CN111734558A - Method and device for measuring burning rate of solid-liquid rocket engine - Google Patents
Method and device for measuring burning rate of solid-liquid rocket engine Download PDFInfo
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- CN111734558A CN111734558A CN202010233585.7A CN202010233585A CN111734558A CN 111734558 A CN111734558 A CN 111734558A CN 202010233585 A CN202010233585 A CN 202010233585A CN 111734558 A CN111734558 A CN 111734558A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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Abstract
The invention provides a method and a device for measuring the burning rate of a solid-liquid rocket engine, which comprises the following steps: acquiring three-dimensional original data; reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images; determining the length of each three-dimensional tangent plane layer image according to a preset calibration value; calculating the axial solid fuel thickness of the explosive column after the engine test run according to the length of the three-dimensional sectional layer image; the burning rate of the solid-liquid rocket engine is calculated according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested, the distribution condition of the engine combustion along the axial direction is represented by the burning rate of the solid-liquid rocket engine, and the measurement accuracy is high.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a method and a device for measuring the burning speed of a solid-liquid rocket engine.
Background
The solid fuel burning rate of the solid-liquid rocket engine is an important index for representing the working performance of the engine, and is closely related to a propellant formula, an oxidant flow rate and the like, so that the effective and accurate measurement of the solid fuel burning rate is an important step in experimental measurement.
The current measurement techniques include a target line method, an acoustic emission method and a start-stop point averaging method. The target line method and the acoustic emission method can only measure the burning rate under a certain working pressure, and are influenced by factors such as the pressure of a combustion chamber and the like, the upper limit of the pressure is lower, and thus the measurement accuracy is low; the common start-stop point average method has measurement errors, the distribution condition of the burning rate along the axial direction of the solid explosive column cannot be calculated, and the measurement accuracy is low.
Disclosure of Invention
In view of the above, the invention aims to provide a method and a device for measuring the combustion speed of a solid-liquid rocket engine, which are used for representing the distribution condition of engine combustion along the axial direction through the combustion speed of the solid-liquid rocket engine, and have high measurement accuracy.
In a first aspect, an embodiment of the present invention provides a method for measuring a combustion speed of a solid-liquid rocket engine, where the method includes:
acquiring three-dimensional original data;
reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images;
determining the length of each three-dimensional tangent plane layer image according to a preset calibration value;
calculating the axial solid fuel thickness of the explosive column after the engine test according to the length of the three-dimensional sectional layer images;
and calculating the burning speed of the solid-liquid rocket engine according to the thickness of the axial solid fuel of the explosive column after the engine is tested.
Further, the reconstructing the three-dimensional original data to obtain three-dimensional images of each slice layer includes:
inputting the three-dimensional original data into a back projection algorithm to obtain a three-dimensional model image;
and obtaining three-dimensional each section layer image according to the three-dimensional model image.
Further, the determining the length of each three-dimensional section layer image according to a preset calibration value includes:
determining the boundary of each three-dimensional tangent plane layer image;
and obtaining the length of each three-dimensional tangent plane layer image through the preset calibration value and the pixel size of each three-dimensional tangent plane layer image based on the boundary of each three-dimensional tangent plane layer image.
Further, the calculating the burning rate of the solid-liquid rocket engine according to the thickness of the explosive column axial solid fuel after the engine test run comprises:
calculating the burning rate of the solid-liquid rocket engine according to the following formula:
wherein V is the burning speed of the solid-liquid rocket engine, 1 is the axial solid fuel thickness of the grain after the engine is tested, 2 is the preset axial solid fuel thickness of the grain before the engine is tested, and t is the ignition time.
In a second aspect, an embodiment of the present invention provides a device for measuring a combustion speed of a rocket motor, where the device includes:
an acquisition unit configured to acquire three-dimensional original data;
the reconstruction unit is used for reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images;
the determining unit is used for determining the length of each three-dimensional tangent plane layer image according to a preset calibration value;
the thickness calculation unit is used for calculating the axial solid fuel thickness of the explosive column after the trial run of the engine according to the length of the three-dimensional sectional layer images;
and the burning rate calculation unit is used for calculating the burning rate of the solid-liquid rocket engine according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested.
Further, the reconstruction unit is specifically configured to:
inputting the three-dimensional original data into a back projection algorithm to obtain a three-dimensional model image;
and obtaining three-dimensional each section layer image according to the three-dimensional model image.
Further, the determining unit is specifically configured to:
determining the boundary of each three-dimensional tangent plane layer image;
and obtaining the length of each three-dimensional tangent plane layer image through the preset calibration value and the pixel size of each three-dimensional tangent plane layer image based on the boundary of each three-dimensional tangent plane layer image.
Further, the burning rate calculation unit is specifically configured to:
calculating the burning rate of the solid-liquid rocket engine according to the following formula:
wherein V is the burning speed of the solid-liquid rocket engine, 1 is the axial solid fuel thickness of the grain after the engine is tested, 2 is the preset axial solid fuel thickness of the grain before the engine is tested, and t is the ignition time.
In a third aspect, an embodiment of the present invention provides an electronic device, including a memory and a processor, where the memory stores a computer program operable on the processor, and the processor implements the method described above when executing the computer program.
In a fourth aspect, embodiments of the invention provide a computer readable medium having non-volatile program code executable by a processor, the program code causing the processor to perform the method as described above.
The embodiment of the invention provides a method and a device for measuring the burning rate of a solid-liquid rocket engine, which comprises the following steps: acquiring three-dimensional original data; reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images; determining the length of each three-dimensional tangent plane layer image according to a preset calibration value; calculating the axial solid fuel thickness of the explosive column after the engine test run according to the length of the three-dimensional sectional layer image; the burning rate of the solid-liquid rocket engine is calculated according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested, the distribution condition of the engine combustion along the axial direction is represented by the burning rate of the solid-liquid rocket engine, and the measurement accuracy is high.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a flow chart of a method for measuring a combustion speed of a solid-liquid rocket engine according to an embodiment of the present invention;
FIG. 2 is a schematic view of a combustion speed measuring device of a solid-liquid rocket engine according to a second embodiment of the present invention;
FIG. 3 is a schematic view of a system for measuring the combustion rate of a rocket motor according to a third embodiment of the present invention;
FIG. 4 is a schematic view of another system for measuring the combustion speed of a rocket motor according to a third embodiment of the present invention;
fig. 5 is a schematic structural view of a guide rail of a rotating bracket according to a third embodiment of the present invention;
fig. 6 is a schematic structural view of a rotating bracket according to a third embodiment of the present invention.
Icon:
111-an acquisition unit; 112-a reconstruction unit; 113-a determination unit; 114-a thickness calculation unit; 115-combustion rate calculation unit; 1-a bottom plate; 2-a vertical adapter plate; 3-a triangular support frame; 4-a thrust chamber body simulation component; 5-a head simulating component; 6-rotating the carriage rail; 7-rotating the bracket; 8-CT probe; 9-a detector; 10-a cylindrical support frame; 101-a guide rail; 102-a groove; 103-bolt through holes; 104-a threaded hole; 201-a boss; 202-a first support; 203-a second bracket; 204-through hole.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
For the understanding of the present embodiment, the following detailed description will be given of the embodiment of the present invention.
The first embodiment is as follows:
fig. 1 is a flow chart of a method for measuring a combustion speed of a solid-liquid rocket engine according to an embodiment of the present invention.
Referring to fig. 1, the method includes the steps of:
step S101, acquiring three-dimensional original data;
here, the acquisition of three-dimensional raw data mainly employs a nuclear imaging technique in industrial CT (Computer Tomography). Due to different scanning modes, the industrial CT is mainly classified into cone beam CT, spiral CT, fan CT and other types, wherein the most common is cone beam CT. The scanning mode of cone beam CT is open ray scanning, a flat panel is used for collecting a two-dimensional ray projection sequence of an object, the whole tomographic image in a scanning area is rapidly reconstructed through three dimensions, and finally the three-dimensional image of the object to be detected is completed. A cone-beam CT system includes an X-ray source, a gantry, and a detector.
The specific detection process is as follows: starting an industrial CT device and checking a machine; placing and fixing the tested explosive column on a sample table of a CT (computed tomography), starting a ray power supply, and emitting X rays by a probe; rotating the CT sample table for 360 degrees, keeping the X-ray in an emission state, observing whether the outline of the test piece to be tested exceeds the window range of the interface from industrial CT software, namely, checking whether the whole outline of the test piece to be tested is contained in the interface of the industrial CT software, and if so, rotating the test piece to be tested for a certain angle so as to obtain a plurality of groups of projection data; if not, the position of the test piece to be tested is readjusted, and the X, Y and Z-direction positions of the test piece to be tested are adjusted.
The detection process of the multiple sets of projection data is as follows: the test piece to be tested is positioned between the CT probe and the detector, and because the sizes of the test piece to be tested are different, the attenuation of X-rays emitted by the CT probe in an object is different, the detector can obtain a series of data information. The data information is only two-dimensional data of the test piece to be tested, and to obtain three-dimensional structure data of the test piece to be tested, the test piece to be tested needs to be rotated by delta alpha, the X-ray is used for irradiating the test piece again, the detector receives signal data again, and the operation is repeated, so that a series of projection data can be obtained, and Y groups of projection data, namely a plurality of groups of projection data, are obtained until the test piece is rotated for Y times (Y. delta alpha is 360 degrees), wherein the plurality of groups of projection data are three-dimensional original data.
S102, reconstructing three-dimensional original data to obtain three-dimensional sectional layer images;
specifically, in the process of reconstructing three-dimensional original data, a back projection algorithm such as FDK (Feldkamp-Davis-Kress, cone beam type algorithm) can be adopted to reconstruct and obtain the three-dimensional structure of the test piece, so that a one-time scanning reconstruction process is realized.
After the three-dimensional original data is reconstructed, spatial rotation, sectioning, amplification, reduction, movement and other operations can be carried out on the test piece to be tested, and detail diagrams of various sectioning surfaces of the three-dimensional structure can be observed, so that the visualization of a three-dimensional model is realized.
Step S103, determining the length of each three-dimensional tangent plane layer image according to a preset calibration value;
step S104, calculating the axial solid fuel thickness of the explosive column after the trial run of the engine according to the length of each three-dimensional section layer image;
and step S105, calculating the burning speed of the solid-liquid rocket engine according to the axial solid fuel thickness of the explosive column after the engine is tested.
In the embodiment, the CT device is turned on, whether the profile of the test piece to be tested exceeds the window range of the interface is observed from industrial CT software, the CT probe continuously emits X-rays, the rotating bracket is rotated by 360 degrees, the X-rays complete scanning of the drug column for one circle, so that three-dimensional original data of the drug column are obtained, and the scanned three-dimensional original data are subjected to image reconstruction processing by the computer, so that three-dimensional images of each section layer are obtained; determining the length of each three-dimensional tangent plane layer image according to a preset calibration value; calculating the axial solid fuel thickness of the explosive column after the engine test run according to the length of the three-dimensional sectional layer image; the burning rate of the solid-liquid rocket engine is calculated according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested, the distribution condition of the engine combustion along the axial direction is represented by the burning rate of the solid-liquid rocket engine, and the measurement accuracy is high.
Further, step S102 includes the steps of:
step S201, inputting three-dimensional original data into a back projection algorithm to obtain a three-dimensional model image;
and S202, obtaining three-dimensional each section layer image according to the three-dimensional model image.
Specifically, three-dimensional original data are imported into VGstudio Max software, a three-dimensional model image is output and obtained through a back projection algorithm in the software, and the three-dimensional model image is processed by the software to obtain three-dimensional sectional layer images.
Further, step S103 includes the steps of:
s301, determining the boundary of each three-dimensional tangent plane layer image;
specifically, the boundary of each three-dimensional sectional layer image can be identified by a gray value marking method, that is, each part is marked according to the difference of gray values of each part in each three-dimensional sectional layer image. According to the gray value difference of the image, the boundary of the grain is marked, and combustion products, a carbonization layer, a heated grain layer, a combustion chamber heat insulation layer and the like are distinguished, so that the thickness of the grain required for calculating the burning rate is measured more accurately.
Step S302, based on the boundary of each three-dimensional tangent plane layer image, the length of each three-dimensional tangent plane layer image is obtained through presetting a calibration value and the pixel size of each three-dimensional tangent plane layer image.
Specifically, after the boundary of each three-dimensional section layer image is determined, the measurement tool in the software is calibrated, that is, the software has a default value initially, and the calibration process is to redefine the default value, so as to obtain a preset calibration value.
When CT scanning is carried out, a measuring tool is placed in a field of view, the measuring tool in each three-dimensional tangent plane layer image exists, the length of a pixel value with a certain length in each three-dimensional tangent plane layer image is defined, the length of one pixel can be converted, and therefore pixel calibration is completed. And finally, the length of each three-dimensional tangent plane layer image is obtained through presetting a calibration value and the pixel size of each three-dimensional tangent plane layer image.
Further, step S105 includes:
calculating the burning speed of the solid-liquid rocket engine according to a formula:
(1)
wherein V is the burning speed of the solid-liquid rocket engine, 1 is the axial solid fuel thickness of the grain after the engine is tested, 2 is the preset axial solid fuel thickness of the grain before the engine is tested, and t is the ignition time.
The embodiment of the invention provides a method for measuring the burning rate of a solid-liquid rocket engine, which comprises the following steps: acquiring three-dimensional original data; reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images; determining the length of each three-dimensional tangent plane layer image according to a preset calibration value; calculating the axial solid fuel thickness of the explosive column after the engine test run according to the length of the three-dimensional sectional layer image; the burning rate of the solid-liquid rocket engine is calculated according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested, the distribution condition of the engine combustion along the axial direction is represented by the burning rate of the solid-liquid rocket engine, and the measurement accuracy is high.
Example two:
fig. 2 is a schematic view of a combustion speed measuring device of a solid-liquid rocket engine provided by the second embodiment of the invention.
Referring to fig. 2, the apparatus includes:
an acquisition unit 111 for acquiring three-dimensional original data;
the reconstruction unit 112 is configured to reconstruct the three-dimensional original data to obtain three-dimensional images of each slice layer;
a determining unit 113, configured to determine lengths of the three-dimensional slice layer images according to a preset calibration value;
the thickness calculating unit 114 is used for calculating the axial solid fuel thickness of the explosive column after the trial run of the engine according to the length of the three-dimensional section layer image;
and the burning rate calculation unit 115 is used for calculating the burning rate of the solid-liquid rocket engine according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested.
Further, the reconstruction unit 112 is specifically configured to:
inputting the three-dimensional original data into a back projection algorithm to obtain a three-dimensional model image;
and obtaining three-dimensional sectional layer images according to the three-dimensional model image.
Further, the determining unit 113 is specifically configured to:
determining the boundary of each three-dimensional tangent plane layer image;
and based on the boundary of each three-dimensional tangent plane layer image, the length of each three-dimensional tangent plane layer image is obtained by presetting a calibration value and the pixel size of each three-dimensional tangent plane layer image.
Further, the burning rate calculation unit 115 is specifically configured to:
calculating the burning speed of the solid-liquid rocket engine according to the formula (1); wherein V is the burning speed of the solid-liquid rocket engine, 1 is the axial solid fuel thickness of the grain after the engine is tested, 2 is the preset axial solid fuel thickness of the grain before the engine is tested, and t is the ignition time.
The embodiment of the invention provides a burning rate measuring device of a solid-liquid rocket engine, which comprises: acquiring three-dimensional original data; reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images; determining the length of each three-dimensional tangent plane layer image according to a preset calibration value; calculating the axial solid fuel thickness of the explosive column after the engine test run according to the length of the three-dimensional sectional layer image; the burning rate of the solid-liquid rocket engine is calculated according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested, the distribution condition of the engine combustion along the axial direction is represented by the burning rate of the solid-liquid rocket engine, and the measurement accuracy is high.
Example three:
fig. 3 is a schematic view of a combustion speed measuring system of a hybrid rocket engine provided in a third embodiment of the present invention, and fig. 4 is a schematic view of another combustion speed measuring system of a hybrid rocket engine provided in the third embodiment of the present invention.
Referring to fig. 3 and 4, the system comprises a base plate 1, a vertical adapter plate 2, a triangular support frame 3, a thrust chamber body part simulation component 4, a head part simulation component 5, a rotating support slide rail guide 6, a rotating support 7, a CT probe 8, a detector 9 and a cylindrical support frame 10.
The system can scan the explosive column by 360 degrees, when the CT probe 8 emits X rays, the detector 9 receives the scanned X rays and obtains a plurality of three-dimensional original data according to the attenuation result, and the CT probe 8 can scan the explosive column by 360 degrees through the rotation of the rotating bracket 7.
Referring to the structural schematic diagram of the rotating bracket guide rail shown in fig. 5, the groove 102 is installed in cooperation with the thrust chamber body simulation component 4, connected with the thrust chamber body through the bolt through hole 103, and the threaded hole 104 is connected with the vertical adapter plate 2.
Referring to the structural schematic diagram of the rotating bracket shown in fig. 6, the boss 201 is installed in cooperation with the guide rail 101 in the rotating bracket guide rail 6, the thrust room body simulation component 4 is fixed by the through hole 204, the first bracket 202 is connected with the detector 9, and the second bracket 203 is connected with the CT probe 8.
In the embodiment, the CT device is turned on, the CT probe continuously emits X-rays, the rotating bracket is rotated by 360 degrees, the X-rays complete a circle of scanning of the grain, and the detector continuously receives the X-rays emitted by the CT probe, so that three-dimensional original data of the grain is obtained; according to the three-dimensional original data, the change of the burning speed of the fuel grain on a certain axis in the ignition process of the engine along with the time can be obtained, and the change of the burning speed of a certain point in the tangent plane in the fuel grain along with the time can also be obtained.
The method can also be applied to the measurement of the burning rate of the solid-liquid rocket engine. Starting a CT device, observing whether the outline of a test piece to be tested exceeds the window range of the interface or not from industrial CT software, enabling a CT probe to continuously emit X rays, rotating a rotating support for 360 degrees, enabling the X rays to complete scanning of the explosive column for one circle, thereby obtaining three-dimensional original data of the explosive column, and carrying out image reconstruction processing on the scanned three-dimensional original data through a computer to obtain three-dimensional images of each section layer; determining the length of each three-dimensional tangent plane layer image according to a preset calibration value; calculating the axial solid fuel thickness of the explosive column after the engine test run according to the length of the three-dimensional sectional layer image; according to the thickness of the solid fuel in the axial direction of the grain after the engine is tested, the burning speed of the solid-liquid rocket engine is calculated according to the ignition time, so that the distribution condition of the engine in the axial direction of combustion is represented by the burning speed of the solid-liquid rocket engine, and the measurement accuracy is high.
The embodiment of the invention also provides a computer readable medium with a nonvolatile program code executable by a processor, wherein the computer readable medium stores a computer program, and the computer program is executed by the processor to execute the steps of the method for measuring the combustion speed of the solid-liquid rocket engine of the embodiment.
The computer program product provided in the embodiment of the present invention includes a computer-readable storage medium storing a program code, where instructions included in the program code may be used to execute the method described in the foregoing method embodiment, and specific implementation may refer to the method embodiment, which is not described herein again.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the system and the apparatus described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In addition, in the description of the embodiments of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, which are used for illustrating the technical solutions of the present invention and not for limiting the same, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not depart from the spirit and scope of the embodiments of the present invention, and they should be construed as being included therein. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. A method for measuring the burning rate of a solid-liquid rocket engine is characterized by comprising the following steps:
acquiring three-dimensional original data;
reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images;
determining the length of each three-dimensional tangent plane layer image according to a preset calibration value;
calculating the axial solid fuel thickness of the explosive column after the engine test according to the length of the three-dimensional sectional layer images;
and calculating the burning speed of the solid-liquid rocket engine according to the thickness of the axial solid fuel of the explosive column after the engine is tested.
2. The method for measuring the burning rate of the solid-liquid rocket engine according to claim 1, wherein the reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images comprises:
inputting the three-dimensional original data into a back projection algorithm to obtain a three-dimensional model image;
and obtaining three-dimensional each section layer image according to the three-dimensional model image.
3. The method for measuring the burning rate of the solid-liquid rocket engine according to claim 1, wherein the determining the length of the three-dimensional section layer images according to a preset calibration value comprises:
determining the boundary of each three-dimensional tangent plane layer image;
and obtaining the length of each three-dimensional tangent plane layer image through the preset calibration value and the pixel size of each three-dimensional tangent plane layer image based on the boundary of each three-dimensional tangent plane layer image.
4. The method for measuring the burning rate of the solid-liquid rocket engine according to claim 1, wherein the step of calculating the burning rate of the solid-liquid rocket engine according to the thickness of the solid fuel in the axial direction of the grain after the engine test run comprises the following steps:
calculating the burning rate of the solid-liquid rocket engine according to the following formula:
wherein V is the burning speed of the solid-liquid rocket engine, 1 is the axial solid fuel thickness of the grain after the engine is tested, 2 is the preset axial solid fuel thickness of the grain before the engine is tested, and t is the ignition time.
5. A solid-liquid rocket engine burning rate measuring device is characterized by comprising:
an acquisition unit configured to acquire three-dimensional original data;
the reconstruction unit is used for reconstructing the three-dimensional original data to obtain three-dimensional sectional layer images;
the determining unit is used for determining the length of each three-dimensional tangent plane layer image according to a preset calibration value;
the thickness calculation unit is used for calculating the axial solid fuel thickness of the explosive column after the trial run of the engine according to the length of the three-dimensional sectional layer images;
and the burning rate calculation unit is used for calculating the burning rate of the solid-liquid rocket engine according to the thickness of the solid fuel in the axial direction of the explosive column after the engine is tested.
6. The apparatus for measuring combustion rate of a solid-liquid rocket engine according to claim 5, wherein said reconfiguration unit is specifically configured to:
inputting the three-dimensional original data into a back projection algorithm to obtain a three-dimensional model image;
and obtaining three-dimensional each section layer image according to the three-dimensional model image.
7. The apparatus for measuring combustion rate of a solid-liquid rocket engine according to claim 5, wherein said determining unit is specifically configured to:
determining the boundary of each three-dimensional tangent plane layer image;
and obtaining the length of each three-dimensional tangent plane layer image through the preset calibration value and the pixel size of each three-dimensional tangent plane layer image based on the boundary of each three-dimensional tangent plane layer image.
8. The apparatus for measuring combustion rate of a solid-liquid rocket engine according to claim 5, wherein said combustion rate calculating unit is specifically configured to:
calculating the burning rate of the solid-liquid rocket engine according to the following formula:
wherein V is the burning speed of the solid-liquid rocket engine, 1 is the axial solid fuel thickness of the grain after the engine is tested, 2 is the preset axial solid fuel thickness of the grain before the engine is tested, and t is the ignition time.
9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor implements the method of any of claims 1 to 4 when executing the computer program.
10. A computer-readable medium having non-volatile program code executable by a processor, wherein the program code causes the processor to perform the method of any of claims 1 to 4.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN112526058A (en) * | 2020-11-04 | 2021-03-19 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
| CN112526058B (en) * | 2020-11-04 | 2022-05-24 | 东南大学 | Small-thrust solid propellant grain combustion and propulsion performance detection test device |
| CN114810429A (en) * | 2022-04-11 | 2022-07-29 | 北京航空航天大学 | Device and method for measuring charge burning rate of solid-liquid rocket engine |
| CN114810429B (en) * | 2022-04-11 | 2024-01-19 | 北京航空航天大学 | Device and method for measuring explosive loading burning speed of solid-liquid rocket engine |
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