Compatibility test method for penetrating fluid, carrier rocket storage tank and spaceflight medium

Abstract

The invention provides a compatibility test method for penetrating fluid, a carrier rocket storage tank and a spaceflight medium. The compatibility test method comprises the following steps: S1, manufacturing a sample; s2, weighing and observing the sample before penetration detection; s3, performing penetration detection on the sample; s4, weighing and observing the sample after penetration detection; s5, analyzing the compatibility condition of the penetrating fluid and the carrier rocket storage tank sample; s6, soaking the sample with the residual penetrating fluid in a spaceflight medium; step S7, weighing and observing the soaked sample; s8, analyzing the quality appearance change condition of the sample before and after soaking; and analyzing the quality appearance change condition of the sample subjected to penetration detection before and after being soaked in the spaceflight medium so as to analyze whether the sample subjected to penetration detection is compatible with the spaceflight medium.

Description

Technical Field

[0001] The present invention belongs to the field of penetrant detection compatibility testing, and specifically relates to a compatibility testing method for a penetrant with a carrier rocket tank and a space medium, and especially relates to a compatibility testing method for a penetrant with a carrier rocket tank and a space medium. Background Art

[0002] Penetrant testing is a common method for detecting surface defects in launch vehicle tank welds. The penetrant testing process includes pre-cleaning, penetration, removal of excess penetrant, drying, imaging, inspection, and post-processing. During the penetration step, the penetrant has a strong penetrant capacity. During the removal of excess penetrant, due to surface defects or structural unevenness, the penetrant is difficult to clean completely. This can lead to potential incompatibility between the residual penetrant and the launch vehicle tank, as well as between the tank and the medium it contains after penetrant testing. However, there is currently a lack of compatibility testing methods for penetrant testing penetrants, launch vehicle tanks, and the medium contained in the tank after penetrant testing.

[0003] Currently, the relevant existing technologies are: Penetrant Testing Method for Testing Rough Surfaces and Cleaning Agent Used in the Testing Method (Patent Document JP2530194B2) This patent document discloses a penetrant testing method for testing rough surfaces and a cleaning agent used in the testing method. It primarily provides a penetrant testing method and a cleaning agent suitable for use with rough surfaces. The penetrant testing method itself is not suitable for products with porous surfaces. The technical solution proposes a cleaning agent that can clean porous and rough surfaces. The pH value of the cleaning agent is 2.0-4.5, which is acidic. Space tanks are primarily made of aluminum, which can react chemically. The technical solution also states that it can be used for porous ceramic products and cast products with cast skins. Cleaning the products with an acidic solution may even require a secondary cleaning, making it unsuitable for space tanks. Furthermore, the technical solution does not investigate whether the acid residue remaining after cleaning with the cleaning agent will react with the tank or the media contained within it.

[0004] Therefore, in order to solve the problem of lack of test methods, a compatibility test method for penetrants with launch vehicle tanks and aerospace media was proposed. Summary of the Invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a compatibility test method for penetrants with launch vehicle tanks and aerospace media.

[0006] The compatibility test method of the penetrant with the carrier rocket tank and aerospace medium provided by the present invention includes: Step S1: sample preparation; Step S2: weighing and observing the sample before the penetration test; Step S3: performing a penetration test on the sample; Step S4: weighing and observing the sample after the penetration test; Step S5: analyzing the compatibility of the permeate with the launch vehicle tank sample; Step S6: immersing the sample with the remaining penetrant in aerospace medium; Step S7: weighing and observing the sample after immersion; Step S8: Analyze the changes in the quality and appearance of the sample before and after immersion.

[0007] Preferably, in step S1, the material of the sample is consistent with the material of the carrier rocket tank, the diameter of the sample is 25 to 30 mm, and the thickness is 2.0 to 5.0 mm. At the same time, a through hole with a diameter of 2 to 8 mm is made on the sample to have appropriate residue when removing the penetrant; the surface state of the test piece is machined to remove burrs and the surface is smooth.

[0008] Preferably, in step S2, the sample is first cleaned with ethanol to remove impurities such as grease and powder on the surface of the sample, and 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 with a high-precision balance with an accuracy of 0.0001g (denoted as a1), and then the appearance of the sample is observed with a metallographic microscope at magnifications of 20 times and 100 times, respectively, and photographed to record the appearance; the sample is placed in a dust bag to prevent corrosion or contamination.

[0009] Preferably, in step S3, the sample is subjected to a penetration test according to the penetration test steps, which includes the following basic steps: penetration, removal of excess penetrant on the surface, drying, and imaging; and the sample after the penetration test is placed in a dustproof bag to prevent corrosion or contamination.

[0010] Preferably, in step S4, the sample is weighed / observed after the penetrant test. 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), and then the appearance of the sample is observed using a metallographic microscope at magnifications of 20 times and 100 times, respectively, and photographs are taken to record the appearance.

[0011] Preferably, the step S5 includes: Step S5.1: Analyze mass changes; compare the two weighing results before and after the penetrant test, and calculate the mass change percentage before and after the penetrant test (denoted as b1). The calculation formula is as follows:

[0012] Step S5.2: Analyze changes in appearance; analyze the consistency of the sample surface under 20x and 100x magnification before and after penetration, and check whether there is any corrosion or rust on the sample surface after penetration; Step S5.3: Comprehensive analysis: If the mass change rate of the sample before and after the penetrant test is between -0.03% and 0.03%, and there is no obvious change in the appearance of the sample before and after the penetrant test, it is determined that the penetrant is compatible with the launch vehicle tank sample.

[0013] Preferably, in step S6, the sample that has undergone the penetration test is immersed in a spaceflight medium, and step S6 includes: Step S6.1: Immerse the sample after the penetration test in a conventional aerospace medium such as liquid hydrogen, liquid oxygen, nitrogen tetroxide, methylhydrazine, or anhydrous hydrazine; Step S6.2: Calculation method for immersion time: 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. Step S6.3: Use ground-mouth glass bottles to hold the medium and specimens. 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 out, wash and dry.

[0014] Preferably, in step S7, the sample is weighed using a high-precision balance with an accuracy of 0.0001 g (denoted as a3), and then the appearance of the sample is observed using a metallographic microscope at magnifications of 20 times and 100 times, respectively, and photographed to record the appearance; the sample is placed in a dustproof bag to prevent corrosion or contamination.

[0015] Preferably, in step S8, the changes in quality and appearance of the sample that has undergone the penetration test before and after being immersed in the aerospace medium are analyzed, so as to analyze whether the sample that has undergone the penetration test is compatible with the aerospace medium.

[0016] Preferably, step S8 includes: Step S8.1: Analyze mass change: Compare the weighing results before and after immersion and calculate the mass change percentage (denoted as b2) as follows:

[0017] Step S8.2: Analyze appearance changes: Analyze the consistency of the sample surface under 20x and 100x magnification before and after penetration, and check whether there is any corrosion or rust 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 there is no obvious change in the appearance of the sample before and after immersion, it is determined that the launch vehicle tank sample is compatible with the aerospace medium.

[0018] Compared with the prior art, the present invention has the following beneficial effects: 1. In view of the lack of compatibility testing for aerospace penetrants in the prior art, the present invention proposes a reliable and simple compatibility testing method, which is easy to operate and highly efficient. 2. The present invention can quantitatively evaluate the compatibility of the penetrant with the launch vehicle tank and aerospace cutoff by comparing and analyzing the changes in mass and appearance of the sample before and after penetration and before and after immersion in the medium, and has high engineering application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings: Figure 1 Flowchart for the implementation of the present invention.

[0020] Figure 2 Schematic diagram of the shape and size of the sample of the present invention.

[0021] Figure 3 This is a comparison diagram of the sample before and after penetration testing under a metallographic microscope at 20 times and 100 times magnification according to an embodiment of the present invention. DETAILED DESCRIPTION

[0022] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0023] like Figures 1 to 3 As shown, an embodiment of the present invention provides a compatibility test method for a penetrant with a launch vehicle tank and a space medium, comprising: Step S1: sample preparation; Step S2: weighing and observing the sample before the penetration test; Step S3: performing a penetration test on the sample; Step S4: weighing and observing the sample after the penetration test; Step S5: analyzing the compatibility of the permeate with the launch vehicle tank sample; Step S6: immersing the sample with the remaining penetrant in aerospace medium; Step S7: weighing and observing the sample after immersion; Step S8: Analyze the changes in the quality and appearance of the sample before and after immersion; analyze the changes in the quality and appearance of the sample that has undergone penetration testing before and after immersion in aerospace media, so as to analyze whether the sample that has undergone penetration testing is compatible with aerospace media.

[0024] Furthermore, in step S1, the material of the sample is consistent with the material of the carrier rocket tank, the diameter of the sample is 25 to 30 mm, and the thickness is 2.0 to 5.0 mm. At the same time, a through hole with a diameter of 2 to 8 mm is made on the sample to have appropriate residue when removing the penetrant; the surface state of the test piece is machined to remove burrs and the surface is smooth.

[0025] In step S2, the sample is first cleaned with ethanol to remove impurities such as grease and powder on the surface of the sample. The sample is 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 0.0001 g (denoted as a1). The appearance of the sample is then observed using a metallographic microscope at magnifications of 20x and 100x, respectively, and photographed to record the appearance. The sample is then placed in a dust bag to prevent corrosion or contamination.

[0026] In step S3, the sample is subjected to a penetration test according to the penetration test steps, which includes the following basic steps: penetration, removal of excess penetrant on the surface, drying, and imaging; the sample after the penetration test is placed in a dustproof bag to prevent corrosion or contamination.

[0027] In step S4, the sample is weighed / observed after the penetrant test. On the fifth day after the penetrant test, the sample is weighed using a high-precision balance with an accuracy of 0.0001g (denoted as a2). The appearance of the sample is then observed using a metallographic microscope at magnifications of 20x and 100x, respectively, and photographs are taken to record the appearance.

[0028] Furthermore, the step S5 includes: Step S5.1: Analyze mass changes; compare the two weighing results before and after the penetrant test, and calculate the mass change percentage before and after the penetrant test (denoted as b1). The calculation formula is as follows:

[0029] Step S5.2: Analyze changes in appearance; analyze the consistency of the sample surface under 20x and 100x magnification before and after penetration, and check whether there is any corrosion or rust on the sample surface after penetration; Step S5.3: Comprehensive analysis: If the mass change rate of the sample before and after the penetrant test is between -0.03% and 0.03%, and there is no obvious change in the appearance of the sample before and after the penetrant test, it is determined that the penetrant is compatible with the launch vehicle tank sample.

[0030] In step S6, the sample that has undergone the penetration test is immersed in a spaceflight medium. Step S6 includes: Step S6.1: Immerse the sample after the penetration test in a conventional aerospace medium such as liquid hydrogen, liquid oxygen, nitrogen tetroxide, methylhydrazine, or anhydrous hydrazine; Step S6.2: Calculation method for immersion time: 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. Step S6.3: Use ground-mouth glass bottles to hold the medium and specimens. 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 out, wash and dry.

[0031] In step S7, the sample is weighed using a high-precision balance with an accuracy of 0.0001 g (denoted as a3), and the appearance of the sample is observed using a metallographic microscope at magnifications of 20 times and 100 times, respectively, and photographed to record the appearance; the sample is placed in a dust bag to prevent corrosion or contamination.

[0032] The step S8 comprises: Step S8.1: Analyze mass change: Compare the weighing results before and after immersion and calculate the mass change percentage (denoted as b2) as follows:

[0033] Step S8.2: Analyze appearance changes: Analyze the consistency of the sample surface under 20x and 100x magnification before and after penetration, and check whether there is any corrosion or rust 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 there is no obvious change in the appearance of the sample before and after immersion, it is determined that the launch vehicle tank sample is compatible with the aerospace medium.

[0034] In summary, an embodiment of the present invention provides a compatibility test method for a penetrant with a carrier rocket tank and a space medium. The test method includes sample preparation, weighing and observing the sample before penetration testing, penetration testing of the sample, weighing and observing the sample after the penetration testing, analyzing the compatibility of the penetrant with the carrier rocket tank sample, immersing the penetration tested sample in a space medium, weighing and observing the sample after immersion, and analyzing the changes in the quality and appearance of the penetration tested sample before and after immersion in the space medium, thereby analyzing whether the penetration tested sample is compatible with the space medium.

[0035] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other at will without conflict.

Claims

1. A compatibility test method for penetrants with launch vehicle tanks and aerospace media, characterized in that: include: Step S1: sample preparation; Step S2: weighing and observing the sample before the penetration test; Step S3: performing a penetration test on the sample; Step S4: weighing and observing the sample after the penetration test; Step S5: analyzing the compatibility of the permeate with the launch vehicle tank sample; Step S6: immersing the sample with the remaining penetrant in aerospace medium; Step S7: weighing and observing the sample after immersion; Step S8: Analyze the changes in the quality and appearance of the sample before and after immersion.

2. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 1, characterized in that: In step S1, the material of the sample is consistent with the material of the carrier rocket tank, the diameter of the sample is 25 to 30 mm, and the thickness is 2.0 to 5.0 mm. At the same time, a through hole with a diameter of 2 to 8 mm is made on the sample to ensure appropriate residue when removing the penetrant; the surface state of the test piece is machined to remove burrs and the surface is smooth.

3. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 1, characterized in that: In step S2, the sample is first cleaned with ethanol to remove impurities on the surface, and 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 with a high-precision balance with an accuracy of 0.0001g, recorded as a1, and then the appearance of the sample is observed with a metallographic microscope at magnifications of 20 times and 100 times, respectively, and photographed to record the appearance; the sample is placed in a dust bag to prevent corrosion or contamination.

4. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 1, characterized in that: In step S3, the sample is subjected to a penetration test according to the penetration test steps, which includes the following basic steps: penetration, removal of excess penetrant on the surface, drying, and imaging; the sample after the penetration test is placed in a dustproof bag to prevent corrosion or contamination.

5. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 3, characterized in that: In the step S4, the sample is weighed / observed after the penetration test, which is characterized in that the sample is weighed / observed on the 5th day after the penetration test using a high-precision balance with an accuracy of 0.0001g and recorded as a2, and then the appearance of the sample is observed using a metallographic microscope at magnifications of 20 times and 100 times respectively, and the appearance is photographed and recorded.

6. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 5, characterized in that: The step S5 comprises: Step S5.1: Analyze the mass change; compare the two weighing results before and after the penetrant test, and calculate the mass change percentage before and after the penetrant test, recorded as b1, using the following formula: Step S5.2: Analyze changes in appearance; analyze the consistency of the sample surface under 20x and 100x magnification before and after penetration, and check whether there is any corrosion or rust on the sample surface after penetration; Step S5.3: Comprehensive analysis: If the mass change rate of the sample before and after the penetrant test is between -0.03% and 0.03%, and there is no obvious change in the appearance of the sample before and after the penetrant test, it is determined that the penetrant is compatible with the launch vehicle tank sample.

7. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 6, characterized in that: In step S6, the sample that has undergone the penetration test is immersed in a spaceflight medium. Step S6 includes: Step S6.1: Immerse the above-mentioned sample that has undergone the penetration test in a conventional aerospace medium; Step S6.2: Calculation method for immersion time: First, perform 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: Use ground-mouth glass bottles to hold the medium and specimens. 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 out, wash and dry.

8. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 7, characterized in that: In step S7, the sample is weighed using a high-precision balance with an accuracy of 0.0001 g and recorded as a3. The appearance of the sample is then observed using a metallographic microscope at magnifications of 20 times and 100 times, and photographs are taken to record the appearance. The sample is placed in a dust bag to prevent corrosion or contamination.

9. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 8, characterized in that: In step S8, the changes in the quality and appearance of the sample that has undergone the penetration test before and after being immersed in the aerospace medium are analyzed, thereby analyzing whether the sample that has undergone the penetration test is compatible with the aerospace medium.

10. The compatibility test method of the permeate with the carrier rocket tank and aerospace medium according to claim 9, characterized in that: The step S8 comprises: Step S8.1: Analyze mass change: Compare the weighing results before and after immersion, and calculate the mass change percentage before and after immersion, which is recorded as b2. The calculation formula is as follows: Step S8.2: Analyze appearance changes: Analyze the consistency of the sample surface under 20x and 100x magnification before and after penetration, and check whether there is any corrosion or rust 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 there is no obvious change in the appearance of the sample before and after immersion, it is determined that the launch vehicle tank sample is compatible with the aerospace medium.

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