Three-dimensional burning rate characterization method and device for a solid-liquid rocket engine

Abstract

The present invention provides a method and device for three-dimensional burn rate characterization of a solid-liquid rocket engine, relating to the technical field of aerospace, including: obtaining CT scan image pairs of each cross-sectional slice along the axis of the solid-liquid rocket engine; determining the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center based on the CT scan image pairs; determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine based on the CT scan image pairs and the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center; determining the three-dimensional burn rate distribution law of the solid-liquid rocket engine based on the characteristic points and the working duration of the solid-liquid rocket engine, solving the technical problem that it is difficult to determine the three-dimensional burn rate of the complex grain shape of the solid-liquid rocket engine in the prior art.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace, and in particular, to a method and device for characterizing the three-dimensional burning rate of a solid-liquid rocket engine. Background Art

[0002] The solid-liquid rocket engine has the advantages of adjustable thrust, multiple start-stop operations, safety and reliability, environmental protection, and high grain stability, and has good economy, and has broad application prospects in the fields of small launch vehicles, sounding rockets, suborbital aircraft, manned spacecraft, etc. The solid-liquid rocket engine is generally a chemical rocket engine that uses a liquid oxidizer and a solid fuel. It mixes and burns the liquid oxidizer injected into the combustion chamber with the solid fuel. The grain is decomposed by heat and further burns and releases heat with the oxidizer. The high-temperature combustion products are accelerated and ejected through a Laval nozzle to generate thrust. Since it is difficult to measure the three-dimensional burning rate distribution law of complex grain shapes, it is the key to the internal ballistics research of the engine to be able to characterize the three-dimensional burning rate spatial distribution law of complex grain shapes.

[0003] The solid fuel burning rate of a solid-liquid rocket engine is an important index for characterizing the engine's working performance. It is closely related to the propellant formula, oxidizer flow rate, etc. Therefore, effectively and accurately characterizing the burning rate of the solid fuel is a necessary step in experimental measurement. The existing measurement techniques include the target wire method, the acoustic emission method, the ultrasonic dynamic burning rate method, and the start-stop point averaging method. The commonly used experimental burning rate measurement method is to conduct a short-term hot test, weigh the grain mass before and after the hot test, and obtain the average burning rate. However, the target wire method and the acoustic emission method can only measure the burning rate at a certain working pressure, and are affected by factors such as the combustion chamber pressure, and the pressure upper limit is low, resulting in a low measurement accuracy; while the commonly used start-stop point averaging method has measurement errors and cannot measure the three-dimensional burning rate spatial distribution law of complex grain shapes.

[0004] In view of the above problems, no effective solution has been proposed yet. Summary of the Invention

[0005] In view of this, the purpose of the present invention is to provide a method and device for characterizing the three-dimensional burning rate of a solid-liquid rocket engine, so as to alleviate the technical problem that it is difficult to determine the three-dimensional burning rate of the complex grain shape of the solid-liquid rocket engine in the prior art.

[0006] In a first aspect, an embodiment of the present invention provides a method for characterizing the three-dimensional burning rate of a solid-liquid rocket engine, including: obtaining a pair of CT scan images of each cross-sectional slice along the axis of the solid-liquid rocket engine, where the pair of CT scan images includes: a CT scan image before the operation of the solid-liquid rocket engine and a CT scan image after the operation of the solid-liquid rocket engine; based on the pair of CT scan images, determining the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center; based on the pair of CT scan images and the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine, where the characteristic points include: the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine and the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine; based on the characteristic points and the operating duration of the solid-liquid rocket engine, determining the three-dimensional burning rate distribution law of the solid-liquid rocket engine.

[0007] Further, based on the pair of CT scan images, determining the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center includes: performing binarization processing and morphological processing on the pair of CT scan images to obtain a pair of target images; based on the pair of target images, determining the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine; based on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine, determining the grain center; calculating the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center; and determining the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center as the initial distance.

[0008] Further, the pair of target images includes: a first target image and a second target image, where the first target image is the image corresponding to the CT scan image before the operation of the solid-liquid rocket engine in the pair of target images, and the second target image is the image corresponding to the CT scan image after the operation of the solid-liquid rocket engine in the pair of target images; based on the CT scan image and the distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine includes: based on the first target image, determining the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine, where the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine include: a first initial characteristic point, a second initial characteristic point, a third initial characteristic point, a fourth initial characteristic point, and a fifth initial characteristic point;

[0009] Based on the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine, and the distances between each pixel point in the second target image and the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center, the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine are determined.

[0010] Further, based on the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine, the second target image, and the distances between each pixel point in the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center, determining the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine includes: dividing the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine into 5 first regions according to a first preset division rule, determining the first pixel point closest to the grain center in each first region, and determining the first pixel point as the first target characteristic point; dividing the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine into 10 second regions according to a second preset division rule, determining the second pixel point closest to the second initial characteristic point and the third pixel point closest to the third initial characteristic point in each second region, and determining the second pixel point as the second target characteristic point and the third pixel point as the third target characteristic point; determining the angular bisector of the wheel in each first region, and determining the intersection point of the angular bisector and the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine as the fourth target characteristic point; calculating the midpoint between the second target characteristic point and the third characteristic point in each second region, and determining the midpoint as the fifth target characteristic point.

[0011] Further, based on the characteristic points and the operation duration of the solid-liquid rocket engine, determining the three-dimensional burn rate distribution law of the solid-liquid rocket engine includes: based on the characteristic points, calculating the target distances corresponding to each cross-sectional slice in the axial direction of the solid-liquid rocket engine, where the target distances include: the first distance between the third initial characteristic point and the third target characteristic point, the second distance between the fourth initial characteristic point and the fourth target characteristic point, and the third distance between the fifth initial characteristic point and the fifth target characteristic point; based on the target distances and the operation duration of the solid-liquid rocket engine, calculating the burn rates corresponding to each cross-sectional slice in the axial direction of the solid-liquid rocket engine; based on the burn rates corresponding to each cross-sectional slice in the axial direction of the solid-liquid rocket engine, determining the three-dimensional burn rate distribution law of the solid-liquid rocket engine.

[0012] Second aspect, the embodiments of the present invention further provide a three-dimensional burning rate characterization device for a solid-liquid rocket engine, including: an acquisition unit, configured to acquire CT scan image pairs of each cross-sectional slice along the axis of the solid-liquid rocket engine, where the CT scan image pairs include: a CT scan image before the operation of the solid-liquid rocket engine and a CT scan image after the operation of the solid-liquid rocket engine; a first determination unit, configured to determine, based on the CT scan image pairs, the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center; a second determination unit, configured to determine, based on the CT scan image pairs and the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, the feature points of each cross-sectional slice of the solid-liquid rocket engine, where the feature points include: the feature points of each cross-sectional slice before the operation of the solid-liquid rocket engine and the feature points of each cross-sectional slice after the operation of the solid-liquid rocket engine; a third determination unit, configured to determine, based on the feature points and the operation duration of the solid-liquid rocket engine, the three-dimensional burning rate distribution law of the solid-liquid rocket engine.

[0013] Further, the second determination unit is configured to: perform binarization processing and morphological processing on the CT scan image pairs to obtain a target image pair; determine, based on the target image pair, the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine; determine the grain center based on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine; calculate the distances between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center; and determine the distances between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center as the initial distances.

[0014] Further, the target image pair includes: a first target image and a second target image, where the first target image is the image corresponding to the CT scan image before the operation of the solid-liquid rocket engine in the target image pair, and the second target image is the image corresponding to the CT scan image after the operation of the solid-liquid rocket engine in the target image pair; the second determination unit is configured to: determine, based on the first target image, the feature points of each cross-sectional slice before the operation of the solid-liquid rocket engine, where the feature points of each cross-sectional slice before the operation of the solid-liquid rocket engine include: a first initial feature point, a second initial feature point, a third initial feature point, a fourth initial feature point, and a fifth initial feature point; and determine, based on the feature points of each cross-sectional slice before the operation of the solid-liquid rocket engine, the second target image, and the distances between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center, the feature points of each cross-sectional slice after the operation of the solid-liquid rocket engine.

[0015] In a third aspect, an embodiment of the present invention further provides an electronic device, including a memory and a processor, where the memory is used to store a program for supporting the processor to execute the method described in the first aspect above, and the processor is configured to execute the program stored in the memory.

[0016] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored.

[0017] In an embodiment of the present invention, by obtaining CT scan image pairs of each cross-sectional slice along the axis of a solid-liquid rocket engine, where the CT scan image pair includes: a CT scan image before the solid-liquid rocket engine operates and a CT scan image after the solid-liquid rocket engine operates; based on the CT scan image pair, determining the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center; based on the CT scan image pair and the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, determining the feature points of each cross-sectional slice of the solid-liquid rocket engine, where the feature points include: the feature points of each cross-sectional slice before the solid-liquid rocket engine operates and the feature points of each cross-sectional slice after the solid-liquid rocket engine operates; based on the feature points and the operating duration of the solid-liquid rocket engine, determining the three-dimensional burn rate distribution law of the solid-liquid rocket engine, achieving the purpose of determining the three-dimensional burn rate of the solid-liquid rocket engine through the CT scan images of each cross-sectional slice along the axis before and after the operation of the solid-liquid rocket engine, and further solving the technical problem that it is difficult to determine the three-dimensional burn rate of the complex grain of the solid-liquid rocket engine in the prior art, thereby realizing the technical effect of accurately characterizing the three-dimensional burn rate of the complex grain of the solid-liquid rocket engine.

[0018] Other features and advantages of the present invention will be described in the following specification, and part of them will become obvious from the specification, or be understood by implementing the present invention. The objectives and other advantages of the present invention are achieved and obtained by the structures specifically pointed out in the specification, claims and drawings.

[0019] To make the above objectives, features and advantages of the present invention more obvious and understandable, the following specific preferred embodiments are given, and detailed descriptions are made in conjunction with the accompanying drawings as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0021] Figure 1 It is a flowchart of a three-dimensional burning rate characterization method for a solid-liquid rocket engine provided by an embodiment of the present invention;

[0022] Figure 2 It is a schematic diagram of the characteristic points of the cross-sectional slice of the solid-liquid rocket engine before operation provided by an embodiment of the present invention;

[0023] Figure 3 It is a schematic diagram of the characteristic points of the cross-sectional slice of the solid-liquid rocket engine before operation and the characteristic points of the cross-sectional slice of the solid-liquid rocket engine after operation provided by an embodiment of the present invention;

[0024] Figure 4 It is a schematic diagram of a three-dimensional burning rate characterization device for a solid-liquid rocket engine provided by an embodiment of the present invention;

[0025] Figure 5 It is a schematic diagram of an electronic device provided by an embodiment of the present invention. Specific Embodiments

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions of the present invention with reference to the drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0027] Embodiment 1:

[0028] According to an embodiment of the present invention, an embodiment of a three-dimensional burning rate characterization method for a solid-liquid rocket engine is provided. It should be noted that the steps shown in the flowchart of the drawings can be executed in a computer system such as a set of computer-executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0029] Figure 1 It is a flowchart of the three-dimensional burning rate characterization method for a solid-liquid rocket engine according to an embodiment of the present invention. As Figure 1 shown, the method includes the following steps:

[0030] Step S102: Obtain CT scan image pairs of each cross-sectional slice along the axis of the solid-liquid rocket engine, where the CT scan image pairs include: the CT scan image before the solid-liquid rocket engine operates and the CT scan image after the solid-liquid rocket engine operates;

[0031] Step S104: Based on the CT scan image pairs, determine the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center;

[0032] Step S106: Based on the CT scan image pairs and the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, determine the feature points of each cross-sectional slice of the solid-liquid rocket engine, where the feature points include: the feature points of each cross-sectional slice before the solid-liquid rocket engine operates and the feature points of each cross-sectional slice after the solid-liquid rocket engine operates;

[0033] Step S108: Based on the feature points and the operating duration of the solid-liquid rocket engine, determine the three-dimensional burn rate distribution law of the solid-liquid rocket engine.

[0034] In the embodiment of the present invention, by obtaining CT scan image pairs of each cross-sectional slice along the axis of the solid-liquid rocket engine, where the CT scan image pairs include: the CT scan image before the solid-liquid rocket engine operates and the CT scan image after the solid-liquid rocket engine operates; based on the CT scan image pairs, determining the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center; based on the CT scan image pairs and the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, determining the feature points of each cross-sectional slice of the solid-liquid rocket engine, where the feature points include: the feature points of each cross-sectional slice before the solid-liquid rocket engine operates and the feature points of each cross-sectional slice after the solid-liquid rocket engine operates; based on the feature points and the operating duration of the solid-liquid rocket engine, determining the three-dimensional burn rate distribution law of the solid-liquid rocket engine, the object of determining the three-dimensional burn rate of the solid-liquid rocket engine through the CT scan images of each cross-sectional slice along the axis before and after the operation of the solid-liquid rocket engine is achieved, and further solves the technical problem that it is difficult to determine the three-dimensional burn rate of the complex grain of the solid-liquid rocket engine in the prior art, thus realizing the technical effect of accurately characterizing the three-dimensional burn rate of the complex grain of the solid-liquid rocket engine.

[0035] In the embodiment of the present invention, Step S104 includes the following steps:

[0036] Perform binarization processing and morphological processing on the CT scan image pairs to obtain a target image pair;

[0037] Based on the target image pair, determine the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine;

[0038] Based on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine, determine the center of the grain;

[0039] Calculate the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the center of the grain;

[0040] Determine the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the center of the grain as the initial distance.

[0041] In the embodiment of the present invention, first, perform binarization processing and morphological processing on the CT scan image pairs of each cross-sectional slice in the axial direction of the solid-liquid rocket engine to obtain the target image pairs of each cross-sectional slice in the axial direction of the solid-liquid rocket engine, and then crop the target image pairs of each cross-sectional slice in the axial direction of the solid-liquid rocket engine according to a preset size to obtain the target images of each cross-sectional slice in the axial direction of the solid-liquid rocket engine with unified sizes.

[0042] Next, use image recognition technology to identify the inner contour edge of the single-channel wheel-shaped grain and the center of the grain in each cross-sectional slice in the axial direction of the solid-liquid rocket engine, and calculate the distance from the center of the grain to each pixel point on the inner contour edge of the single-channel wheel-shaped grain in each cross-sectional slice in the axial direction of the solid-liquid rocket engine, so as to determine the initial distance.

[0043] In the embodiment of the present invention, the target image pair includes: a first target image and a second target image, where the first target image is the image corresponding to the CT scan image of the solid-liquid rocket engine before operation in the target image pair, and the second target image is the image corresponding to the CT scan image of the solid-liquid rocket engine after operation in the target image pair. Step S106 includes the following steps:

[0044] Based on the first target image, determine the characteristic points of each cross-sectional slice of the solid-liquid rocket engine before operation, where the characteristic points of each cross-sectional slice of the solid-liquid rocket engine before operation include: a first initial characteristic point, a second initial characteristic point, a third initial characteristic point, a fourth initial characteristic point, and a fifth initial characteristic point;

[0045] Based on the characteristic points of each cross-sectional slice of the solid-liquid rocket engine before operation, the second target image, and the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the center of the grain, determine the characteristic points of each cross-sectional slice of the solid-liquid rocket engine after operation.

[0046] In the embodiment of the present invention, first, characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine are determined by using the first target image. As Figure 2 shown, the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine include a first initial characteristic point A from the wheel angle to the wheel root, a second initial characteristic point B, a third initial characteristic point C, a fourth initial characteristic point D, and a fifth initial characteristic point E.

[0047] Next, according to the first preset division rule, the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine is divided into 5 first regions, the first pixel point closest to the grain center in each first region is determined, and the first pixel point is determined as the first target characteristic point;

[0048] According to the second preset division rule, the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine is divided into 10 second regions, the second pixel point closest to the second initial characteristic point and the third pixel point closest to the third initial characteristic point in each second region are determined, the second pixel point is determined as the second target characteristic point, and the third pixel point is determined as the third target characteristic point;

[0049] The angular bisector of the wheel in each first region is determined, and the intersection point of the angular bisector and the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine is determined as the fourth target characteristic point;

[0050] The midpoint between the second target characteristic point and the third characteristic point in each second region is calculated, and the midpoint is determined as the fifth target characteristic point.

[0051] As Figure 3 shown, the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine include: the first target characteristic point A * , the second target characteristic point B * , the third target characteristic point C * , the fourth target characteristic point D * and the fifth target characteristic point E * .

[0052] In the embodiment of the present invention, step S108 includes the following steps:

[0053] Based on the characteristic points, the target distances corresponding to each cross-sectional slice in the axial direction of the solid-liquid rocket engine are calculated, where the target distances include: a first distance between the third initial characteristic point and the third target characteristic point, a second distance between the fourth initial characteristic point and the fourth target characteristic point, and a third distance between the fifth initial characteristic point and the fifth target characteristic point;

[0054] Based on the target distance and the working duration of the solid-liquid rocket engine, calculate the burning rates corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine;

[0055] Based on the burning rates corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine, determine the three-dimensional burning rate distribution law of the solid-liquid rocket engine.

[0056] In an embodiment of the present invention, first, according to the coordinate positions of the characteristic points corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine, determine the first distance between the third initial characteristic point and the third target characteristic point, the second distance between the fourth initial characteristic point and the fourth target characteristic point, and the third distance between the fifth initial characteristic point and the fifth target characteristic point corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine.

[0057] Then, divide the first distance by the working duration of the solid-liquid rocket engine, divide the second distance by the working duration of the solid-liquid rocket engine, and divide the third distance by the working duration of the solid-liquid rocket engine respectively to obtain the burning rates corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine;

[0058] Finally, according to the burning rates corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine, determine the distribution of the burning rates along the axis corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine (i.e., the three-dimensional burning rate distribution law of the solid-liquid rocket engine).

[0059] In an embodiment of the present invention, for the CT scan cross-sectional images after the single-wheel solid-liquid rocket engine test, conduct research on the digital image processing and recognition technology of characteristic points. According to the geometric characteristics of each characteristic point and combined with the image processing method, the burning rate of each characteristic point can be characterized. By batch processing the slice images in the axial direction of the grain, the distribution law of the burning rates of each characteristic point along the axis can be obtained, and then the three-dimensional burning rate distribution law of the complex single-channel wheel-shaped charge can be obtained. The CT scan cross-sectional images after the solid-liquid rocket engine and the positions of the characteristic points before and after the test are as Figure 3 shown, where the characteristic points A, B, C, D, and E are the positions of each characteristic point before the operation of the solid-liquid rocket engine respectively. The characteristic point A * , B * , C * , D * , and E * are the positions of each characteristic point of the grain after the operation of the solid-liquid rocket engine respectively. The line connecting two points is the distance of the burning surface retreating along the normal direction at each characteristic point, and then the burning rate of each characteristic point can be calculated according to the combustion chamber time.

[0060] In an embodiment of the present invention, digital image processing technology is applied to the cross-sectional images after CT scanning to identify the boundary contour of the grain, and according to the corresponding method, each feature point is identified, and further the burning rate along of each feature of the complex grain shape is characterized. The variation law along the axial direction of the engine.

[0061] Embodiment 2:

[0062] An embodiment of the present invention further provides a three-dimensional burning rate characterization device for a solid-liquid rocket engine. This device for characterizing the three-dimensional burning rate of a solid-liquid rocket engine is used to execute the method for characterizing the three-dimensional burning rate of a solid-liquid rocket engine provided in the above content of the embodiment of the present invention. The following is a specific introduction to the device for characterizing the three-dimensional burning rate of a solid-liquid rocket engine provided by the embodiment of the present invention.

[0063] As Figure 4 shown, Figure 4 is a schematic diagram of the above device for characterizing the three-dimensional burning rate of a solid-liquid rocket engine. This device for characterizing the three-dimensional burning rate of a solid-liquid rocket engine includes:

[0064] An acquisition unit 10, configured to acquire a pair of CT scan images of each cross-sectional slice along the axial direction of the solid-liquid rocket engine, where the pair of CT scan images includes: the CT scan image before the solid-liquid rocket engine works and the CT scan image after the solid-liquid rocket engine works;

[0065] A first determination unit 20, configured to determine the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center based on the pair of CT scan images;

[0066] A second determination unit 30, configured to determine the feature points of each cross-sectional slice of the solid-liquid rocket engine based on the pair of CT scan images and the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, where the feature points include: the feature points of each cross-sectional slice before the solid-liquid rocket engine works and the feature points of each cross-sectional slice after the solid-liquid rocket engine works;

[0067] A third determination unit 40, configured to determine the three-dimensional burning rate distribution law of the solid-liquid rocket engine based on the feature points and the working duration of the solid-liquid rocket engine.

[0068] In an embodiment of the present invention, by obtaining CT scan image pairs of each cross-sectional slice in the axial direction of a solid-liquid rocket engine, where the CT scan image pairs include: a CT scan image before the solid-liquid rocket engine operates and a CT scan image after the solid-liquid rocket engine operates; based on the CT scan image pairs, determining the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center; based on the CT scan image pairs and the initial distances from each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine, where the characteristic points include: the characteristic points of each cross-sectional slice before the solid-liquid rocket engine operates and the characteristic points of each cross-sectional slice after the solid-liquid rocket engine operates; based on the characteristic points and the operating duration of the solid-liquid rocket engine, determining the three-dimensional burn rate distribution law of the solid-liquid rocket engine, achieving the purpose of determining the three-dimensional burn rate of the solid-liquid rocket engine through the CT scan images of each cross-sectional slice in the axial direction before and after the operation of the solid-liquid rocket engine, and further solving the technical problem that it is difficult to determine the three-dimensional burn rate of the complex grain of the solid-liquid rocket engine in the prior art, thereby realizing the technical effect of accurately characterizing the three-dimensional burn rate of the complex grain of the solid-liquid rocket engine.

[0069] Embodiment III:

[0070] The embodiment of the present invention further provides an electronic device, including a memory and a processor, where the memory is used to store a program for supporting the processor to execute the method described in Embodiment 1 above, and the processor is configured to execute the program stored in the memory.

[0071] Refer to Figure 5 , the embodiment of the present invention further provides an electronic device 100, including: a processor 60, a memory 61, a bus 62, and a communication interface 63, where the processor 60, the communication interface 63, and the memory 61 are connected through the bus 62; the processor 60 is used to execute an executable module stored in the memory 61, such as a computer program.

[0072] Among them, the memory 61 may include a high-speed random access memory (RAM, Random Access Memory), and may also include a non-volatile memory, such as at least one disk memory. Through at least one communication interface 63 (which can be wired or wireless), a communication connection is realized between this system network element and at least one other network element, and the Internet, a wide area network, a local area network, a metropolitan area network, etc. can be used.

[0073] The bus 62 can be an ISA bus, a PCI bus, an EISA bus, or the like. The bus can be divided into an address bus, a data bus, a control bus, etc. For the sake of convenience of representation, Figure 5 only a bidirectional arrow is used in Figure 5 , but it does not mean that there is only one bus or one type of bus.

[0074] Among them, the memory 61 is used to store a program. After receiving an execution instruction, the processor 60 executes the program. The method executed by the device defined by the flow process disclosed in any embodiment of the foregoing embodiments of the present invention can be applied to or implemented by the processor 60.

[0075] The processor 60 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the integrated logic circuit in the hardware of the processor 60 or by instructions in the form of software. The above-mentioned processor 60 can be a general-purpose processor, including a central processing unit (CPU for short), a network processor (NP for short), etc.; it can also be a digital signal processor (DSP for short), an application specific integrated circuit (ASIC for short), a field-programmable gate array (FPGA for short), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute the various methods, steps, and logic block diagrams disclosed in the embodiments of the present invention. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present invention can be directly embodied as being executed and completed by a hardware decoding processor, or executed and completed by a combination of hardware and software modules in the decoding processor. The software module can be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory 61, and the processor 60 reads the information in the memory 61 and combines its hardware to complete the steps of the above method.

[0076] Embodiment 4:

[0077] The embodiment of the present invention also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is run by a processor, it executes the steps of the method described in Embodiment 1 above.

[0078] In addition, in the description of the embodiments of the present invention, unless otherwise clearly defined and limited, the terms "installed", "connected", and "coupled" shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0079] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0080] In several embodiments provided by the present application, it should be understood that the disclosed systems, devices, and methods can be implemented in other ways. The device embodiments described above are merely illustrative. For example, the division of the units is only a logical function division, and there may be other division methods in actual implementation. For another example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the displayed or discussed mutual coupling, direct coupling, or communication connection may be through some communication interfaces, and the indirect coupling or communication connection of the devices or units may be in an electrical, mechanical, or other form.

[0081] The units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0082] In addition, the functional units in various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit.

[0083] Finally, it should be noted that the above-described embodiments are only specific implementation manners of the present invention, used to illustrate the technical solutions of the present invention, rather than limiting it. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that any person skilled in the technical field of the present invention can still modify the technical solutions recorded in the foregoing embodiments, or can easily think of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A three-dimensional burning rate characterization method for a solid-liquid rocket engine, characterized in that, Including: Obtaining a pair of CT scan images of each cross-sectional slice along the axis of a solid-liquid rocket engine, where the pair of CT scan images includes: a CT scan image before the solid-liquid rocket engine operates and a CT scan image after the solid-liquid rocket engine operates; Based on the pair of CT scan images, determining the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine to the grain center; Based on the pair of CT scan images and the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine to the grain center, determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine, where the characteristic points include: the characteristic points of each cross-sectional slice before the solid-liquid rocket engine operates and the characteristic points of each cross-sectional slice after the solid-liquid rocket engine operates; Based on the characteristic points, calculating the target distance corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine; Based on the target distance and the operating duration of the solid-liquid rocket engine, calculating the burning rate corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine; Based on the burning rates corresponding to each cross-sectional slice along the axis of the solid-liquid rocket engine, determining the three-dimensional burning rate distribution law of the solid-liquid rocket engine.

2. The method according to claim 1, characterized in that Based on the pair of CT scan images, determining the initial distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine to the grain center includes: Performing binarization processing and morphological processing on the pair of CT scan images to obtain a pair of target images; Based on the pair of target images, determining the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine; Based on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine, determining the grain center; Calculating the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine and the grain center; Determining the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine and the grain center as the initial distance.

3. The method according to claim 2, characterized in that, The pair of target images includes: a first target image and a second target image, where the first target image is the image corresponding to the CT scan image before the solid-liquid rocket engine operates in the pair of target images, and the second target image is the image corresponding to the CT scan image after the solid-liquid rocket engine operates in the pair of target images; Based on the CT scan image and the distance from each pixel point on the inner contour edge of the single-channel wheel-shaped grain in the solid-liquid rocket engine to the grain center, determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine includes: Based on the first target image, determining the characteristic points of each cross-sectional slice before the solid-liquid rocket engine operates, where the characteristic points of each cross-sectional slice before the solid-liquid rocket engine operates include: a first initial characteristic point, a second initial characteristic point, a third initial characteristic point, a fourth initial characteristic point, and a fifth initial characteristic point; Based on the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine, and the distances between each pixel point in the second target image and the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center, the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine are determined.

4. The method according to claim 3, wherein Based on the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine, and the distances between each pixel point in the second target image and the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center, determining the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine includes: According to the first preset division rule, the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine is divided into 5 first regions, the first pixel point closest to the grain center in each first region is determined, and the first pixel point is determined as the first target characteristic point; According to the second preset division rule, the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine is divided into 10 second regions, the second pixel point closest to the second initial characteristic point and the third pixel point closest to the third initial characteristic point in each second region are determined, and the second pixel point is determined as the second target characteristic point, and the third pixel point is determined as the third target characteristic point; The angular bisector of the wheel in each first region is determined, and the intersection point of the angular bisector and the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine is determined as the fourth target characteristic point; The midpoint between the second target characteristic point and the third characteristic point in each second region is calculated, and the midpoint is determined as the fifth target characteristic point.

5. The method according to claim 4, wherein The target distances include: the first distance between the third initial characteristic point and the third target characteristic point, the second distance between the fourth initial characteristic point and the fourth target characteristic point, and the third distance between the fifth initial characteristic point and the fifth target characteristic point.

6. A three-dimensional burning rate characterization device for a solid-liquid rocket engine, characterized in that Including: An acquisition unit for acquiring pairs of CT scan images of each cross-sectional slice in the axial direction of the solid-liquid rocket engine, where the pair of CT scan images includes: the CT scan image before the operation of the solid-liquid rocket engine and the CT scan image after the operation of the solid-liquid rocket engine; A first determination unit for determining the initial distances from each pixel point in the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center based on the pair of CT scan images; A second determination unit for determining the characteristic points of each cross-sectional slice of the solid-liquid rocket engine based on the pair of CT scan images and the initial distances from each pixel point in the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine to the grain center, where the characteristic points include: the characteristic points of each cross-sectional slice before the operation of the solid-liquid rocket engine and the characteristic points of each cross-sectional slice after the operation of the solid-liquid rocket engine; A third determination unit, configured to calculate a target distance corresponding to each cross-sectional slice in the axial direction of the solid-liquid rocket engine based on the feature points; calculate a burn rate corresponding to each cross-sectional slice in the axial direction of the solid-liquid rocket engine based on the target distance and the working duration of the solid-liquid rocket engine; and determine a three-dimensional burn rate distribution law of the solid-liquid rocket engine based on the burn rates corresponding to the cross-sectional slices in the axial direction of the solid-liquid rocket engine.

7. The device according to claim 6, characterized in that, The second determination unit is configured to: Perform binarization processing and morphological processing on the CT scan image pair to obtain a target image pair; Determine the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine based on the target image pair; Determine the grain center based on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine; Calculate the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center; Determine the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center as the initial distance.

8. The device according to claim 7, wherein The target image pair includes: a first target image and a second target image, where the first target image is an image corresponding to the CT scan image of the solid-liquid rocket engine before operation in the target image pair, and the second target image is an image corresponding to the CT scan image of the solid-liquid rocket engine after operation in the target image pair; The second determination unit is configured to: Determine the feature points of each cross-sectional slice of the solid-liquid rocket engine before operation based on the first target image, where the feature points of each cross-sectional slice of the solid-liquid rocket engine before operation include: a first initial feature point, a second initial feature point, a third initial feature point, a fourth initial feature point, and a fifth initial feature point; Determine the feature points of each cross-sectional slice of the solid-liquid rocket engine after operation based on the feature points of each cross-sectional slice of the solid-liquid rocket engine before operation, the second target image, and the distance between each pixel point on the inner contour edge of the single-channel wheel-shaped grain of the solid-liquid rocket engine and the grain center.

9. An electronic device, characterized in that, It includes a memory and a processor, where the memory is used to store a program for supporting the processor to execute the method according to any one of claims 1 to 5, and the processor is configured to execute the program stored in the memory.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is run by the processor, it executes the steps of the method according to any one of claims 1 to 5.

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