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Satellite steady-state availability calculation method

A calculation method and satellite technology, applied in special data processing applications, geometric CAD, probabilistic CAD, etc., can solve the problems of usability requirements without corresponding indicators, unable to analyze and verify, etc., to facilitate statistical data and analysis and calculation, reduce difficulty, and improve The effect of actual operability

Pending Publication Date: 2021-02-26
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

This method solves the problem that there is no corresponding indicator and cannot be analyzed and verified for the usability requirements proposed by users of export models.

Method used

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  • Satellite steady-state availability calculation method
  • Satellite steady-state availability calculation method
  • Satellite steady-state availability calculation method

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Embodiment

[0071] figure 1 Shown is the method flowchart of the present invention, a kind of satellite steady-state availability calculation method provided by the present invention, concrete steps are as follows:

[0072] (1) In the satellite on-orbit safety mode, select a safety mode in turn as the top event for fault tree analysis, and analyze the bottom event until the probability of its occurrence can be counted;

[0073] (2) According to the fault tree analysis results, the probability of occurrence of each bottom event is counted, and the probability of occurrence of the top event is calculated P i , that is, the probability that the satellite enters the safe mode in orbit. If there is not enough bottom event statistical data, the failure rate data in reliability prediction can be used to calculate its occurrence probability;

[0074] (3) Calculate the occurrence probability of all security modes in turn, and calculate the relative occurrence probability P of each security mode ...

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PUM

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Abstract

The invention discloses a satellite steady-state availability calculation method, and the method comprises the steps: calculating the probability that a satellite enters each safety mode according tothe types of in-orbit safety modes of the satellite and the statistics of a fault tree analysis result of each safety mode and the occurrence probability of a bottom event to acquire relative occurrence probability that the satellite enters each safety mode; and counting the average duration of entering each safety mode and the average interval time of entering the safety mode for two times of similar models on the orbit; multiplying the relative occurrence probabilities of all the security modes by the average duration and then accumulating to obtain the average interruption time when the satellite enters the security mode once; and subtracting the average interruption time of the satellite entering the primary safety mode from the interval time of the average twice-advancing safety mode,and then dividing the average interruption time by the interval time of the average twice-advancing safety mode to obtain the steady-state availability of the satellite.

Description

technical field [0001] The invention relates to a method for calculating satellite steady-state availability, and belongs to the technical field of satellite overall design. Background technique [0002] For satellites, they are generally not repairable in orbit and are non-repairable products. Non-repairable products generally emphasize reliability and ignore usability. In recent years, with the increase of foreign export models, foreign exchanges (especially the European Space Agency) have found that foreign countries (especially the European Space Agency) pay more attention to the availability of satellites, and pay more attention to the user experience of satellites than domestic ones. However, domestic satellites currently do not have usability indicators and corresponding calculation methods, which have encountered many problems when undertaking export models. [0003] Availability refers to the extent to which a product is in a working state or usable state when it n...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15
CPCG06F30/15G06F2111/08Y02D30/70
Inventor 王世清
Owner AEROSPACE DONGFANGHONG SATELLITE
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