Charged particle bundling device for aerospace product radiation simulation and manufacturing method

Abstract

The invention provides a charged particle bundling device for aerospace product radiation simulation and a manufacturing method. The charged particle bundling device comprises an axis closing cavity, a deflection magnet assembly and a magnetic field detection and control system. The axis combining cavity is of a three-way structure and comprises an electron beam pipeline and a proton beam pipeline; the deflection magnet assembly comprises side magnet yokes, magnet yokes and magnetic poles, the magnetic poles are connected with the inner sides of the upper magnet yoke and the lower magnet yoke respectively, and the three-way convergence part of the shaft combining cavity is located between the upper magnetic pole and the lower magnetic pole. The magnetic field detection and control system comprises an excitation coil, a Hall magnetic field detector, an excitation power supply and a display control device; the excitation coil is wound on the side magnet yoke and is connected with an excitation power supply; and the Hall magnetic field detector is positioned in the cavity between the upper magnetic pole and the lower magnetic pole and is connected with the out-of-cavity display control device through an electric connector. Through the three-way structure design of the axis closing cavity, the proton beam and the electron beam can be effectively subjected to axis closing, and the requirement that a sample irradiates two kinds of particle beams at the same time in a comprehensive radiation test is met.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of radiation processing technology, in particular to a charged particle beam device for radiation simulation of aerospace products and a manufacturing method. BACKGROUND

[0002] After the aerospace device or material is irradiated by charged particles in space, its chemical and physical properties will change in a series of changes, causing damage to the spacecraft material and affecting its service life. Therefore, it is necessary to carry out radiation simulation test on the spacecraft material by charged particles such as protons and electrons in space, and optimize and screen the related materials through the analysis and comparison of the test results. The charged particle beam device for radiation simulation of aerospace products can realize the normal incidence of electron beam and proton beam alone or simultaneously, and is an important part of the space electron-proton comprehensive irradiation equipment.

[0003] The traditional proton-electron irradiation system presents a certain angle when the proton beam and the electron beam irradiate the sample simultaneously, and cannot achieve simultaneous coaxial normal incidence, which easily leads to the phenomenon of uneven irradiation of the sample due to the irradiation angle. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a charged particle beam device for radiation simulation of aerospace products and a manufacturing method.

[0005] According to the charged particle beam device for radiation simulation of aerospace products provided by the present application, the device comprises:

[0006] The coaxial cavity, the deflection magnet assembly and the magnetic field detection and control system;

[0007] The coaxial cavity is a three-way structure, comprising an electron beam pipeline and a proton beam pipeline;

[0008] The deflection magnet assembly is a U-shaped structure, comprising a side magnetic yoke, a magnetic yoke and a magnetic pole, the magnetic pole is connected with the inner side of the upper and lower magnetic yokes respectively, and the three-way convergence part of the coaxial cavity is located between the upper and lower magnetic poles;

[0009] The magnetic field detection and control system comprises an excitation coil, a Hall magnetic field detector, an excitation power supply and a display control device; the excitation coil is wound on the side magnetic yoke and connected with the excitation power supply; the Hall magnetic field detector is located in the cavity between the upper and lower magnetic poles, and is connected with the display control device outside the cavity through an electrical connector.

[0010] Preferably, the electron beam pipeline is connected to the proton beam pipeline at an angle of 45°-60°.

[0011] Preferably, the pole face of the deflection magnet assembly is a 45°-60° sector structure, the sector included angle is consistent with the included angle of the electron beam channel and the proton beam channel; the pole face width is 2-3 times the upper and lower pole gap, and the pole face is concave with an arc.

[0012] Preferably, the excitation coil is made of enameled wire.

[0013] According to the application, a manufacturing method of a charged particle beam device for radiation simulation of aerospace products is provided, comprising the following steps:

[0014] Step S1: making a coaxial cavity, connecting the electron beam channel to the proton beam channel at an angle of 45°-60° to form a tee structure;

[0015] Step S2: making a deflection magnet assembly, making a U-shaped side yoke, a yoke and a pole, and placing them at the tee junction of the coaxial cavity, determining the pole gap and the pole face width according to the particle beam width, and the pole face width is 2-3 times the pole gap;

[0016] Step S3: processing the yoke and the pole face into a sector structure, determining the pole face area according to the electron deflection radius, making the pole face concave with a preset arc, and determining the width and thickness of the side yoke;

[0017] Step S4: winding the excitation coil on the side yoke, determining the number of turns, the winding height and thickness, and connecting the excitation power supply;

[0018] Step S5: installing the Hall magnetic field detector in the cavity between the upper and lower poles, and connecting it with the display control device outside the cavity; during operation, the excitation voltage and current are adjusted to make the display magnetic field strength equal to the theoretical magnetic field strength.

[0019] Preferably, the step S3 comprises:

[0020]

[0021] Wherein B o is the theoretical magnetic field strength, U o is the electron acceleration voltage, and r is the electron beam deflection radius.

[0022] Φ o =B o S o

[0023] Wherein, Φ o is the working air gap magnetic flux, and S o is the pole face area.

[0024]

[0025] Wherein, S1 is the cross-sectional area of the magnetic yoke, B1 is the maximum working magnetic field, and the leakage magnetic coefficient is maximum delta max = 2.0.

[0026] Preferably, the step S4 comprises:

[0027]

[0028] Wherein I o is the first theoretical excitation current, N is the number of turns, B o is the theoretical magnetic field strength, and L is the length of the air gap space.

[0029] Preferably, in step S1, the electron beam pipe material is 304 stainless steel, the inner diameter is 140mm, the outer diameter is 150mm, and the outer layer is covered with 1-2mm lead.

[0030] Preferably, in step S2, the material of the deflection magnet assembly is industrial pure iron DT4; the sector angle of the pole face is 45°, the electron beam deflection radius is 640mm, the middle gap of the pole is 170mm, the two side gaps are 160mm, and the pole face width is 320mm.

[0031] Preferably, in step S4, the excitation coil selects a bare copper wire with a diameter of 2mm, a diameter of 2.3mm after insulation, a resistance of 1.4 ohms, and a number of turns of 400 turns, and the working current is 1A.

[0032] Compared with the prior art, the present application has the following beneficial effects:

[0033] 1. The present application realizes the comprehensive radiation test sample function by reasonably designing the parallel beam pipe and coaxially combining the proton beam and the electron beam.

[0034] 2. The present application realizes the magnetic deflection of the electron beam by adding a deflection magnet assembly on the parallel beam pipe, completes the normal incidence of the electron beam and the proton beam alone or simultaneously, more truly simulates the space proton electron pair sample irradiation environment, and obtains more accurate test data.

[0035] 3. The proton and electron coaxial system of the present application makes the irradiation intensity of the radiation test more uniform, and ensures that the same batch of samples are irradiated with the same dose.

[0036] 4. The present application effectively combines the proton beam and the electron beam by designing the three-way structure of the coaxial cavity (the electron beam pipe and the proton beam pipe are connected at a specific angle), meets the demand of simultaneous irradiation of the sample on the two kinds of particle beams in the comprehensive radiation test, and solves the problem that the two beams cannot be coaxial in the traditional system. BRIEF DESCRIPTION OF DRAWINGS

[0037] Other features, objects, and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments thereof, when read in conjunction with the accompanying drawings:

[0038] Figure 1 is a schematic diagram of coaxial structure;

[0039] Figure 2 is a schematic diagram of deflection magnet assembly and magnetic field detection and control system. DETAILED DESCRIPTION

[0040] The application will be described in greater detail with reference to specific embodiments. The following embodiments are presented by way of example and are not intended to limit the present application in any manner. It should be noted that, for one of ordinary skill in the art, several changes and modifications can be made without departing from the concept of the present application. These are all within the scope of the present application.

[0041] As shown in Figure 1 and Figure 2 The charged particle beam device for radiation simulation of aerospace products disclosed in the present application comprises a coaxial cavity (1), a deflection magnet assembly (2), and a magnetic field detection and control system (3). The coaxial cavity comprises an electron beam channel (11) and a proton beam channel (12). The deflection magnet assembly (2) comprises a side magnetic yoke (21), a magnetic yoke (22), and magnetic poles (23). The magnetic poles (23) are respectively connected to the inner sides of the upper and lower magnetic yokes (22). The magnetic field detection and control system (3) comprises a magnetizing coil (31), a Hall magnetic field detector (32), a magnetizing power supply, and a display control device. The magnetic coil (31) is wound around the side magnetic yoke (21) and is connected to the magnetizing power supply. The Hall magnetic field detector (32) is located in the cavity between the upper and lower magnetic poles (23) of the deflection magnet and is connected to the control device outside the cavity through an electrical connector. The three-way junction of the coaxial cavity (1) is between the upper and lower magnetic poles (23) of the deflection magnet assembly.

[0042] The electron beam channel (11) is connected to the proton beam channel (12) at an angle in the range of 45° to 60°, obtaining a coaxial cavity with a three-way structure.

[0043] The deflection magnet assembly (2) has a U-shaped structure and can generate a uniform magnetic field perpendicular to the electron beam.

[0044] The pole faces of the upper and lower magnetic poles (23) of the deflection magnet assembly have a fan-shaped structure, the included angle of the fan-shaped structure is consistent with the included angle of the electron beam channel (11) and the proton beam channel (12), and the pole faces of the magnetic poles (23) have a certain curvature.

[0045] The magnetizing coil (31) is wound around the side magnetic yoke (21), preferably using enameled wire, and is powered by the magnetizing power supply.

[0046] The Hall magnetic field detector (32) is located in the cavity between the upper and lower magnetic pole faces of the deflection magnet assembly, and is connected to the cavity display control device through an electrical connector.

[0047] According to the above, a preferred implementation method is provided for the manufacturing method of the maximum energy 200 keV electron beam and proton beam coaxial beam device, and the specific implementation steps are as follows:

[0048] S1: The coaxial cavity is composed of a proton beam pipe and an electron beam pipe. The electron beam pipe is connected to the proton beam pipe at an angle of 45° through mechanical processing, welding and other processes to obtain a coaxial cavity with a three-way structure. The pipe material is selected from 304 non-magnetic stainless steel material, the inner diameter is 140 mm, the outer diameter is 150 mm, and the outer layer is coated with 1-2 mm of lead skin for safety consideration;

[0049] S2: The magnetic guide material is made of industrial pure iron DT4 by mechanical processing method, and the pole face is a 45-shaped structure. The electron beam deflection radius is 640 mm according to the coaxial structure, and the inner diameter is 480 mm and the outer diameter is 800 mm according to the fan-shaped structure. According to the width of the electron beam, the magnetic pole face is designed to have a certain curvature, the middle gap is 170 mm, the two side gaps are 160 mm, the magnetic pole height is 60 mm to ensure the uniformity of the vertical magnetic field, and the width of the magnetic pole face is twice the width of the magnetic pole gap: 320 mm.

[0050] The related parameters of the deflection magnet assembly are determined as follows:

[0051]

[0052] Where B o is the theoretical magnetic field strength (unit: T), U o is the electron acceleration voltage (unit: V), and r is the electron beam deflection radius (unit: m). Given U o = 200 kV, r = 640 mm, the formula gives B o = 0.00235 T

[0053] Φ o = B o S o

[0054] Where Φ o is the working air gap magnetic flux (unit: Wb), S o is the pole face area (unit: m 2 ), and the pole face area is calculated to be 0.1608 m 2 . The formula gives Φ o = 3.78 × 10 -4 Wb.

[0055]

[0056] Wherein, S1 is the cross-sectional area of the yoke, B1 is the maximum working magnetic field of 0.1T, and the leakage magnetic coefficient is the maximum delta max =2.0, and S1=0.00756m is obtained by substituting the formula 2 That is, the cross-sectional area of the yoke should be not less than 0.00756m 2 In order to ensure the mechanical strength, the thickness of the yoke is 50mm;

[0057] S3: The excitation coil is wound on the side yoke of the magnetic guide material in a winding mode, preferably a enameled wire (bare copper wire diameter 2mm, diameter 2.3mm after insulation), resistance 1.4 ohms, current: 1A.

[0058]

[0059] Wherein I o Is the first theoretical excitation current (unit: A), N is the number of turns (unit: turns), B o Is the theoretical magnetic field strength, L is the length of the air gap space (unit: m). Given B o =0.00235T, L=0.17m, then NI o =318AC. A margin is left, and NI=400AC is taken, and the number of turns of the coil is 400 turns.

[0060] S4: The Hall magnetic field detector is installed in the cavity between the upper and lower magnetic poles of the deflection magnet, and is connected with the cavity display control device through an electrical connector.

[0061] The working process of the application is:

[0062] 200keV electron beam is injected at a 45° angle with the proton beam pipe, the energized deflection magnet assembly generates a uniform magnetic field perpendicular to the direction of the electron beam, and the magnetic field detection and control system adjusts the electron beam to deflect 45° after the electron beam and the proton beam are coaxial and bunched. Due to the action of the magnetic field, the protons will produce a very small angle (<0.5°) of deflection, which can be ignored, so that the electron beam and the proton beam are completely coaxial, and then the proton beam and the electron beam are independently or simultaneously incident on the sample, which can more truly simulate the spatial proton-electron pair sample irradiation environment, so that more accurate test results are obtained.

[0063] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0064] The specific embodiments of the present application are described above. It should 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 do not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict, provided that they do not conflict.

Claims

1. A charged particle beam-gathering device for radiation simulation of aerospace products, characterized in that, include: The coaxial cavity (1), the deflecting magnet assembly (2), and the magnetic field detection and control system (3) are included. The coaxial cavity (1) has a three-way structure, including an electron beam channel (11) and a proton beam channel (12); The deflecting magnet assembly (2) has a U-shaped structure, including a side yoke (21), a yoke (22) and a magnetic pole (23). The magnetic pole (23) is connected to the inner side of the upper and lower yokes (22) respectively. The three-way junction of the shaft cavity (1) is located between the upper and lower magnetic poles (23). The magnetic field detection and control system (3) includes an excitation coil (31), a Hall magnetic field detector (32), an excitation power supply, and a display control device; the excitation coil (31) is wound on the side yoke (21) and connected to the excitation power supply; the Hall magnetic field detector (32) is located in the cavity between the upper and lower magnetic poles (23) and is connected to the display control device outside the cavity through an electrical connector.

2. The charged particle beam simulating device for aerospace product radiation according to claim 1, characterized in that, The electron beam channel (11) is connected to the proton beam channel (12) at an angle of 45° to 60°.

3. The charged particle beam simulating device for aerospace product radiation according to claim 1, characterized in that, The magnetic pole (23) of the deflecting magnet assembly (2) has a 45° to 60° fan-shaped structure, and the included angle of the fan shape is consistent with the included angle of the electron beam channel (11) and the proton beam channel (12); the width of the magnetic pole (23) is 2 to 3 times the gap between the upper and lower magnetic poles (23), and the pole surface is concave with an arc.

4. The charged particle beam simulating device for aerospace product radiation according to claim 1, characterized in that, The excitation coil (31) is made of enameled wire.

5. A method for manufacturing a charged particle clustering device for radiation simulation of aerospace products, characterized in that, Includes the following steps: Step S1: Fabricate the coaxial cavity (1), and connect the electron beam channel (11) to the proton beam channel (12) at 45° to 60° to form a three-way structure; Step S2: Fabricate the deflection magnet assembly (2), fabricate the U-shaped side yoke (21), yoke (22) and magnetic pole (23), place them at the three-way junction of the coaxial cavity (1), determine the gap between magnetic poles (23) and the width of the pole surface according to the particle beam width, and the width of the pole surface is 2 to 3 times the gap between magnetic poles; Step S3: Process the magnetic yoke (22) and the magnetic pole (23) into a fan-shaped structure, determine the electron deflection radius and the area of ​​the pole surface, the magnetic pole (23) is concave in a preset arc, and determine the width and thickness of the side magnetic yoke (21); Step S4: Wind the excitation coil (31) around the side yoke (21), determine the number of turns, winding height and thickness, and connect the excitation power supply; Step S5: Install the Hall magnetic field detector (32) in the cavity between the upper and lower magnetic poles (23) and connect it to the external display control device; adjust the excitation voltage and current during operation so that the displayed magnetic field strength is equal to the theoretical magnetic field strength.

6. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 5, characterized in that, Step S3 includes: Among them B o U is the theoretical magnetic field strength. o is the electron accelerating voltage, and r is the electron beam deflection radius; F o =B o S o Where, Φ o S is the working air gap magnetic flux. o The polar surface area; Where S1 is the cross-sectional area of ​​the magnetic yoke, B1 is the maximum working magnetic field, and the leakage magnetic coefficient is taken as the maximum δ. max =2.

0.

7. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 5, characterized in that, Step S4 includes: Among them I o The first theoretical excitation current is given, where N is the number of coil turns, and B... o Where L is the theoretical magnetic field strength and L is the length of the air gap.

8. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 5, characterized in that, In step S1, the electron beam tube is made of 304 stainless steel, with an inner diameter of 140 mm, an outer diameter of 150 mm, and an outer layer covered with 1-2 mm of lead sheet.

9. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 5, characterized in that, In step S2, the material of the deflecting magnet assembly (2) is industrial pure iron DT4; the fan-shaped angle of the magnetic pole (23) is 45°, the electron beam deflection radius is 640mm, the middle gap of the magnetic pole is 170mm, the gap on both sides is 160mm, and the width of the pole surface is 320mm.

10. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 5, characterized in that, In step S4, the excitation coil (31) is made of bare copper wire with a diameter of 2mm and an insulated diameter of 2.3mm, with a resistance of 1.4 ohms, 400 coil turns, and an operating current of 1A.

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