A sensor configuration optimization method for spacecraft folding structure health monitoring

Abstract

The invention discloses a spacecraft-folding-unfolding-structural-health-monitoring-oriented sensor configuration optimization method. The method includes the steps that (1) the alternative sensor data number n is determined, and the final-configuration sensor number m and the sampled mode order N are determined; (2) a structural dynamics-characteristic-equation solving equation is established to obtain a modal matrix; (3) the position of a finite element node serves as an optimization variable d; (4) a fitness function f<1> (d) based on a Fisher information matrix is established; a fitness function f<2> (d) considering the sensor configuration distance uniformity and significant intervals is established; the f<1> (d) and the f<2> (d) are optimized respectively with function maximization as an optimized target, and an optimal fitness function value f<1><*> and a value (The value is defined in the description) are obtained respectively; (5) the f<1><*> and the value (The value is defined in the description) are used in cooperation with the putting reliability degree of sensors on corresponding nodes, and a last fitness function f<4> (d) is established, wherein the f<4> (d) is optimized with function maximization as an optimized target, an optimal fitness function value (The value is defined in the description) and a corresponding optimization variable value (The value is defined in the description) are obtained, and the optimization variable value (The value is defined in the description) is a final sensor configuration position.

Description

technical field [0001] The invention relates to a sensor configuration optimization method oriented to the health monitoring of the deployable structure of the spacecraft, and is especially suitable for the configuration work of sensors that need to consider the effective interval and reliability in the deployable structure of the spacecraft. Background technique [0002] The spacecraft structure will be damaged by various factors in the complex space environment, and the accumulation of damage will inevitably lead to structural damage or performance degradation. In order to ensure the safe operation of the spacecraft structure, Structural Health Monitoring (SHM) technology samples and analyzes the different responses of the structure by embedding or pasting the sensor system in the spacecraft structure, and has obtained the information of the structural state. Changes can be followed by structural health monitoring. Large spacecraft have low-frequency vibration characteris...

AI Technical Summary

Problems solved by technology

However, the reliability of the sensor configuration in the conventional position is not consistent with that of the fold-deployment mechanism

There are a large number of self-rebound and locking devices in the folding mechanism, and the reliability of placing sensors in these positions is lower than that in other positions, but the conventional sensor configuration methods have not noticed the above-mentioned actual problems

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