Reusable spacecraft surface impact damage feature recognition method

Abstract

The invention discloses a reusable spacecraft surface impact damage feature recognition method. The method comprises the steps of representing a thermal image sequence of pixel points collected by a thermal infrared imager by a three-dimensional matrix; finding a temperature peak value in the three-dimensional matrix M; 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 response in a blocking and step-by-step manner; adopting a mean shift algorithm to automatically classify the extracted typical transient thermal responses; adopting a decomposition multi-objective optimization algorithm based ongradient search weight adjustment to select representations 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 change 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 matrixR (x, y) by using a one-dimensional Ostu segmentation algorithm. According to the method, through the uniformly distributed solution sets, the difference and similarity are comprehensively considered,and the defect feature extraction accuracy is improved.

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 identifying impact damage characteristics on the surface of a reusable spacecraft. 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 cau...

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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,

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