Charged particle beam device for radiation simulation of aerospace products and method of manufacturing

Abstract

The application provides a charged particle beam device for radiation simulation of aerospace products and a manufacturing method thereof, which comprises a coaxial cavity, a deflection magnet assembly and a magnetic field detection and control system; the coaxial cavity is a three-way structure and comprises an electron beam pipe and a proton beam pipe; the deflection magnet assembly comprises a side magnetic yoke, a magnetic yoke and magnetic poles, the magnetic poles are connected with the inner sides of the upper and lower magnetic yokes respectively, and the three-way joint part of the coaxial cavity is located between the upper and lower magnetic poles; the magnetic field detection and control system comprises a field coil, a Hall magnetic field detector, a field power supply and a display control device; the field coil is wound on the side magnetic yoke and connected with the field power supply; and the Hall magnetic field detector is located in the cavity between the upper and lower magnetic poles and connected with the cavity display control device through an electric connector. Through the three-way structure design of the coaxial cavity, the proton beam and the electron beam can be effectively coaxial, and the requirement of simultaneous irradiation of the sample on the two kinds of particle beams in the comprehensive radiation test can be met.

Description

Technical Field

[0001] This invention relates to the field of radiation processing technology, specifically to a charged particle clustering device and manufacturing method for radiation simulation of aerospace products. Background Technology

[0002] When spacecraft components or materials are irradiated by charged particles in space, their chemical and physical properties undergo a series of changes, causing damage to spacecraft materials and affecting their service life. Therefore, it is necessary to conduct irradiation simulation experiments on spacecraft materials using charged particles such as protons and electrons, and to optimize and screen relevant materials through analysis and comparison of the experimental results. Charged particle beam emulation devices for spacecraft product radiation simulation can achieve individual or simultaneous normal incidence of electron and proton beams on samples, and are an important component of space-based electron-proton combined irradiation equipment.

[0003] Traditional proton-electron irradiation systems exhibit a certain angle between the proton beam and the electron beam when irradiating the sample simultaneously, making it impossible to achieve simultaneous coaxial normal incidence. This can easily lead to uneven irradiation of the sample due to the irradiation angle. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the purpose of this invention is to provide a charged particle clustering device and manufacturing method for radiation simulation of aerospace products.

[0005] A charged particle beam simulating radiation from aerospace products, according to the present invention, comprises:

[0006] Coaxial cavity, deflector magnet assembly, and magnetic field detection and control system;

[0007] The coaxial cavity has a three-way structure, including an electron beam channel and a proton beam channel;

[0008] The deflecting magnet assembly has a U-shaped structure, including a side yoke, a magnetic yoke, and magnetic poles. The magnetic poles are respectively connected to the inner sides of the upper and lower magnetic yokes, and the three-way confluence part of the coupling cavity is located between the upper and lower magnetic poles.

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

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

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

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

[0013] A method for manufacturing a charged particle beam simulating radiation from aerospace products according to the present invention includes the following steps:

[0014] Step S1: Fabricate the coaxial cavity and connect the electron beam channel to the proton beam channel at 45° to 60° to form a three-way structure;

[0015] Step S2: Fabricate the deflection magnet assembly, fabricate the U-shaped side yoke, yoke and magnetic poles, place them at the three-way junction of the coaxial cavity, determine the magnetic pole gap and pole face width according to the particle beam width, the pole face width is 2 to 3 times the magnetic pole gap;

[0016] Step S3: Process the magnetic yoke and magnetic pole face into a fan-shaped structure, determine the pole face area according to the electron deflection radius, make the magnetic pole face concave with a preset arc, and determine the width and thickness of the side magnetic yoke.

[0017] Step S4: Wind the excitation coil onto the side yoke, determine the number of turns, winding height and thickness, and connect the excitation power supply;

[0018] Step S5: Install the Hall magnetic field detector in the cavity between the upper and lower magnetic poles and connect it to the external display and control device; during operation, adjust the excitation voltage and current to make the displayed magnetic field strength equal to the theoretical magnetic field strength.

[0019] Preferably, step S3 includes:

[0020]

[0021] 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;

[0022] Φ o =B o S o

[0023] Where, Φ o S is the working air gap magnetic flux. o The polar surface area;

[0024]

[0025] 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.

[0026] Preferably, step S4 includes:

[0027]

[0028] Where 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.

[0029] Preferably, 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.

[0030] Preferably, in step S2, the material of the deflecting magnet assembly is industrial pure iron DT4; the fan-shaped angle of the magnetic pole face is 45°, the electron beam deflection radius is 640mm, the gap between the magnetic poles is 170mm, the gap between the two sides is 160mm, and the pole face width is 320mm.

[0031] Preferably, in step S4, the excitation coil is made of enameled wire with a bare copper wire diameter of 2mm and an insulated diameter of 2.3mm, a resistance of 1.4 ohms, 400 coil turns, and an operating current of 1A.

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

[0033] 1. This invention application achieves the function of comprehensive radiation testing sample by rationally designing the parallel beam channel to combine the proton beam and electron beam into a single axis.

[0034] 2. This invention application achieves magnetic deflection of the electron beam by adding a deflecting magnet assembly to the beam-splitting pipe, enabling the electron beam and proton beam to be incident on the sample individually or simultaneously in the normal direction, thus more realistically simulating the irradiation environment of the sample by protons and electrons in space and obtaining more accurate experimental data.

[0035] 3. The proton and electron coaxial system described in this invention application makes the irradiance of the radiation test more uniform, ensuring that the irradiation dose of samples in the same batch is the same.

[0036] 4. This invention, through the three-way structure design of the coaxial cavity (the electron beam channel and the proton beam channel are connected at a specific angle), can effectively coaxialize the proton beam and the electron beam, meeting the requirement of simultaneous irradiation of the sample with two particle beams in comprehensive radiation testing, and solving the problem that the two beams cannot be coaxial in traditional systems. Attached Figure Description

[0037] 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:

[0038] Figure 1 This is a schematic diagram of the coupling structure;

[0039] Figure 2 This is a schematic diagram of the deflection magnet assembly and the magnetic field detection and control system. Detailed Implementation

[0040] 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 scope of protection of the present invention.

[0041] like Figure 1 and Figure 2 As shown, the charged particle beam simulating radiation of aerospace products disclosed in this invention includes a coaxial cavity (1), a deflecting magnet assembly (2), and a magnetic field detection and control system (3). The coaxial cavity includes an electron beam channel (11) and a proton beam channel (12). The deflecting magnet assembly (2) includes a side yoke (21), a yoke (22), and magnetic poles (23). The magnetic poles (23) are connected to the inner sides of the upper and lower yokes (22), respectively. 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 magnetic coil (31) is wound around 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) of the deflecting magnet and is connected to the external control device via an electrical connector. The three-way junction of the coaxial cavity (1) is located between the upper and lower pole surfaces (23) of the deflecting magnet assembly.

[0042] The electron beam channel (11) is connected to the proton beam channel (12) at an angle range of 45° to 60° to obtain a three-way coaxial cavity;

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

[0045] The excitation coil (31) is wound on the side yoke (21), preferably with enameled wire, and powered by an excitation power supply.

[0046] The Hall magnetic field detector (32) is located in the cavity between the upper and lower magnetic poles (23) of the deflection magnet assembly and is connected to the external display control device via an electrical connector.

[0047] Based on the above, a preferred implementation method is provided for fabricating a coaxial parallel beam device for an electron beam and proton beam with a maximum energy of 200 keV. The specific implementation steps are as follows:

[0048] S1: The coaxial cavity consists of two parts: the proton beam channel and the electron beam channel. The electron beam channel is connected to the proton beam channel at a 45° angle through machining, welding and other processes to obtain a coaxial cavity with a three-way structure. The channel material is 304 non-magnetic stainless steel with an inner diameter of 140mm and an outer diameter of 150mm. For safety reasons, a 1-2mm lead sheet is used to cover the outer layer.

[0049] S2: The magnetic permeable material is made of industrial pure iron DT4 using mechanical processing methods. Its pole face has a 45-shaped structure. According to the coaxial structure, the electron beam deflection radius is selected as 640mm. The fan-shaped structure has an inner diameter of 480mm and an outer diameter of 800mm. According to the electron beam width, the magnetic pole face is designed with a certain curvature, with a middle gap of 170mm and two side gaps of 160mm. The magnetic pole height is 60mm. To ensure the uniformity of the vertical magnetic field, the width of the magnetic pole face is twice the magnetic pole gap: 320mm.

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

[0051]

[0052] Among them B o U is the theoretical magnetic field strength (unit: T). o U is the electron accelerating voltage (V), and r is the electron beam deflection radius (m). Given U... o =200kV, r=640mm, substituting into the formula, we get B o =0.00235T

[0053] Φ o =B o S o

[0054] Where, Φ o S is the working air gap magnetic flux (unit: Wb). o Polar surface area (unit: m²) 2 The polar surface area is calculated to be 0.1608 m². 2 Substituting into the formula, we get Φ o =3.78×10 -4 Wb.

[0055]

[0056] Where S1 is the cross-sectional area of ​​the magnetic yoke, with an adjustment margin, B1 is the maximum working magnetic field (0.1T), and the leakage magnetic coefficient is the maximum δ. max =2.0, substituting into the formula, we get S1 = 0.00756m 2 That is, the cross-sectional area of ​​the magnetic yoke should not be less than 0.00756 m². 2 To ensure mechanical strength, the thickness of the magnetic yoke is 50mm;

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

[0058]

[0059] Where I o Where N is the first theoretical excitation current (unit: A), N is the number of coil turns (unit: turns), and B is the first theoretical excitation current. o Let B be the theoretical magnetic field strength, and L be the length of the air gap (in meters). o =0.00235T, L=0.17m, then NI o =318AC. Leaving a margin, we take NI = 400AC, resulting in 400 coil turns.

[0060] S4: The Hall magnetic field detector is installed in the cavity between the upper and lower magnetic poles of the deflecting magnet and is connected to the external display and control device via an electrical connector.

[0061] The working process of this invention is as follows:

[0062] A 200keV electron beam is injected into the proton beam channel at a 45° angle. An energized deflector magnet assembly generates a uniform magnetic field perpendicular to the electron beam direction. The magnetic field detection and control system adjusts the electron beam to deflect it by 45°, ensuring it is coaxial with the proton beam. Due to the magnetic field, the protons experience a negligible deflection of less than 0.5°, achieving complete coaxiality between the electron and proton beams. This allows for the individual or simultaneous incidence of the proton and electron beams on the sample, more realistically simulating the irradiation environment of the sample by protons and electrons in space, thus yielding more accurate experimental results.

[0063] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0064] 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 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); 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. The energized deflecting magnet assembly (2) generates a uniform magnetic field perpendicular to the direction of the electron beam. It includes 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 confluence part of the coaxial 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. The electron beam channel (11) is connected to the proton beam channel (12) at an angle of 45°~60°. The deflecting magnet assembly (2) has a 45°~60° fan-shaped structure for its magnetic pole (23) surface, 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) surface is 2~3 times the gap between the upper and lower magnetic poles (23), and the pole surface is concave with an arc.

2. 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.

3. A method for manufacturing a charged particle beam simulating radiation from aerospace products, characterized in that, The charged particle beam simulating aerospace product radiation method according to claim 1 or 2 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°~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 the pre-set 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.

4. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 3, characterized in that, Step S3 includes: in The theoretical magnetic field strength, For electron accelerating voltage, The electron beam deflection radius; in, The working air gap magnetic flux, The polar surface area; in, Let be the cross-sectional area of ​​the magnetic yoke. To determine the maximum operating magnetic field, the leakage magnetic coefficient is set to the maximum value. .

5. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 3, characterized in that, Step S4 includes: in The first theoretical excitation current, The number of coil turns. The theoretical magnetic field strength, This represents the length of the air gap space.

6. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 3, characterized in that, In step S1, the electron beam tube is made of 304 stainless steel, with an inner diameter of 140mm, an outer diameter of 150mm, and an outer layer covered with 1-2mm of lead sheet.

7. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 3, 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.

8. The method for manufacturing a charged particle clustering device for radiation simulation of aerospace products according to claim 3, 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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