CN115656413A - Method for processing ultrasonic measurement of dynamic burning rate data of solid propellant - Google Patents
Method for processing ultrasonic measurement of dynamic burning rate data of solid propellant Download PDFInfo
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- 238000003672 processing method Methods 0.000 claims abstract description 6
- 238000002485 combustion reaction Methods 0.000 claims description 13
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Abstract
The invention belongs to the technical field of aerospace and discloses a method for processing dynamic burning rate data of a solid propellant measured by ultrasonic waves. Aiming at the data processing of measuring the dynamic burning rate of the solid propellant by an ultrasonic pulse echo method, an automatic data processing method combined with an image method is provided, the manual participation degree is low, and the processing efficiency is high; the problems that a large amount of manual judgment is needed and time consumption is long in data processing in the prior art are solved, and guarantee is provided for practicability of ultrasonic measurement of the dynamic burning rate of the solid propellant. The invention has the advantages that the manual judgment is simple, the precision is not influenced, and the automatic processing is easy; according to the method, the efficiency and the accuracy of processing the dynamic burning rate data measured by the ultrasonic pulse echo method can be improved, and the engineering application is facilitated.
Description
Technical Field
The invention belongs to the technical field of aerospace, and relates to a method for processing measurement data of the burning rate of a solid propellant, in particular to a method for quickly obtaining the dynamic burning rate of the propellant by using echo data when the dynamic burning rate of the solid propellant is measured by using an ultrasonic pulse echo method.
Background
The burning rate of solid propellants is an important parameter in the design of solid rocket engines. The ultrasonic pulse echo method is one of important foreign means for researching the dynamic combustion performance of the solid propellant, and has the advantage of being capable of monitoring the combustion condition of the propellant during the working of an engine in real time.
The ultrasonic pulse echo method is to measure the thickness of a propagation medium by utilizing the characteristic that when ultrasonic waves propagate in different media, the ultrasonic waves are reflected when meeting material interfaces with different acoustic impedances; the distance information of the sound wave reflecting surface can be obtained by measuring the time difference between the transmitted wave and the echo receiving time of the ultrasonic wave and according to the wave speed of the sound wave in the medium. For example, when the ultrasonic probe is mounted on the outer side of the engine case, the ultrasonic probe emits ultrasonic waves at a certain frequency to the propellant charge inside; the ultrasonic waves penetrate through the shell and the solid propellant and are reflected at a propellant/gas interface, and the thickness of the propellant can be calculated after the reflected waves are received by the probe again; by measuring the thickness of the propellant at different times in real time, the burning rate can be obtained.
However, in the working process of the engine, the combustion surface of the solid propellant is not a smooth surface, the attenuation effect of the solid propellant on ultrasonic signals is strong, and meanwhile, the solid rocket engine vibrates strongly, so that a plurality of factors are superposed together, so that the echo waveform received by the probe is relatively scattered, a plurality of wave crests and wave troughs exist, and it is difficult to judge which wave crest or wave trough represents the combustion surface, so that the combustion surface thickness data cannot be directly obtained, and the echo data must be processed.
At present, when ultrasonic pulse echo data is processed, for an ideal condition that an echo peak value is clear, a method of manually and directly reading peak value data is generally adopted to determine a reflection interface; in the document "application of ultrasonic real-time measurement technology to solid rocket engines" (Sun Dechuan et al, war institute, 37, 11 th, 1969-1975, 2016, 11 months), the peak position is directly determined as a combustion surface. For the condition that the echo peak values are relatively disordered in practical application, generally, the echo waveforms acquired at different moments are represented by gray values, and then data (a gray line) represented by the gray values are arranged according to a time sequence to obtain a two-dimensional image; therefore, the moving burning surface is represented as a diagonal stripe in the image, and is easy to identify manually; and then, obtaining the position data of the burning surface on the oblique stripes by adopting an artificial interpretation method (application research of ultrasonic measurement of burning speed of the solid propellant, ronity and Yokou, master academic paper, university of general technology, 5 months in 2020), "ultrasonic method test of burning speed of the solid rocket engine, wangkai and the like, chinese test, no. 43, no. 8, pages 19 to 23 and 8 months in 2017).
The main disadvantages of these combustion surface echo processing methods are that it is necessary to manually judge the waveform at each measurement time to determine the combustion surface position, and particularly, for the data with disordered waveforms, the discrimination criteria are uncertain, and the processing efficiency is low. Therefore, the effective data points given finally in the literature are all sparse, the time interval is large, and the processing precision is poor.
Disclosure of Invention
The invention provides an automatic data processing method combined with images aiming at data processing of measuring dynamic burning rate of a solid propellant by an ultrasonic pulse echo method, which is easy to realize by a computer, low in manual participation, high in processing efficiency and free of data omission; the problems that a large amount of manual judgment is needed and time consumption is long in data processing in the prior art are solved, and guarantee is provided for practicability of ultrasonic measurement of the dynamic burning rate of the solid propellant.
The technical scheme of the invention is as follows:
a method for processing ultrasonic measurement solid propellant dynamic burning rate data comprises the following steps:
(1) The original data collected by the ultrasonic pulse echo method is a one-dimensional array with equal length corresponding to different collecting time, and t is used y Representing the acquisition time, t x Representing the position of data in a one-dimensional array, and u represents the value of an array element; with t x Is the abscissa, t y The longitudinal coordinate is used, and u is expressed by gray scale, so that a series of collected echo data can be converted into a two-dimensional gray scale image;
(2) Observing the two-dimensional gray image by naked eyes, judging the oblique stripes representing the dynamic burning surface, wherein if the wave crests represent the burning surface, the stripes are light-colored stripes, and if the wave troughs represent the burning surface, the stripes are dark-colored stripes; then marking three points at two ends and middle part of the oblique stripe, recording their coordinate values, and determining quadratic curve t passing through these three points according to the coordinate values x ＝at y 2 +bt y + c, wherein a, b, c are constants;
(3) Measuring the pixel number d occupied by the transverse width of the oblique stripes in the image; then, taking the vertical coordinate intervals of two end points of the stripes as a data processing range, and sequentially processing the one-dimensional arrays of the echoes, wherein the processing method is as the step (4);
(4) Let the collection time of the ith array be t yi First, t is yi Substituting the value into the quadratic curve in the step (2) to obtain the corresponding element position t in the ith one-dimensional array xi (ii) a Then searching the one-dimensional array for [ t ] xi -d,t xi +d]The extreme value of u in the interval is marked as t ri ；
(5) Aiming at all discrete points (t) obtained by processing according to the step (4) in the vertical coordinate interval of two end points of the oblique stripes ri ,t yi ) Performing polynomial fitting to obtain a fitting curve t x ＝c 3 t y 3 +c 2 t y 2 +c 1 t y +c 0 ；
(6) Multiplying the polynomial in step (5) by v 0 /2，v 0 And (3) representing the sound velocity in the propellant, namely obtaining the variation relation of the thickness of the propellant along with the acquisition time: l (t) y )＝(c 3 t y 3 +c 2 t y 2 +c 1 t y +c 0 )v 0 /2；
(7) The relation in the step (6) is paired with t y Taking a derivative andtaking the inverse number to obtain the burning rate r and the time t y Relation r = - (3 c) 3 t y 2 +2c 2 t y +c 1 )v 0 /2。
The invention has the advantages that: the data processing method is simple and easy to realize automatic processing by a computer; test data are not omitted, and the data fitting precision is high; according to the method, the efficiency and the accuracy of measuring the dynamic burning rate data by the ultrasonic pulse echo method can be improved, and engineering application is facilitated.
Drawings
FIG. 1 is ultrasonic data graphically representing the dynamic recession of the combustion face of a solid propellant in example 1.
In the figure: A. c represents two end points of the oblique stripes of the combustion surface; b, oblique stripe middle point; d, stripe width; t is t x Is the echo return time (unit 1/60 microsecond), t y Is the acquisition time (unit 0.01 second).
Figure 2 is all the discrete points obtained by the treatment in example 1.
In the figure: t is t x Is the echo return time (unit 1/60 microsecond), t y Is the acquisition time (unit 0.01 second).
Detailed Description
The following detailed description of the invention refers to the accompanying drawings and accompanying claims.
Example 1: ultrasonic measurement data of solid propellant test blocks combusted in a closed combustor are processed.
(1) Representing the ultrasonic measurement data as a two-dimensional grayscale image with an ordinate t y Represents the acquisition time in units of 0.01 seconds, abscissa t x The echo return time is expressed in units of 1/60 microsecond.
(2) Observing the two-dimensional gray image, judging that a second dark oblique stripe represents a dynamic burning surface, marking three points A (1292, 674), B (2118, 450) and C (2913, 185) at the two ends and the middle of the oblique stripe, wherein the coordinate values are in brackets; determining a quadratic curve passing through A, B and C according to the coordinate values
t x ＝-0.00140593t y 2 –2.10723t y +3350.96,t y ∈[185,674]；
(3) Measuring the approximate pixel number occupied by the horizontal width of the diagonal stripes in the image to be 40;
(4) The ordinate interval [185,674 ] of two end points A, C of the stripe]In the range of 1, the values are sequentially substituted into a quadratic curve t x ＝-0.00140593t y 2 -2.10723t y +3350.96, to determine the corresponding t xi (ii) a Then searching the one-dimensional array for [ t ] xi -40,t xi +40]Minimum value of echo signal in interval, mark its position as t ri ；
(5) All discrete points (t) ri ,t yi ) And (3) displaying in a two-dimensional coordinate system, and performing polynomial fitting on the points to obtain a curve:
t x ＝1.62964×10 -6 t y 3 -3.58677×10 -3 t y 2 -1.21838t y +3240.71,t y ∈[185,674]；
will t x 、t y All units of (d) are converted to seconds, the curve becomes:
t x ＝2.71607×10 -4 t y 3 -5.97795×10 -3 t y 2 -0.0203063t y +0.540118,t y ∈[1.85,6.74]；
(6) The sound velocity of the propellant in the test is 1570m/s; since propellant thickness is commonly used in millimeter units, multiplying the polynomial in step (5) by 1570000mm/s and dividing by 2 yields the propellant thickness (millimeters) as a function of acquisition time (seconds):
L＝0.0213211t y 3 -0.469269t y 2 -1.59405t y +42.3993,t y ∈[1.85,6.74]；
(7) The relation in the step (6) is paired with t y Obtaining the burning rate r (mm/s) and the time t by taking the derivative and taking the inverse number y (s) relationship:
r＝-0.0639633t y 2 +0.938538t y +1.59405,t y ∈[1.85,6.74]。
490 pieces of acquired data are processed by the computer in one step in the embodiment, the whole processing time is within 3 minutes, data are not omitted, the data fitting precision is high, and the high efficiency of data processing is realized.
Claims (1)
1. A method for processing ultrasonic wave measured solid propellant dynamic burning rate data is characterized by comprising the following steps:
(1) The original data acquired by the ultrasonic pulse echo method is a one-dimensional array with equal length corresponding to different acquisition time, and t is used y Denotes the acquisition time, t x Representing the position of data in the one-dimensional array, and u represents the value of an array element; with t x Is the abscissa, t y The longitudinal coordinate is used, the u is expressed by gray scale, and a series of collected echo data are converted into a two-dimensional gray scale image;
(2) Observing the two-dimensional gray image, and judging oblique stripes representing the dynamic combustion surface, wherein if the wave crests represent the combustion surface, the stripes are light-colored stripes, and if the wave troughs represent the combustion surface, the stripes are dark-colored stripes; then marking three points on two end points and the middle part of the oblique stripe, recording the coordinate values of the three points, and determining a quadratic curve t passing through the three points according to the coordinate values x ＝at y 2 +bt y + c, wherein a, b, c are constants;
(3) Measuring the number d of pixels occupied by the transverse width of the oblique stripes in the two-dimensional gray image; then, taking the vertical coordinate interval of two end points of the oblique stripes as a data processing range, and sequentially processing the one-dimensional array of the echoes, wherein the processing method comprises the following steps:
let the collection time of the ith one-dimensional array be t yi First, t is yi Substituting the value into the quadratic curve in the step (2) to obtain the corresponding element position t in the ith one-dimensional array xi (ii) a Then searching the one-dimensional array for [ t ] xi -d,t xi +d]The extreme value of u in the interval is marked as t ri ；
(4) Aiming at all discrete points (t) obtained by processing in the step (3) in the vertical coordinate interval of two end points of the oblique stripes ri ,t yi ) Performing polynomial fitting to obtain a fitting curve t x ＝c 3 t y 3 +c 2 t y 2 +c 1 t y +c 0 ；
(5) Multiplying the polynomial in step (4) by v 0 /2，v 0 And (3) representing the sound velocity in the propellant, namely obtaining the variation relation of the thickness of the propellant along with the acquisition time: l (t) y )＝(c 3 t y 3 +c 2 t y 2 +c 1 t y +c 0 )v 0 2, for t y The derivative is calculated and the inverse number is taken, and the burning speed r and the time t are obtained y Relationship r = - (3 c) 3 t y 2 +2c 2 t y +c 1 )v 0 /2。
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| CN118519157A (en) * | 2024-06-13 | 2024-08-20 | 中北大学 | Propellant burning rate measuring method and system based on multichannel ultrasonic waves |
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Cited By (2)
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