Compatibility test methods for permeate with launch vehicle propellant tanks and aerospace media

Abstract

This invention provides a compatibility test method for a permeate with a launch vehicle propellant tank and aerospace media, comprising: step S1: sample preparation; step S2: weighing and observing the sample before permeate testing; step S3: performing permeate testing on the sample; step S4: weighing and observing the sample after permeate testing; step S5: analyzing the compatibility between the permeate and the launch vehicle propellant tank sample; step S6: immersing the sample with residual permeate in the aerospace media; step S7: weighing and observing the sample after immersion; step S8: analyzing the changes in the mass and appearance of the sample before and after immersion; by analyzing the changes in the mass and appearance of the sample after permeate testing before and after immersion in the aerospace media, the compatibility of the sample after permeate testing with the aerospace media can be analyzed.

Description

Technical Field

[0001] This invention belongs to the field of permeation testing compatibility testing, specifically, it relates to a method for testing the compatibility of permeate with launch vehicle tanks and aerospace media, and more particularly to a method for testing the compatibility of permeate with launch vehicle tanks and aerospace media. Background Technology

[0002] Penetrant testing is a commonly used method for detecting surface defects in the welds of launch vehicle propellant tanks. The penetrant testing process includes pre-cleaning, penetrant testing, removal of excess penetrant, drying, development, inspection, and post-processing. However, during the penetrant testing stage, due to the extremely strong penetrant's penetrating power, it is difficult to completely remove excess penetrant during the removal process. This can be caused by open defects or uneven surfaces, leading to potential incompatibility issues between the residual penetrant and the launch vehicle propellant tank, as well as between the tank and the contained medium after penetrant testing. Currently, there is a lack of compatibility testing methods for penetrant testing related to the penetrant, the launch vehicle propellant tank, and the contained medium after penetrant testing.

[0003] Currently, the relevant existing technologies include:

[0004] The patent document JP2530194B2 discloses a penetrant testing method and a cleaning agent used in the testing method for products with rough surfaces. It primarily provides a penetrant testing method and a suitable cleaning agent for products with rough surfaces. However, the penetrant testing method itself is not suitable for porous products. This technical solution proposes a cleaning agent, describing it as capable of cleaning porous and rough surfaces. The cleaning agent has a pH value of 2.0-4.5, which is acidic. Since aerospace tanks are primarily made of aluminum, a chemical reaction would occur. Furthermore, this technical solution describes its applicability to porous ceramic products and cast products with casting skin, requiring acidic solutions for cleaning, sometimes even secondary cleaning. This is unsuitable for aerospace tanks. Moreover, this technical solution does not investigate whether the residual acid after cleaning with the cleaning agent will react with the tank or the medium contained within it.

[0005] Therefore, to address the lack of experimental methods, a compatibility test method for the permeate with the launch vehicle tank and aerospace media is proposed. Summary of the Invention

[0006] In view of the deficiencies in the prior art, the purpose of this invention is to provide a method for testing the compatibility of permeate with launch vehicle tanks and aerospace media.

[0007] The compatibility test method for permeate with launch vehicle tanks and aerospace media provided by the present invention includes:

[0008] Step S1: Sample preparation;

[0009] Step S2: Weigh and observe the sample before penetrant testing;

[0010] Step S3: Perform a penetrant test on the sample;

[0011] Step S4: After the penetration test, weigh and observe the sample;

[0012] Step S5: Analyze the compatibility between the permeate and the rocket propellant tank sample;

[0013] Step S6: Immerse the sample containing residual permeate in aerospace medium;

[0014] Step S7: Weigh and observe the sample after soaking;

[0015] Step S8: Analyze the changes in the mass and appearance of the sample before and after immersion.

[0016] Preferably, in step S1, the material of the sample is the same as that of the launch vehicle tank, the diameter of the sample is 25-30 mm, the thickness is 2.0-5.0 mm, and through holes with a diameter of 2-8 mm are made on the sample to allow for appropriate residue when removing permeate; the surface of the sample is machined to remove burrs and has a smooth surface.

[0017] Preferably, in step S2, the sample surface is first cleaned with ethanol to remove impurities such as grease and powder, then thoroughly rinsed with distilled water and placed in an oven to dry with circulating hot air. After drying, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (denoted as a1). The appearance of the sample is then observed using a metallographic microscope at magnifications of 20x and 100x, and photographs are taken to record the appearance. The sample is then placed in a dust bag to prevent corrosion or contamination.

[0018] Preferably, in step S3, the sample is subjected to penetrant testing according to the penetrant testing steps, which includes the following basic steps: penetrant testing, removal of excess penetrant from the surface, drying, and development; the sample after penetrant testing is placed in a dust bag to prevent corrosion or contamination.

[0019] Preferably, in step S4, after the penetrant test, the sample is weighed / observed. On the 5th day after the penetrant test, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (denoted as a2). Then, the appearance of the sample is observed using a metallographic microscope at magnifications of 20x and 100x, respectively, and the appearance is photographed and recorded.

[0020] Preferably, step S5 includes:

[0021] Step S5.1: Analyze the mass change; compare the two weighing results before and after the penetrant test, and calculate the percentage change in mass before and after the penetrant test (denoted as b1). The calculation formula is as follows:

[0022]

[0023] Step S5.2: Analyze the changes in appearance; analyze the consistency of the sample surface in 20x and 100x magnification photographs before and after penetration, and check whether corrosion or rust appears on the sample surface after penetration.

[0024] Step S5.3: Comprehensive analysis; if the mass change rate of the sample before and after the permeation test is between -0.03% and 0.03%, and the appearance of the sample does not change significantly before and after the permeation test, then it is determined that the permeate is compatible with the rocket tank sample.

[0025] Preferably, in step S6, the sample that has undergone penetrant testing is immersed in an aerospace medium, and step S6 includes:

[0026] Step S6.1: Immerse the sample after the permeation test in conventional aerospace media such as liquid hydrogen, liquid oxygen, nitrogen tetroxide, methylhydrazine, and anhydrous hydrazine.

[0027] Step S6.2: Immersion time calculation method; First, conduct a 1-day (24-hour) immersion test to calculate the annual corrosion rate. When the corrosion rate V = 0.1~1.0 mm / year, the recommended immersion time is 3~7 days.

[0028] Step S6.3: Select ground glass bottles to hold the medium and sample. The soaking process should be controlled according to the corresponding protective measures for each medium.

[0029] Step S6.4: After soaking for 3 to 7 days, take it out, wash it, and dry it.

[0030] Preferably, in step S7, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (denoted as a3), and the appearance of the sample is observed using a metallographic microscope at magnifications of 20x and 100x respectively, and the appearance is recorded by taking pictures; the sample is placed in a dust bag to prevent corrosion or contamination.

[0031] Preferably, in step S8, the changes in the mass and appearance of the sample after penetration testing before and after immersion in the aerospace medium are analyzed, thereby analyzing whether the sample after penetration testing is compatible with the aerospace medium.

[0032] Preferably, step S8 includes:

[0033] Step S8.1: Analyze the change in mass: Compare the weighing results before and after soaking, and calculate the percentage change in mass before and after soaking (denoted as b2). The calculation formula is as follows:

[0034]

[0035] Step S8.2: Analyze the changes in appearance: Analyze the consistency of the sample surface in 20x and 100x magnification photographs before and after immersion, and check whether corrosion or rust appears on the sample surface before and after immersion.

[0036] Step S8.3: Comprehensive analysis; if the mass change rate of the sample before and after immersion is between -0.03% and 0.03%, and the appearance of the sample does not change significantly before and after immersion, then it is determined that the rocket propellant tank sample is compatible with the aerospace medium.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. In view of the lack of compatibility testing for aerospace penetrants in the existing technology, this invention proposes a reliable and simple compatibility testing method that is easy to operate and highly efficient.

[0039] 2. By comparing and analyzing the changes in mass and appearance of the sample before and after permeation and before and after immersion in the medium, this invention can quantitatively assess the compatibility of the permeate with the rocket tank and aerospace cutoff, and has high engineering application value. Attached Figure Description

[0040] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0041] Figure 1 This is a flowchart illustrating the implementation of the present invention.

[0042] Figure 2 This is a schematic diagram showing the shape and size of the sample of the present invention.

[0043] Figure 3 These are comparative images of samples before and after penetrant testing under a metallographic microscope at 20x and 100x magnification, respectively, according to an embodiment of the present invention. Detailed Implementation

[0044] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0045] like Figures 1 to 3 As shown, this embodiment of the invention provides a method for testing the compatibility of a permeate with a launch vehicle propellant tank and aerospace media, comprising:

[0046] Step S1: Sample preparation;

[0047] Step S2: Weigh and observe the sample before penetrant testing;

[0048] Step S3: Perform a penetrant test on the sample;

[0049] Step S4: After the penetration test, weigh and observe the sample;

[0050] Step S5: Analyze the compatibility between the permeate and the rocket propellant tank sample;

[0051] Step S6: Immerse the sample containing residual permeate in aerospace medium;

[0052] Step S7: Weigh and observe the sample after soaking;

[0053] Step S8: Analyze the changes in the mass and appearance of the sample before and after immersion; analyze the changes in the mass and appearance of the sample after penetrant testing before and after immersion in the aerospace medium, thereby analyzing whether the sample after penetrant testing is compatible with the aerospace medium.

[0054] Furthermore, in step S1, the material of the sample is the same as that of the launch vehicle tank. The diameter of the sample is 25-30 mm and the thickness is 2.0-5.0 mm. At the same time, through holes with a diameter of 2-8 mm are made on the sample to allow for appropriate residue when removing the permeate. The surface of the sample is machined to remove burrs and has a smooth surface.

[0055] In step S2, the sample surface is first cleaned with ethanol to remove impurities such as grease and powder. Then, the sample is thoroughly rinsed with distilled water and placed in an oven to dry with circulating hot air. After drying, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (recorded as a1). The appearance of the sample is then observed using a metallographic microscope at magnifications of 20x and 100x, and photographs are taken to record the appearance. The sample is then placed in a dust bag to prevent corrosion or contamination.

[0056] In step S3, the sample is subjected to penetrant testing according to the penetrant testing procedure, which includes the following basic steps: penetrant testing, removal of excess penetrant from the surface, drying, and development; the sample after penetrant testing is placed in a dust bag to prevent corrosion or contamination.

[0057] In step S4, after the penetrant test, the sample is weighed / observed. On the 5th day after the penetrant test, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (recorded as a2). Then, the appearance of the sample is observed using a metallographic microscope at magnifications of 20x and 100x, and the appearance is photographed and recorded.

[0058] Further, step S5 includes:

[0059] Step S5.1: Analyze the mass change; compare the two weighing results before and after the penetrant test, and calculate the percentage change in mass before and after the penetrant test (denoted as b1). The calculation formula is as follows:

[0060]

[0061] Step S5.2: Analyze the changes in appearance; analyze the consistency of the sample surface in 20x and 100x magnification photographs before and after penetration, and check whether corrosion or rust appears on the sample surface after penetration.

[0062] Step S5.3: Comprehensive analysis; if the mass change rate of the sample before and after the permeation test is between -0.03% and 0.03%, and the appearance of the sample does not change significantly before and after the permeation test, then it is determined that the permeate is compatible with the rocket tank sample.

[0063] In step S6, the sample that has undergone penetrant testing is immersed in an aerospace medium. Step S6 includes:

[0064] Step S6.1: Immerse the sample after the permeation test in conventional aerospace media such as liquid hydrogen, liquid oxygen, nitrogen tetroxide, methylhydrazine, and anhydrous hydrazine.

[0065] Step S6.2: Immersion time calculation method; First, conduct a 1-day (24-hour) immersion test to calculate the annual corrosion rate. When the corrosion rate V = 0.1~1.0 mm / year, the recommended immersion time is 3~7 days.

[0066] Step S6.3: Select ground glass bottles to hold the medium and sample. The soaking process should be controlled according to the corresponding protective measures for each medium.

[0067] Step S6.4: After soaking for 3 to 7 days, take it out, wash it, and dry it.

[0068] In step S7, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (denoted as a3), and the appearance of the sample is observed using a metallographic microscope at magnifications of 20x and 100x respectively, and the appearance is photographed and recorded; the sample is placed in a dust bag to prevent corrosion or contamination.

[0069] Step S8 includes:

[0070] Step S8.1: Analyze the change in mass: Compare the weighing results before and after soaking, and calculate the percentage change in mass before and after soaking (denoted as b2). The calculation formula is as follows:

[0071]

[0072] Step S8.2: Analyze the changes in appearance: Analyze the consistency of the sample surface in 20x and 100x magnification photographs before and after immersion, and check whether corrosion or rust appears on the sample surface before and after immersion.

[0073] Step S8.3: Comprehensive analysis; if the mass change rate of the sample before and after immersion is between -0.03% and 0.03%, and the appearance of the sample does not change significantly before and after immersion, then it is determined that the rocket propellant tank sample is compatible with the aerospace medium.

[0074] In summary, the embodiments of the present invention provide a compatibility test method for a permeate with a launch vehicle propellant tank and aerospace media. The test method includes sample preparation, weighing and observing the sample before permeation testing, performing permeation testing on the sample, weighing and observing the sample after permeation testing, analyzing the compatibility between the permeate and the launch vehicle propellant tank sample, immersing the permeation-tested sample in aerospace media, weighing and observing the sample after immersion, and analyzing the changes in the mass and appearance of the permeation-tested sample before and after immersion in aerospace media, thereby analyzing whether the permeation-tested sample is compatible with the aerospace media.

[0075] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for testing the compatibility of a permeate with a launch vehicle propellant tank and aerospace media, characterized in that, include: Step S1: Sample preparation; Step S2: Weigh and observe the sample before penetrant testing; Step S3: Perform a penetrant test on the sample; Step S4: After the penetration test, weigh and observe the sample; Step S5: Analyze the compatibility between the permeate and the rocket propellant tank sample; Step S6: Immerse the sample containing residual permeate in aerospace medium; Step S7: Weigh and observe the sample after soaking; Step S8: Analyze the changes in the mass and appearance of the sample before and after immersion; In step S2, the sample surface is first cleaned with ethanol to remove impurities, then thoroughly rinsed with distilled water and placed in an oven to dry with circulating hot air. After drying, the sample is weighed using a high-precision balance with an accuracy of 0.0001g and recorded as a1. The appearance of the sample is then observed using a metallographic microscope at magnifications of 20x and 100x, and photographs are taken to record the appearance. The sample is then placed in a dust bag to prevent corrosion or contamination. In step S4, after the penetration test, the sample is weighed and observed. On the 5th day after the penetration test, the sample is weighed using a high-precision balance with an accuracy of 0.0001g and recorded as a2. Then, the appearance of the sample is observed using a metallographic microscope at magnifications of 20x and 100x respectively, and the appearance is photographed and recorded. Step S5 includes: Step S5.1: Analyze the mass change; compare the two weighing results before and after the penetrant test, calculate the percentage change in mass before and after the penetrant test, and denot it as b1. The calculation formula is as follows: Step S5.2: Analyze the changes in appearance; analyze the consistency of the sample surface in 20x and 100x magnification photographs before and after penetration, and check whether corrosion or rust appears on the sample surface after penetration. Step S5.3: Comprehensive analysis; If the mass change rate of the sample before and after the permeation test is between -0.03% and 0.03%, and the appearance of the sample does not change significantly before and after the permeation test, then it is determined that the permeate is compatible with the rocket tank sample. In step S7, the sample is weighed using a high-precision balance with an accuracy of 0.0001g and recorded as a3. The appearance of the sample is then observed using a metallographic microscope at magnifications of 20x and 100x, and photographs are taken to record the appearance. The sample is then placed in a dust bag to prevent corrosion or contamination. Step S8 includes: Step S8.1: Analyze the change in mass: Compare the weighing results before and after soaking, and calculate the percentage change in mass before and after soaking, denoted as b2. The calculation formula is as follows: Step S8.2: Analyze the changes in appearance: Analyze the consistency of the sample surface in 20x and 100x magnification photos before and after immersion, and check whether corrosion or rust appears on the sample surface before and after immersion. Step S8.3: Comprehensive analysis; if the mass change rate of the sample before and after immersion is between -0.03% and 0.03%, and the appearance of the sample does not change significantly before and after immersion, then it is determined that the rocket propellant tank sample is compatible with the aerospace medium.

2. The compatibility test method for the permeate with the launch vehicle propellant tank and aerospace media according to claim 1, characterized in that, In step S1, the material of the sample is the same as that of the launch vehicle tank. The diameter of the sample is 25-30 mm and the thickness is 2.0-5.0 mm. At the same time, through holes with a diameter of 2-8 mm are made on the sample to allow for appropriate residue when removing the permeate. The surface of the sample is machined to remove burrs and make the surface smooth.

3. The compatibility test method for the permeate with the launch vehicle propellant tank and aerospace media according to claim 1, characterized in that, In step S3, the sample is subjected to penetrant testing according to the penetrant testing procedure, which includes the following basic steps: penetrant testing, removal of excess penetrant from the surface, drying, and development; the sample after penetrant testing is placed in a dust bag to prevent corrosion or contamination.

4. The compatibility test method for the permeate with the launch vehicle propellant tank and aerospace medium according to claim 1, characterized in that, In step S6, the sample that has undergone penetrant testing is immersed in an aerospace medium. Step S6 includes: Step S6.1: Immerse the above-mentioned sample that has undergone penetrant testing in a conventional aerospace medium; Step S6.2: Calculation method for immersion time; First, conduct a 24-hour immersion test to calculate the annual corrosion rate. When the corrosion rate V = 0.1~1.0 mm / year, the recommended immersion time is 3~7 days. Step S6.3: Select ground glass bottles to hold the medium and samples. The immersion process should be controlled according to the corresponding protective measures for each medium. Step S6.4: After soaking for 3 to 7 days, take it out, wash it, and dry it.

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