Aerospace heat-proof material impact damage characteristic type determination method

Abstract

The invention discloses an aerospace heat-proof material impact damage characteristic type determination method. The method comprises the steps: representing a thermal image sequence of pixel points collected by a thermal infrared imager by a three-dimensional matrix; finding out a temperature peak point in the three-dimensional matrix; performing temperature division on the row of the frame number where the temperature peak point is located; performing temperature division on the column of the frame number where the temperature peak point is located; extracting transient thermal responses ina block-by-block and step-by-step manner; using a mean shift algorithm to automatically classify the extracted typical transient thermal responses; using a decomposition multi-objective optimization algorithm based on adaptive weight adjustment to extract representatives of each type of transient thermal response to form a matrix Y; converting the three-dimensional matrix into a two-dimensional matrix, and performing linear transformation on the two-dimensional matrix by utilizing the matrix Y to obtain a two-dimensional image matrix R (x, y); and performing feature extraction on the two-dimensional image matrix R (x, y) by using a one-dimensional Ostu segmentation algorithm. According to the method, the defects of a traditional clustering method in setting the clustering number and selecting the initial clustering center are overcome, and the accuracy of defect feature extraction is guaranteed.

Description

technical field [0001] The invention belongs to the technical field of spacecraft damage detection and evaluation, and more specifically, the invention relates to a method for interpreting impact damage characteristic types of aerospace heat-resistant materials. Background technique [0002] For reusable space vehicles, in order to ensure that no serious aerodynamic thermal damage occurs when entering / re-entering the atmosphere, it is necessary to lay various heat-resistant materials on its surface to ensure the safety of the spacecraft. However, due to the high-speed impact of the fragments of the spacecraft's own coating, or the ultra-high-speed impact of space debris in the earth's orbit, physical damage to the heat-resistant material on its surface will be caused. Especially when a spacecraft is performing missions in a space debris environment, the probability of being hit by tiny space debris is very high. It is worth noting that ultra-high-speed impacts will directly...

AI Technical Summary

Problems solved by technology

However, when reassigning the weight vector, it is necessary to know the distribution of the real solution in advance, and assign different weight vectors according to the density of the solution set, and the adjustment of the weight vector will affect the distribution of the solution set in the space and the objective function Therefore, when adjusting the weight vector, if the adjustment is not enough, the algorithm will not achieve the expected effect, and the ideal uniformly distributed Pareto optimal solution set cannot be obtained; and too much adjustment may cause generation There is no solution in the solution set that can make the decomposed sub-problem tend to a stable minimum value, thus affecting the convergence of the algorithm

Images