Spaceflight linear separation ring structural strength measurement method based on electrical logging technology

Abstract

The invention provides a spaceflight linear separation ring structural strength measurement method based on the electrical logging technology. The method comprises the following steps: firstly, establishing a linear separation ring model, and performing finite element analysis on a stress field of a spaceflight linear separation ring structure to obtain an area in which the stress variation is relatively gentle; then, designing and arranging a electrical logging strain measurement point array in the area in which the stress variation is relatively gentle, carrying out a preloading test to obtain a strain value of the measurement point array, and detecting the design validity of the measurement point array according to the gentleness of the strain value; and performing a formal loading testto obtain structural strain measurement point data, performing calculation according to electrical logging strain measurement point data to obtain the stress field of a concerned area of the spaceflight linear separation ring structure, and evaluating the structural strength. The spaceflight linear separation ring structural strength measurement method provided by the invention is based on the electrical logging technology, the cost is low, the measurement precision is high, the practicability is relatively high, and the problem that the structural strength of a spaceflight linear separationring is difficult to be measured due to the narrow space of the own structure and the complicated curved surface.

Description

technical field [0001] The invention belongs to the field of aerospace and measurement technology, and relates to a method for measuring the strength of an interstage separation device in a launch vehicle, in particular to a method for measuring the structural strength of an aerospace line type separation ring based on electrical measurement technology. Background technique [0002] The stage separation during the flight of the launch vehicle is a very important aspect in the overall design. In the design of interstage separation of launch vehicle at present, the method of destroying the radial direction of the linear separation ring is usually used to ensure the smooth separation of multi-stage sections. [0003] The linear separation ring is generally installed in two adjacent stages of the launch vehicle, and is used to separate the depleted stage of jettisoned propellant, which is a key component of the separation device. When the launch vehicle is separated, radial dam...

AI Technical Summary

Problems solved by technology

[0004] At present, the stress at the opening tip of the separation ring cannot be directly measured by traditional electrical measurement techniques due to the narrow space and complex curved surface of the structure itself, and it is impossible to know the stress distribution form in the dangerous area and evaluate the structural strength. Practical applications bring a certain degree of security risks

Due to the high cost of materials and processing of aerospace structures, it is not advisable to establish a database through a large number of electrical tests

[0005] In addition, although other measurement technologies (such as optical measurement technology represented by infrared imaging technology and digital image correlation technology) can obtain field results such as structural displacement and strain by comparing the optical data before and after the deformation of the test piece, but due to its measurement It is not the best choice due to high cost, sensitivity to the measurement environment, and large full-field measurement error for large test pieces.

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