Propellant burning surface testing system and method based on double-view-angle X-ray imaging principle
By adopting the test system of the dual-view X-ray imaging principle in solid rocket engines, the problem that the existing technology cannot monitor the changes and defects in real time is solved, and the three-dimensional dynamic combustion surface removal test and accurate establishment of combustion models is achieved. Provides accurate test data for engine performance prediction.
Patent Information
- Application Number
- CN202411705046.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-26
- Publication Date
- 2025-02-11
AI Technical Summary
The prior art cannot monitor the generation and expansion of defects such as combustion surface changes and column cracks of solid rocket engines in real time, and cannot meet the requirements of accurate combustion profile testing during engine test.
Adopt propellant combustion surface testing system based on the principle of dual-view angle X-ray imaging, and consists of two sets of X-ray imaging systems with exactly the same design. The two sets of systems are arranged at an angle of 90° to realize the imaging of the engine combustion surface from two directions. .
Realize the three-dimensional dynamic combustion surface retraction test of solid rocket engines, obtain accurate test data of combustion retraction, accurately grasp the changes of the charging combustion surface, establish an accurate combustion model, and provide a foundation for accurate predictive modeling and model correction of engine performance. Test data.
Smart Images
Figure CN119413462A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of engine combustion surface testing, and in particular to a propellant combustion surface testing system and method based on the dual-viewing angle X-ray imaging principle. Background Art
[0002] At present, X-ray inspection of solid rocket engines is carried out by photography or CT after the charge is loaded. This traditional CT imaging mode cannot meet the detection of internal structural changes during the engine combustion process. During the operation of the engine, due to defects such as holes and cracks in the grain, the combustion surface will change, and it cannot burn according to the designed combustion surface, causing the internal ballistic curve to deviate from the design requirements. Moreover, during the operation of the engine, due to the high temperature and high pressure inside the combustion chamber and vibration, new defects will be generated in the grain, changing the shape of the combustion surface. Existing technical means cannot monitor the changes in the combustion surface of the grain in real time, as well as the generation and expansion of defects such as grain cracks during combustion, and cannot meet the needs of the overall engine design unit for accurate testing of the combustion profile during the engine test process. The combustion surface recession process of solid rocket engines directly determines its internal ballistic performance. Realizing quantitative measurement of the combustion surface recession process can effectively improve the prediction accuracy of the engine internal ballistics, which plays an important role in engine design.
[0003] At present, there are two methods for engine combustion surface testing: microwave testing and ultrasonic testing. The microwave testing method is based on the principle of radio frequency wireless measurement to carry out research on solid rocket engine test combustion surface regression test technology. According to the engine combustion surface regression attenuation characteristics, a multi-band multi-waveform test scheme is designed, and a corresponding test radio frequency link is established to scan and detect the change process of the solid rocket engine test combustion surface to obtain combustion surface regression test data. However, the microwave testing method can only be used for engines with fiberglass shells, and cannot be used for engines with other material shells.
[0004] The ultrasonic test method is to install an ultrasonic probe on the outside of the engine casing and emit ultrasonic waves to the charge at a certain trigger frequency. The ultrasonic waves pass through the casing, insulation layer, and charge in turn, propagating in the charge at the speed of sound, and are reflected after reaching the combustion surface. The reflected ultrasonic waves are still received by the probe, and the combustion surface position parameters can be measured by measuring the round-trip propagation time of the ultrasonic waves in the charge. However, the ultrasonic test method can only perform point testing and cannot achieve testing of the entire circumferential direction of the engine test position.
[0005] In view of the shortcomings of the above-mentioned propellant combustion surface testing method, the present invention proposes a propellant combustion surface testing system and method based on the principle of dual-view X-ray imaging, which can realize three-dimensional dynamic combustion surface recession test of solid rocket engines, obtain accurate test data of combustion recession, accurately grasp the changing law of charge combustion surface, establish an accurate combustion model, and provide basic test data for accurate prediction modeling and model correction of engine performance. Summary of the invention
[0006] The present invention proposes a propellant combustion surface testing system and method based on the dual-view X-ray imaging principle to solve the technical problems that the dynamic combustion surface of a solid rocket engine cannot be detected in real time or the detection is inaccurate.
[0007] In order to achieve the above object, the present invention solves the above technical problems through the following technical solutions:
[0008] A propellant combustion surface testing system based on the dual-view X-ray imaging principle, the testing system comprising:
[0009] X-ray imaging systems based on image intensifiers and high-speed cameras;
[0010] Based on a dual-view X-ray combustion surface dynamic test system, the combustion surface dynamic test system consists of two sets of X-ray imaging systems based on image intensifiers and high-speed cameras with exactly the same design, and the two systems are arranged at a 90° angle to each other.
[0011] The X-ray imaging system based on an image intensifier and a high-speed camera consists of an X-ray source, an image intensifier, and a high-speed camera.
[0012] The X-ray source emits X-rays, the image intensifier is used to receive the X-rays and enhance the brightness of the image, and the high-speed camera is used to receive visible light image signals.
[0013] A propellant burning surface testing method based on the principle of dual-view X-ray imaging, the testing method comprising the following steps:
[0014] S1: Construct an X-ray imaging system based on an image intensifier and a high-speed camera, wherein the image intensifier is coupled to the high-speed camera using a flange coupling spacing test method;
[0015] S2: Construct a propellant combustion surface test system based on the principle of dual-view X-ray imaging, using two sets of ray source-image intensifier-high-speed camera systems at 90 degrees to each other to achieve imaging of the engine combustion surface from two directions.
[0016] The transmission process of the image data stream in the X-ray imaging system is as follows: the X-ray source emits rays, which are attenuated to varying degrees after passing through the solid rocket engine. The image intensifier receives the attenuated X-rays and converts them into electronic image signals. The electronic image signals are transmitted to the enhancement unit, which applies a strong electric field to the electrons through the electron optical system therein, so that the electrons gain energy, thereby accelerating the electron beam emitted by the photocathode and focusing it on the fluorescent screen, thereby enhancing the image brightness. After passing through the electronic lens, the enhanced image data will be emitted as a visible light image signal.
[0017] The visible light image signal will be directly received by the high-speed camera. After receiving the visible light image signal, the high-speed camera will decode it through the modulation circuit and convert it into a data electrical signal. Finally, it will be converted into a data stream that meets the interface communication protocol through the data interface and transmitted to the host computer for storage, processing, reconstruction, etc.
[0018] When the image intensifier is coupled to a high-speed camera, the optimal distance range for deploying the high-speed camera is 10 mm to 70 mm, the center resolution is 34 Lp / mm to 50 Lp / mm, and the optimal flange fixing distance range is 110 mm to 170 mm.
[0019] The inner diameter of the transmission space inside the flange ranges from 90 mm to 110 mm.
[0020] The material of the flange is selected from engineering plastics, aluminum alloy, and Q235 steel, preferably Q235 steel.
[0021] Based on the implementation of the above technical solution, the present invention can achieve the following technical effects:
[0022] 1. The present invention provides a propellant combustion surface testing system and method based on the principle of dual-view X-ray imaging. The system is composed of two sets of X-ray imaging systems, which are arranged at a 90° angle to image the combustion surface of the engine from two directions. This can avoid superimposed imaging of engine structural information and feature occlusion, and realize three-dimensional dynamic combustion surface regression testing of solid rocket engines.
[0023] 2. The present invention provides a propellant combustion surface testing system and method based on the principle of dual-view X-ray imaging. The image intensifier and the high-speed camera are coupled using a flange coupling spacing test method, which can ensure the coupling accuracy of the image intensifier and the high-speed camera and ensure the accuracy of the test results.
[0024] 3. The present invention provides a propellant combustion surface testing system and method based on the principle of dual-view X-ray imaging, which uses X-ray detection technology to test the combustion surface of engines with shells made of all materials such as fiberglass, carbon fiber, and metal. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0026] Figure 1It is a schematic diagram of the process of acquiring the X-ray imaging image of the combustion surface of the engine provided by the present invention;
[0027] Figure 2 This is a design diagram of a test of the flange coupling distance between an image intensifier and a high-speed camera provided by the present invention;
[0028] Figure 3 It is a schematic diagram of the coupling structure of the image intensifier and the high-speed camera provided by the present invention;
[0029] Figure 4 It is a schematic diagram of the orthogonal arrangement of an X-ray imaging system based on an image intensifier and a high-speed camera provided by the present invention;
[0030] Figure 5 It is a design diagram of a dual-viewing angle X-ray combustion surface dynamic testing system provided by the present invention. DETAILED DESCRIPTION
[0031] The following embodiments of the present invention are described in further detail in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.
[0032] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limitations on the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.
[0033] In the description of the embodiments of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present invention can be understood according to specific circumstances.
[0034] In the embodiments of the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.
[0035] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.
[0036] Combine the following Figure 1-Figure 5 A propellant combustion surface testing system and method based on the dual-view X-ray imaging principle provided by the present invention are introduced in detail:
[0037] Combination Figure 1 As shown, in an embodiment of the present invention, a propellant combustion surface testing system based on the dual-view X-ray imaging principle includes:
[0038] X-ray imaging systems based on image intensifiers and high-speed cameras;
[0039] Based on a dual-view X-ray combustion surface dynamic test system, the combustion surface dynamic test system consists of two sets of X-ray imaging systems based on image intensifiers and high-speed cameras with exactly the same design, and the two systems are arranged at a 90° angle to each other.
[0040] Furthermore, the X-ray imaging system based on the image intensifier and the high-speed camera is composed of an X-ray source, an image intensifier, and a high-speed camera.
[0041] Combination Figure 2 As shown, the image intensifier is coupled to the high-speed camera using a flange coupling distance test method, which can ensure the coupling accuracy of the image intensifier and the high-speed camera and ensure the accuracy of the test results.
[0042] Furthermore, the X-ray source emits X-rays, the image intensifier is used to receive the X-rays and enhance the brightness of the image, and the high-speed camera is used to receive visible light image signals.
[0043] Furthermore, an image intensifier is used to convert the X-rays attenuated by the engine into visible light signals, and then a high-speed camera is used to convert the visible light signals into image data output.
[0044] Furthermore, the construction of the dual-view X-ray combustion surface dynamic test system is based on two sets of ray source-image intensifier-high-speed camera systems at 90° to each other, so as to realize the imaging of the engine combustion surface from two directions, thereby avoiding the superposition imaging of the engine structure information and causing feature occlusion.
[0045] Combination Figure 5 As shown, a test method for a propellant combustion surface test system based on the dual-view X-ray imaging principle comprises the following steps:
[0046] S1: Construct an X-ray imaging system based on an image intensifier and a high-speed camera, wherein the image intensifier is coupled to the high-speed camera using a flange coupling spacing test method;
[0047] S2: Construct a propellant combustion surface test system based on the principle of dual-view X-ray imaging, using two sets of ray source-image intensifier-high-speed camera systems at 90 degrees to each other to achieve imaging of the engine combustion surface from two directions.
[0048] Furthermore, in the acquisition of the X-ray imaging image of the combustion surface of the engine in S1, the X-ray source emits rays, which are attenuated to varying degrees after passing through the solid rocket engine. The X-ray receiving screen of the image intensifier receives the attenuated X-rays and converts them into electronic image signals. The electronic image signals are transmitted to the enhancement unit, which applies a strong electric field to the electrons through the electron optical system therein, so that the electrons gain energy, thereby accelerating the electron beam emitted by the photocathode and focusing the image on the fluorescent screen, thereby enhancing the image brightness and making the fluorescent screen emit stronger light energy. After passing through the electronic lens, the enhanced image data will be emitted as a visible light image signal.
[0049] In the system, after the image intensifier and the high-speed camera are coupled, the visible light image signal emitted by the image intensifier screen will be directly received by the high-speed camera. After receiving the visible light image data signal, the high-speed camera will decode it through the modulation circuit and convert it into a data electrical signal. Finally, it will be converted into a data stream that meets the interface communication protocol through the data interface and transmitted to the host computer for storage, processing, reconstruction, etc.
[0050] Combination Figure 2 , Figure 3As shown, in S1, the image intensifier is coupled to the high-speed camera, and the coupling between the image intensifier and the high-speed camera is carried out by the flange coupling distance test method to determine the imaging distance and other related parameters. The specific coupling steps are as follows:
[0051] ① Determine the best placement distance for high-speed cameras. Use high-speed cameras to test the imaging results at different distances, and the best placement distance for high-speed cameras corresponding to the best imaging effect is 10mm to 70mm.
[0052] ② Determine the optimal parameters of the intensifier. Adjust the output image diameter of the intensifier to 25 mm and the center resolution to 34 Lp / mm to 50 Lp / mm.
[0053] ③ Determine the optimal flange fixing distance. Research on different flange fixing distances was conducted and the optimal flange fixing distance was determined to be 110mm to 170mm;
[0054] ④ Determine the flange diameter. Conduct a comparative test on the flange inner diameter, adjust different flange inner diameters for actual imaging tests, and determine that the flange inner diameter range is 90mm to 110mm.
[0055] ⑤ Determine the flange material. Use flanges of different material types for the actual imaging process, select the material type with the least impact on the imaging, and achieve the best imaging effect. Determine Q235 steel as the final flange material. Flange materials can also be selected from engineering plastics, aluminum alloys, etc.
[0056] After completing the above steps, the coupling process of the image intensifier and the high-speed camera is realized.
[0057] Furthermore, S2 constructed a propellant combustion surface test system based on the principle of dual-view X-ray imaging.
[0058] Combination Figure 4 As shown, two sets of ray source-image intensifier-high-speed camera systems are arranged orthogonally at 90 degrees to construct a propellant combustion surface test system based on the dual-view X-ray imaging principle.
[0059] For CT imaging, projections from multiple perspectives need to be obtained for reconstruction, mainly to avoid superimposed imaging of the structural information of the detected object in a single perspective, which would cause feature occlusion and make reconstruction impossible. As the number of perspectives increases, the occlusion problem of projection information from a single perspective will be effectively suppressed.
[0060] The present invention has completed the static test simulation verification of the engine cross-section under a single viewing angle. The system is used to collect projection data of the manufactured propellant grains from two directions perpendicular to each other. The reconstructed combustion surface image has a similarity of more than 95% with the real object, verifying the feasibility of the engine propellant combustion surface X-ray test method and test system.
[0061] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims
1. A propellant combustion surface testing system based on the principle of dual-view X-ray imaging, characterized in that: The test system comprises: X-ray imaging systems based on image intensifiers and high-speed cameras; Based on a dual-view X-ray combustion surface dynamic test system, the combustion surface dynamic test system consists of two sets of X-ray imaging systems based on image intensifiers and high-speed cameras with exactly the same design, and the two systems are arranged at a 90° angle to each other.
2. The propellant combustion surface testing system based on the dual-view X-ray imaging principle according to claim 1 is characterized in that: The X-ray imaging system based on an image intensifier and a high-speed camera consists of an X-ray source, an image intensifier, and a high-speed camera.
3. The propellant combustion surface testing system based on the dual-view X-ray imaging principle according to claim 2 is characterized in that: The X-ray source emits X-rays, the image intensifier is used to receive the X-rays and enhance the brightness of the image, and the high-speed camera is used to receive visible light image signals.
4. A testing method using the propellant burning surface testing system based on the dual-view X-ray imaging principle as claimed in any one of claims 1 to 3, characterized in that: The test method comprises the following steps: S1: Construct an X-ray imaging system based on an image intensifier and a high-speed camera, wherein the image intensifier is coupled to the high-speed camera using a flange coupling spacing test method; S2: Construct a propellant combustion surface test system based on the principle of dual-view X-ray imaging, using two sets of ray source-image intensifier-high-speed camera systems at 90 degrees to each other to achieve imaging of the engine combustion surface from two directions.
5. The propellant burning surface testing method based on the dual-view X-ray imaging principle according to claim 4 is characterized in that: The transmission process of the image data stream in the X-ray imaging system is as follows: the X-ray source emits rays, which are attenuated to varying degrees after passing through the solid rocket engine. The image intensifier receives the attenuated X-rays and converts them into electronic image signals. The electronic image signals are transmitted to the enhancement unit, which applies a strong electric field to the electrons through the electron optical system therein, so that the electrons gain energy, thereby accelerating the electron beam emitted by the photocathode and focusing it on the fluorescent screen, thereby enhancing the image brightness. After passing through the electronic lens, the enhanced image data will be emitted as a visible light image signal.
6. The propellant burning surface testing method based on the dual-view X-ray imaging principle according to claim 5 is characterized in that: The visible light image signal will be directly received by the high-speed camera. After receiving the visible light image signal, the high-speed camera will decode it through the modulation circuit and convert it into a data electrical signal. Finally, it will be converted into a data stream that meets the interface communication protocol through the data interface and transmitted to the host computer for storage, processing, reconstruction, etc.
7. The propellant burning surface testing method based on the dual-view X-ray imaging principle according to claim 6 is characterized in that: When the image intensifier is coupled to a high-speed camera, the optimal distance range for deploying the high-speed camera is 10 mm to 70 mm, the center resolution is 34 Lp / mm to 50 Lp / mm, and the optimal flange fixing distance range is 110 mm to 170 mm.
8. The propellant burning surface testing method based on the dual-view X-ray imaging principle according to claim 7 is characterized in that: The inner diameter of the transmission space inside the flange ranges from 90 mm to 110 mm.
9. The propellant burning surface testing method based on the dual-view X-ray imaging principle according to claim 8, characterized in that: The material of the flange is selected from one of engineering plastics, aluminum alloy, and Q235 steel, preferably Q235 steel.