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Method for determining reconfigurability of satellite control system

A technology for satellite control systems and determination methods, which is applied in the aerospace field, can solve problems such as no reconfigurability measurement methods, no reconfigurability measurement indicators, etc., and achieve the effect of easy construction, simple solution method, and clear physical meaning

Active Publication Date: 2012-11-21
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Reconfigurability measurement is the basis of satellite reconfigurability design, but since satellite reconfigurability design has just started, there is no systematic reconfigurability measurement index, let alone a corresponding reconfigurability measurement method

Method used

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  • Method for determining reconfigurability of satellite control system
  • Method for determining reconfigurability of satellite control system
  • Method for determining reconfigurability of satellite control system

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Embodiment approach

[0044] Construct the function tree of the satellite control system. The root of the function tree is the general function of the satellite control system. The general function includes three functions: attitude control, orbit control and sailboard control. Each function is divided into three parts: measurement function, controller and actuator. Each sub-function can be further divided into lower-level sub-functions according to different implementation methods. The sub-functions serve as the trunk of the function tree, and the components that realize the sub-functions serve as the leaves of the function tree. The implementation method is to connect with the gate or the gate;

[0045] The specific construction steps of the satellite control system function tree are as follows:

[0046]①Aiming at the problem to be analyzed, select the total function (tree root) of the function tree. When analyzing all the functions of the satellite control system, the root of the function tree ...

Embodiment

[0092] The present invention is described in detail by taking the attitude control function of a typical high-orbit satellite when jet control is used in orbit as an example. In engineering practice, the satellite control system has a variety of components, so the function tree is also relatively complex. In order to illustrate the simplicity of the specific implementation, the composition of the satellite control system is simplified here, and the composition is as follows:

[0093] ① 2-way earth sensor (ES master and ES backup): under normal circumstances, one ES works, and the other cold backup. If necessary, two ESs can also work at the same time.

[0094] ② 4-way sun sensor (SS): including pitch SS master, roll SS master, pitch SS backup, roll SS backup. The pitch SS master and pitch SS backup are mutually active and backup, and the rolling SS master and rolling SS backup are mutually active and backup.

[0095] ③Propulsion system: The propulsion system includes multiple...

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Abstract

The invention discloses a method for determining the reconfigurability of a satellite control system. The method comprises the following steps of: (1) constructing a satellite control system function tree and connecting the different levels of the function tree by means of AND Gate or OR Gate according to the function implementation mode of the satellite control system; (2) according to the AND / OR relationship between different levels of the function tree, determining the cut-set family C of the function tree by using the descending method or the ascending method, wherein the elements of the cut-set family are cut-sets and the cut-sets are component sets for implementing the functions of the satellite control system; (3) performing absorption treatment on the cut-set family C determined in the step (2) to obtain the minimum cut-set family Cmin of the function tree, wherein the elements of the minimum cut-set family Cmin are minimum cut-sets cmin and the minimum cut-sets cmini are the sets of least components required for implementing the functions of the satellite control system; (4) performing failure mode effect analysis (FMEA) on the satellite control system to determine the failure mode, failure occurrence probability and failure severity of the satellite control system; (5) determining the reconfigurable degree (Gamma-i) of the failure mode i; and (6) determining the reconfigurable rate of the satellite control system.

Description

technical field [0001] The invention belongs to the field of aerospace and relates to a method for determining the reconfigurability of a satellite control system based on a function tree. Background technique [0002] With the development of science and technology, satellites have played an irreplaceable role in various fields such as national defense, military, communications, and meteorology. In order to cope with various failures that may occur in satellites in orbit and improve the quality of operation, it is necessary to ensure that effective measures are taken in time to minimize the impact of failures after failures occur. This is to overcome the inherent reliability of products at the system level and improve the reliability of satellite operations. Effective means of sex and life extension. Since satellites cannot be maintained on-orbit, generally only reconfiguration can be used to restore system functions. Therefore, in order to improve the fault handling capabi...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 刘成瑞王南华王大轶何英姿张国琪
Owner BEIJING INST OF CONTROL ENG
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