function E (W) reaches a minimum value, the attitude stability of a spacecraft is judged according to the output value of the BP neural network; 0 in the output value represents attitude stabilization, and 1 in the output value represents attitude rolling. The method can utilize the characteristics to judge the attitude stability of the spacecraft, and measured data prove that the space target attitude stability identification rate of the method is more than 90 percent and that the operation speed is high ( single target identification time is less than 2s).

Description

technical field [0001] The invention belongs to the field of aerospace measurement and control, and relates to a method for judging the attitude stability of a spacecraft by using RCS, which is suitable for judging the attitude stability of a spacecraft by using radar RCS measurement time series. Background technique [0002] Ground-based radar detection is one of the main means of non-cooperative space target surveillance. During the failure of the spacecraft, especially when the downlink telemetry of the satellite is interrupted, the aerospace measurement and control network can no longer complete the analysis and judgment of the satellite failure, and it is necessary to measure the target through non-cooperative measurement means, which is different from the non-cooperative measurement in the normal state of the spacecraft. Data comparison, analysis and judgment of the failure target state, provide technical support for the decision-making of the spacecraft failure rescue...

Claims

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Application Information

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IPC IPC(8): G01S13/88G01S7/40
Inventor 牛威寇鹏苏威
Owner CHINA XIAN SATELLITE CONTROL CENT
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