Charged particle beam spot and overlaying method, apparatus, device and medium

Abstract

The application relates to a charged particle beam fixed-point and surface covering delivery method, device, equipment and medium. By constructing a high-energy electron emitter running track, the initial running track height of the high-energy electron is determined; the high-energy electron motion track is determined based on Larmor rotation, reciprocal rebound motion between mirror points of the geomagnetic field and drift motion along the geomagnetic meridian to construct a fixed-point delivery strategy and a surface covering delivery strategy; the outer boundary constraint of the track running of the fixed-point delivery and the inner boundary constraint of the track running of the fixed-point delivery are determined, the high-energy electron emitter runs according to the track, and the high-energy electron beam is emitted based on the fixed-point delivery strategy; the outer boundary constraint of the track running of the surface covering delivery and the inner boundary constraint of the track running of the surface covering delivery are determined, the high-energy electron emitter runs according to the track, and the high-energy electron beam is continuously emitted based on the surface covering delivery strategy; the application can realize rapid and fixed-time delivery to a certain point in space and has the capability of single-ellipsoid surface covering delivery and multi-ellipsoid surface covering delivery.

Description

Methods, apparatus, equipment and media for targeted and surface delivery of charged particle beams Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a method, apparatus, equipment and medium for targeted and surface delivery of charged particle beams. Background Technology

[0002] The application of high-energy electron beams in the aerospace field typically involves various missions in satellites and spacecraft, such as communications satellite maintenance, spacecraft protection, spacecraft navigation, and directed energy transfer. In these applications, long-distance pinpointing and accurate coverage of high-energy electron beams are crucial.

[0003] To date, some research has been conducted on the constraint of charged particle beams by the Earth's magnetic field, including theoretical derivations using single-particle dynamics / magnetohydrodynamics and quantitative analyses based on multiphysics software such as Comsol. These studies have been widely applied in areas such as the formation and evolution of the Earth's magnetosphere and the mechanism of the Van Allen radiation belts. However, no publicly published results have been found on the active use of the Earth's magnetic field to constrain the motion of charged particle beams for on-demand delivery. Summary of the Invention

[0004] Therefore, it is necessary to provide a method, apparatus, equipment, and medium for delivering high-energy electrons to a fixed location in space or covering a certain spatial area on demand and in a timely manner, addressing the aforementioned technical problems.

[0005] A method for targeted and surface delivery of charged particle beams, the method comprising:

[0006] Construct a high-energy electron emitter orbital model to determine the initial orbital altitude of the high-energy electrons;

[0007] Based on the Larmor cyclotron motion, the reciprocating bounce motion between mirror points of the geomagnetic field and the drift motion along the geomagnetic meridian, the trajectory of high-energy electrons is determined, and a fixed-point delivery strategy and a surface delivery strategy are constructed. The fixed-point delivery strategy includes the design of a first delivery angle, and the surface delivery strategy includes the design of a second delivery angle.

[0008] The outer boundary constraint of the orbit for fixed-point delivery is determined based on the initial orbital height of the high-energy electrons, and the inner boundary constraint of the orbit for fixed-point delivery is determined based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy.

[0009] The outer boundary constraint of the orbital operation for surface delivery is determined based on the launch point location, and the inner boundary constraint of the orbital operation for surface delivery is determined based on the second launch angle. The high-energy electron transmitter operates according to the orbit and continuously emits high-energy electron beams based on the surface delivery strategy.

[0010] One embodiment further includes: establishing a spatial coordinate system, calculating the geomagnetic field at a point in the coordinate system, and constructing a dynamic model of high-energy electrons under the action of a geomagnetic dipole field based on the geomagnetic field.

[0011] In one embodiment, a high-energy electron emitter orbital model is constructed to determine the initial orbital altitude of the high-energy electrons, including:

[0012] Construct the fixed-point delivery trajectory configuration of high-energy electrons and determine the coverage configuration of high-energy electrons;

[0013] The latitude of the coverage configuration is defined by the location of the geomagnetic mirror point and the altitude at which high-energy electrons collide with the atmosphere, thus determining the initial orbital altitude of the high-energy electrons.

[0014] In one embodiment, constructing the fixed-point delivery trajectory configuration of high-energy electrons and determining the coverage configuration of high-energy electrons includes:

[0015] The configuration of the fixed-point delivery trajectory is represented as follows:

[0016]

[0017] In the formula, (x S ,y S ,z S (x) represents the launch point location; T ,y T ,z T (a, c) represents the target point location; (a, c) represents the parameters to be determined.

[0018] Based on the fixed-point delivery trajectory configuration, the trajectory of high-energy electrons is determined according to the Larmor cyclotron motion, the reciprocating bounce motion between geomagnetic mirror points, and the drift motion along geomagnetic meridians. The coverage configuration of the high-energy electrons is determined to be an ellipsoidal ring based on the trajectory of the high-energy electrons.

[0019] In one embodiment, the latitude of the coverage configuration is defined by the location of the geomagnetic mirror point and the altitude at which high-energy electrons collide with the atmosphere, thereby determining the initial orbital altitude of the high-energy electrons, including:

[0020] The first latitude is calculated based on the location of the geomagnetic mirror point, and the second latitude is calculated based on the height of the atmosphere after high-energy electron impacts.

[0021] The smaller value between the first latitude and the second latitude is selected as the orbital height constraint of the ellipsoidal ring to determine the initial orbital height of the high-energy electrons.

[0022] In one embodiment, the fixed-point delivery strategy includes the design of a first throwing angle, as well as the design of launch speed and launch timing;

[0023] The design of the first throwing angle includes:

[0024] Based on the periodic effects of the reciprocating bounce motion between geomagnetic mirror points and the drift motion along geomagnetic meridians, the first throwing angle is determined by calculating the period of the repeated bouncing motion and the period of drift along geomagnetic meridians; and the gyratory radius of the fixed-point delivery is calculated based on the influence of the Larmor gyratory motion.

[0025] The design of the launch speed includes:

[0026] Based on the influence of the high-energy electron's meridian drift along the geomagnetic orbital plane, the velocity of the high-energy electron's entire meridian drift is determined according to the gradient drift and curvature drift corresponding to the geomagnetic dipole magnetic field, and the emission speed is adjusted according to the velocity of the high-energy electron's entire meridian drift.

[0027] The launch timing design includes:

[0028] Based on the effects of drift along geomagnetic meridians and movement along a single geomagnetic field line, the delivery time is calculated by the time of drift along geomagnetic meridians and the time of movement along a single geomagnetic field line; and the time of drift along geomagnetic meridians is adjusted by adjusting the launch time, thereby meeting the delivery time requirements.

[0029] In one embodiment, the surface delivery strategy includes the design of a second throwing angle and the design of a launch velocity;

[0030] For single ellipsoidal coverage delivery, based on the periodic effect of drift along the geomagnetic meridian, the second throwing angle and launch velocity are determined by calculating the period of drift along the geomagnetic meridian; and based on the effect of Larmor cyclotron motion, the cyclotron radius during coverage delivery is calculated.

[0031] For multi-ellipsoidal coverage delivery, transmitters at different orbital altitudes are deployed by combining single ellipsoidal coverage with different orbits.

[0032] A charged particle beam delivery device for targeted and surface application, the device comprising:

[0033] The orbit construction module is used to build the orbital model of the high-energy electron emitter and determine the initial orbital altitude of the high-energy electrons.

[0034] The delivery strategy design module is used to determine the trajectory of high-energy electrons based on Larmor cyclotron motion, reciprocating bounce motion between mirror points of the geomagnetic field, and drift motion along geomagnetic meridians, and to construct a fixed-point delivery strategy and a surface delivery strategy; the fixed-point delivery strategy includes the design of a first throwing angle, and the surface delivery strategy includes the design of a second throwing angle.

[0035] The fixed-point delivery module is used to determine the outer boundary constraint of the fixed-point delivery orbit based on the initial orbital height of the high-energy electrons, and to determine the inner boundary constraint of the fixed-point delivery orbit based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy.

[0036] The surface delivery module is used to determine the outer boundary constraint of the surface delivery orbit based on the launch point location, and to determine the inner boundary constraint of the surface delivery orbit based on the second delivery angle. The high-energy electron transmitter operates according to the orbit and continuously emits a high-energy electron beam based on the surface delivery strategy.

[0037] A computer device includes a memory and a processor, the memory storing a computer program, the processor executing the computer program to implement the steps of any of the methods described above.

[0038] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of any of the methods described above.

[0039] The aforementioned method, apparatus, equipment, and medium for targeted and surface delivery of charged particle beams determine the initial orbital height of high-energy electrons by constructing a high-energy electron emitter orbital model; the trajectory of high-energy electrons is determined based on Larmor cyclotron motion, reciprocating bounce motion between geomagnetic mirror points, and drift motion along geomagnetic meridians, and a targeted delivery strategy and a surface delivery strategy are constructed. The targeted delivery strategy includes the design of a first delivery angle, and the surface delivery strategy includes the design of a second delivery angle. The outer boundary constraint of the targeted delivery orbit is determined based on the initial orbital height, and the inner boundary constraint of the targeted delivery orbit is determined based on the first delivery angle. The high-energy electron emitter operates according to the orbit and emits a high-energy electron beam based on the targeted delivery strategy. The outer boundary constraint of the surface delivery orbit is determined based on the emission point location, and the inner boundary constraint of the surface delivery orbit is determined based on the second delivery angle. The high-energy electron emitter operates according to the orbit and continuously emits a high-energy electron beam based on the surface delivery strategy.

[0040] This invention, by constructing a fixed-point delivery strategy and a surface delivery strategy, quantitatively provides the relationship between various physical parameters of the ellipsoidal ring corresponding to the high-energy electron trajectory and the high-energy electron emission parameters. Specifically, the constructed high-energy electron transmitter trajectory provides the initial orbital height of the high-energy electron transmitter; the fixed-point delivery strategy quantitatively provides the required emission speed, emission time, and delivery angle for fixed-point delivery, enabling rapid and timely delivery to a specific point in space; the surface delivery strategy achieves the capability of delivery over a single ellipsoid or multiple ellipsoidal surfaces; this invention can be used to perform electron accumulation testing on loads at corresponding locations. Attached Figure Description

[0041] Figure 1 is a flowchart illustrating a method for targeted and surface delivery of charged particle beams in one embodiment;

[0042] Figure 2 is a spatial geometric schematic diagram of the geomagnetic dipole pointing setting and the desired calculation point in one embodiment;

[0043] Figure 3 is a schematic diagram of the projection of a high-energy electron delivery ellipsoid ring onto the equatorial plane in one embodiment;

[0044] Figure 4 is a schematic diagram showing the relationship between the high-energy electron throwing angle and the latitude of the mirror point in one embodiment;

[0045] Figure 5 is a schematic diagram of the relationship between high-energy electron reciprocating bounce and latitude angle in one embodiment; wherein, Figure 5(a) is a schematic diagram of the relationship between 1 / 4 period of reciprocating bounce and latitude angle, and Figure 5(b) is a schematic diagram of the relationship between part of the reciprocating bounce time and latitude angle;

[0046] Figure 6 is a simulation diagram of the trajectory and velocity of high-energy electrons in one embodiment; wherein, Figure 6(a) is a schematic diagram of the xt trajectory of high-energy electrons, Figure 6(b) is a schematic diagram of the yt trajectory of high-energy electrons, Figure 6(c) is a schematic diagram of the xz trajectory of high-energy electrons, and Figure 6(d) is a schematic diagram of the velocity of high-energy electrons.

[0047] Figure 7 is a structural block diagram of a charged particle beam delivery device for point positioning and surface coverage in one embodiment;

[0048] Figure 8 is an internal structure diagram of a computer device in one embodiment. Detailed Implementation

[0049] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0050] It should be noted that in this invention, the use of terms such as "first," "second," etc., is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0051] In realizing this solution, the inventors targeted the need for rapid, long-distance delivery of high-energy electron beams (hereinafter referred to as high-energy electron beams) to both fixed points and covered areas. Based on the effects of the geomagnetic dipole field and the mechanism of motion evolution, they designed a high-energy electron transmitter track. The high-energy electron transmitter runs along the track and emits high-energy electron beams according to a control strategy (including the setting of the emission time, speed, and throw angle). After emission, the high-energy electron beam moves under the constraint of the geomagnetic dipole field, including three types of motion: Larmor gyratory around the geomagnetic field lines, reciprocating bounces between geomagnetic field mirror points, and drifting along geomagnetic meridians. Through effective emission control and the synthesis of these three types of motion, the trajectory of the high-energy electron beam is planned, and the high-energy electron beam is delivered to a fixed spatial location or a spatial area covering a certain area as needed and on time. That is, through the optimized deployment of the high-energy electron transmitter track and the design of the delivery strategy for fixed-point and covered areas, the delivery of high-energy electron beams to the desired target points and surface coverage is achieved, thereby enabling electron accumulation testing of the load at the corresponding locations.

[0052] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0053] In one embodiment, as shown in Figure 1, a method for targeted and surface delivery of charged particle beams is provided, comprising the following steps:

[0054] Step 202: Construct a high-energy electron emitter orbital model and determine the initial orbital altitude of the high-energy electrons.

[0055] Specifically, the coverage configuration of high-energy electrons is determined by constructing the fixed-point delivery trajectory configuration of high-energy electrons;

[0056] By defining the latitude of the coverage configuration using the location of the geomagnetic mirror point and the altitude at which high-energy electrons collide with the atmosphere, the mission orbit altitude of the high-energy electron transmitter can be determined.

[0057] This is understandable, because the geomagnetic dipole field is relative to O E The z-axis symmetry and the characteristic that the trajectory of a charged particle under the constraint of a geomagnetic dipole field is a synthesis of three motions result in the trajectory configuration of a high-energy charged particle under geomagnetic dipole field constraint as a rotating ellipsoid symmetric about the geomagnetic dipole. Its mathematical expression is:

[0058]

[0059] In the formula, (a,c) are the parameters to be determined.

[0060] In one embodiment, for the targeted delivery mode of high-energy electrons, the emission point position (x) S ,y S ,z S ) and target point location (xT ,y T ,z T All of these lie on the ellipsoidal surface; therefore, the trajectory configuration for fixed-point delivery is represented as:

[0061]

[0062] The parameters (a, c) can be determined from the fixed-point delivery trajectory configuration expression.

[0063] Based on the above fixed-point delivery trajectory configuration, considering that the motion of high-energy electrons under the action of the geomagnetic dipole field is composed of three types of motion: Larmor gyroscope around the geomagnetic field lines, reciprocating bounce between geomagnetic field mirror points, and drift along geomagnetic meridians, the trajectory of high-energy electrons should not be a completely covered ellipsoid, but rather an ellipsoidal ring.

[0064] In one embodiment, the ellipsoidal ring is formed by removing a certain width of the north-south curved surface, thus constraining latitude. The latitude constraint of the ellipsoidal ring is determined by the location of the geomagnetic mirror point and the altitude at which high-energy electrons collide with the atmosphere, thereby determining the initial orbital altitude of the high-energy electrons.

[0065] Specifically, considering the convenience of high-energy electron launch, the constraint characteristics of the geomagnetic field on the motion of charged particles, and the influence of the Earth's rotation, the operational orbit of the high-energy electron launcher is set as an equatorial circular orbit, with the orbital altitude to be determined. Using an equatorial circular orbit as the mission orbit of the high-energy electron launcher ensures the uniformity of the geomagnetic field vector at the initial launch moment. Based on this, the automatic drift rate of the high-energy electron launcher along the circular orbit can be fully utilized to adjust the launch time, increasing the degrees of control freedom. For high-energy electron launch in an equatorial circular orbit, with its orbital altitude set to H, the geocentric distance of the launch position satisfies:

[0066] r S =R E +H;

[0067] In the formula, R E The radius is the Earth's radius.

[0068] First, calculate the first latitude based on the location of the geomagnetic mirror point.

[0069] Based on the high-energy electron transmitter's operational trajectory design, the geomagnetic field strength corresponding to the launch location is calculated, expressed by the following formula:

[0070]

[0071] The throw angle is defined as the angle between the direction of the high-energy electron emission velocity and the in-situ geomagnetic field lines. Therefore, based on the geomagnetic mirror point constraint condition... and the throwing angle α at the moment of launch SUsing the formula Calculate the geomagnetic field strength B corresponding to the geomagnetic mirror point. M Analysis shows that the throwing angle α S The smaller the value, the stronger the geomagnetic field intensity B at the geomagnetic mirror point. M The larger.

[0072] Furthermore, based on the geomagnetic field strength B corresponding to the geomagnetic mirror point M Using the formula r M =r S cos 2 φ M and Comprehensive calculation of the first latitude φ corresponding to the geomagnetic mirror point M The calculation formula is expressed as:

[0073]

[0074] In the formula, B0 is the surface magnetic field strength at the equatorial plane.

[0075] Then, the second latitude is calculated based on the height of the atmosphere caused by high-energy electron impacts.

[0076] Considering that high-energy electrons will be absorbed upon impact with the atmosphere without rebounding, and that the default altitude of the Earth's atmosphere above the surface is H. A =100km, therefore, based on the set launch point location, launch velocity, and launch angle, the height H of the Earth's atmospheric boundary is calculated. A =100km corresponds to the second latitude φ A .

[0077] After being emitted, high-energy electrons will undergo Larmor cyclotron motion and reciprocating bounces between mirror points around the geomagnetic field lines. Therefore, the second latitude φ corresponding to the altitude at which the high-energy electrons impact the atmosphere can be calculated based on the geocentric distance of the cluster of attached magnetic field lines. A .

[0078] The formula for calculating the distance between the Earth's centers is: r = r S cos 2 φ, then the second latitude corresponding to the height of the high-energy electron impact on the atmosphere is φ. A The calculation formula is:

[0079] r A =r S cos 2 φ A ;

[0080] The Earth's center distance r corresponding to the altitude of the atmosphere when high-energy electrons collide A =R E +H A Substituting into the above formula, we can solve for the second latitude φ.A .

[0081] Finally, the first latitude φ M With the second latitude φ A By comparison, the smaller value of the two is selected as the height constraint φ of the ellipsoidal ring. min That is, the height range of the elliptical ring is limited to [-φ]. min φ min ].

[0082] The desired delivery coverage range is defined as H. L ~H H Considering the target orbit needs to intersect with the ellipsoidal ring and the Earth's atmosphere needs to be at an altitude of 100km, based on the principle that the outermost edge of the delivery elliptical ring is determined by the launch point's orbital altitude, the outer edge altitude of the high-energy electron transmitter mission orbit needs to be greater than H. H The inner edge height of 100km automatically meets the requirement of being less than H. L .

[0083] For example, assuming the desired delivery coverage orbital altitude is 300–1100 km, then the mission orbital altitude H of the high-energy electron transmitter is taken as 1200 km, and the delivery angle is... The first latitude φ is then calculated. M With the second latitude φ A for:

[0084]

[0085] Therefore, the height range of the elliptical ring, i.e. the height range of the trajectory of the high-energy electron, is limited to [-14.7 14.7] (deg). The projection of the high-energy electron delivery ellipsoid ring onto the equatorial plane is shown in Figure 3. The relationship between the high-energy electron delivery angle and the latitude of the mirror point is shown in Figure 4. It can be seen from the figure that the smaller the delivery angle, the larger the latitude of the corresponding mirror point, and the smaller the inner boundary of the elliptical ring.

[0086] Step 204: Based on the Larmor cyclotron motion, the reciprocating bounce motion between mirror points of the geomagnetic field, and the drift motion along the geomagnetic meridian, determine the trajectory of high-energy electrons and construct a fixed-point delivery strategy and a surface delivery strategy; the fixed-point delivery strategy includes the design of the first delivery angle, and the surface delivery strategy includes the design of the second delivery angle.

[0087] It is understandable that the trajectory of high-energy electrons is a combination of Larmor cyclotron motion, reciprocating bounce motion between mirror points of the geomagnetic field, and drift motion along geomagnetic meridians. These three types of motion correspond to the expected point-to-point and coverage delivery objectives, and the parameters of the launch time are determined in reverse based on the coverage delivery objectives.

[0088] In one embodiment, the fixed-point delivery strategy includes the design of the first throwing angle, the launch speed, and the launch time.

[0089] First, the first throwing angle is designed:

[0090] As shown in step 202, the design of the throwing angle determines the inner boundary of the elliptical ring. The smaller the throwing angle, the larger the latitude of the corresponding mirror point, and the smaller the inner boundary of the elliptical ring (it cannot be less than φ). A The larger the feasible coverage ellipse (corresponding to the inner boundary), the better. Furthermore, the timing requirements for point-to-point delivery also influence the design of the throwing angle.

[0091] After being emitted from the equatorial circular orbit, high-energy electrons will undergo a complex motion involving Larmor gyration, repeated bouncing, and drifting along geomagnetic meridians, which is a typical periodic motion.

[0092] The period T of the Lamoer spin L The calculation formula is:

[0093]

[0094] In the formula, ν is the relativistic factor (c is the speed of light, v is the instantaneous velocity of high-energy electrons); B represents the local geomagnetic field strength.

[0095] Studies have shown that the period T of the Larmor cyclotron L The period is much smaller than the corresponding period of the reciprocating bounce between mirror points of the geomagnetic field and the drift along the geomagnetic meridian. Therefore, the design of the throwing angle can only consider the influence of the period of the reciprocating bounce between mirror points of the geomagnetic field and the drift along the geomagnetic meridian.

[0096] The period T of the cyclical bounce motion between mirror points of the geomagnetic field b The calculation formula is:

[0097]

[0098] In the formula, v S Here, represents the launch speed, and represents a controllable parameter.

[0099] The period T of drifting along the geomagnetic meridian d The calculation formula is:

[0100]

[0101] By T b The calculation formula and T d Analysis of the calculation formula shows that T b and T dIt can be calculated from the high-energy electron state at the time of launch (launch position, launch velocity, and launch angle), and is a definite quantity. Therefore, using the above formula, the first launch angle α under the fixed-point delivery strategy can be determined. S1 To carry out the design.

[0102] Furthermore, since high-energy electrons undergo Larmor cyclotron motion around the geomagnetic field lines, the cyclotron radius affects the accuracy of pinpoint delivery. Therefore, based on the influence of Larmor cyclotron motion, the cyclotron radius ρ during pinpoint delivery is calculated. L , is represented as:

[0103]

[0104] In the formula, v ⊥ Let v be the velocity of the high-energy electron perpendicular to the geomagnetic field lines. Under the influence of the geomagnetic dipole field, the Lorentz force generated by the geomagnetic field does no work on the high-energy electron, and the electron's velocity is constant. ⊥ satisfy:

[0105]

[0106] In the formula, v || The velocity of high-energy electrons parallel to the geomagnetic field lines varies according to the following law:

[0107]

[0108] In the formula, Let be the magnetic moment of the high-energy electron, and be a constant.

[0109] Then the launch speed is designed:

[0110] The gradient drift and curvature drift corresponding to the geomagnetic dipole magnetic field, given by the Roederer and Northrop guiding center equations, are expressed as follows:

[0111]

[0112] In the formula,

[0113] Considering the high-energy electron's drift along the geomagnetic orbital plane, and taking φ = 0, the velocity v of the high-energy electron drifting along the entire geomagnetic meridian is... λ The calculation formula is:

[0114]

[0115] Based on the velocity v of high-energy electrons drifting along the geomagnetic meridian λ To adjust the launch speed.

[0116] Finally, the launch timing was designed:

[0117] High-energy electrons are emitted from position (x) S ,y S ) to target point position (x T ,y T ,z T The trajectory of the satellite can be decomposed into two parts: drift along a geomagnetic meridian and movement along a single geomagnetic field line; therefore, the delivery time can also be composed of these two parts, and can be represented as follows:

[0118] Δt = Δt1 ± Δt2;

[0119] In the formula, Δt1 is the drift time along the geomagnetic meridian, Δt2 is the time of movement along a single geomagnetic field line, and '±' is selected as '+' or '-' according to the movement trend of high-energy electrons. '+' is taken when high-energy electrons move towards the geomagnetic north and south poles, and '-' is taken when high-energy electrons move towards the geomagnetic surface.

[0120] Therefore, the period T of a drift motion along the geomagnetic meridian d The formula for calculating the arc length of a high-energy electron moving along the geomagnetic track plane is:

[0121] L = v λ T d ;

[0122] Furthermore, the formula for calculating the geocentric angle corresponding to this arc length is:

[0123]

[0124] Based on the high-energy electron emission position (x S ,y S Calculate the corresponding geomagnetic longitude λ S Target point location (x T ,y T ,z T Calculate the corresponding geomagnetic longitude λ T The formula for calculating the drift time Δt1 of high-energy electrons along the geomagnetic meridian is:

[0125]

[0126] Figure 5 shows the relationship between the 1 / 4 period and part of the time of the high-energy electron's reciprocating bounce and the latitude angle. Therefore, the estimation formula for the time Δt2 of motion along a single geomagnetic field line is:

[0127]

[0128] In the formula, φT Based on the target point location (x) T ,y T ,z T The formula is:

[0129]

[0130] Based on this, the delivery time Δt can be calculated.

[0131] Further analysis reveals that for a target point on the same geomagnetic field line, the time Δt2 for movement along a single geomagnetic field line is constant. If a delivery time Δt is required, the time Δt1 for drifting along the geomagnetic meridian can be adjusted by changing the launch time, thereby meeting the delivery time requirement.

[0132] Specifically, based on the equatorial circular orbit altitude H of the high-energy electron emitter, its corresponding orbital period is calculated as follows:

[0133]

[0134] In the formula, μ E is the Earth's gravitational constant.

[0135] Therefore, the relationship between Δt1 and adjusting the high-energy electron emission time and adjusting Δt1 is:

[0136]

[0137] Assume the launch time is delayed by Δt s Then the longitude of the eastward movement is Then the longitude λ of the launch point Snew Updated to:

[0138] λ Snew =λ S +Δλ;

[0139] Assume the launch time is advanced by Δt s Then the equivalent westward retreat longitude is Then the longitude λ of the launch point Snew Updated to:

[0140] λ Snew =λ S -Δλ;

[0141] Substitute the formula for the launch point longitude for delayed and advanced launch times into the formula for Δt1, replacing the geomagnetic longitude λ. S Then the updated Δt1 can be calculated.

[0142] Figure 6 shows the trajectory and velocity of high-energy electrons obtained through this step. As can be seen from the figure, under the action of the geomagnetic dipole field, the trajectory of the high-energy charged particles is consistent with the expected design, and the velocity meets the requirements for rapid delivery to fixed points and over the entire area.

[0143] In one embodiment, the surface delivery strategy includes the design of a second throwing angle and the design of a launch speed.

[0144] It is understandable that for a single high-energy electron emitter, the position of the emission point constrains the outer boundary of the elliptical ring projected onto the equatorial plane, while the throwing angle determines the inner boundary of the elliptical ring: the larger the throwing angle, the smaller the inner boundary of the elliptical ring projected onto the equatorial plane; the smaller the throwing angle, the larger the inner boundary of the elliptical ring projected onto the equatorial plane; however, the trajectory of the high-energy electrons all belong to the same elliptical surface, that is, the elliptical ring mode remains unchanged.

[0145] The emission velocity affects the speed of high-energy electrons, but not the ellipsoid. Therefore, based on the influence of Larmor cyclotron motion, the cyclotron radius during surface delivery is calculated using the following formula:

[0146]

[0147] In the formula, v ⊥ This represents the high-energy electron velocity component perpendicular to the geomagnetic field lines.

[0148] From the above formula, we can see that B and v ⊥ The radius of Larmor cyclotron motion of an electron is affected by: v ⊥ The larger B is, the larger ρ is; the larger B is, the smaller ρ is. Correspondingly, the Larmor cyclotron frequency is calculated as:

[0149]

[0150] As calculated by the above formula, the Larmor cyclotron frequency is very high, and the corresponding cyclotron velocity is much higher than the radial reciprocating velocity and the drift velocity along the geomagnetic meridian. Therefore, when calculating the time it takes for a high-energy electron to travel from the emission point to the target position, the time corresponding to the cyclotron motion can be ignored.

[0151] For delivery over a single ellipsoidal surface, the second throwing angle and launch velocity are determined by calculating the period of drift along the geomagnetic meridian, based on the periodic effect of drift along the geomagnetic meridian.

[0152] Specifically, for the coverage of a certain ellipsoid, since high-energy electrons drift very quickly along meridians, this can be achieved by continuously launching high-energy electrons along a constant trajectory (see the expression for the fixed-point delivery trajectory configuration) at a set launch angle and speed. This is because the period T of the repeated bouncing motion... b Much smaller than the period T of drift along the geomagnetic meridiand We can consider only the coverage along the meridian; by T d Analysis of the expression shows that for high-energy electrons emitted from the same position at the same throwing angle, if the emission velocities are different, then T d Inconsistent, with Proportional; by adjusting the launch speed v s This generates a sequence of emitted electrons, achieving coverage over a certain time span. The throwing angle α can also be adjusted. S To achieve similar coverage capability. Therefore, based on the above analysis, the launch velocity and / or second launch angle α under the coverage delivery strategy can be adjusted. S2 Design it to achieve coverage.

[0153] For multi-ellipsoidal coverage delivery, transmitters at different orbital altitudes are deployed by combining single ellipsoidal coverage with different orbits.

[0154] Specifically, for coverage of different ellipsoids, high-energy electron transmitters in different orbits can be deployed, and a single transmitter can emit electrons to cover a specific ellipsoid. Transmitters deployed at different orbital altitudes will have varying degrees of coverage density on the ellipsoidal rings; the higher the orbital altitude, the greater the meridional drift velocity, and the sparser the coverage.

[0155] Step 206: Determine the outer boundary constraint of the orbit for fixed-point delivery based on the initial orbital height of the high-energy electrons, and determine the inner boundary constraint of the orbit for fixed-point delivery based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy.

[0156] Step 208: Determine the outer boundary constraint of the orbital operation for surface delivery based on the launch point location, and determine the inner boundary constraint of the orbital operation for surface delivery based on the second launch angle. The high-energy electron transmitter operates according to the orbit and continuously emits high-energy electron beams based on the surface delivery strategy.

[0157] In the aforementioned method for targeted and surface delivery of charged particle beams, the initial orbital height of the high-energy electrons is determined by constructing a high-energy electron emitter orbital model; the trajectory of the high-energy electrons is determined based on Larmor cyclotron motion, reciprocating bounce motion between geomagnetic mirror points, and drift motion along geomagnetic meridians, and a targeted delivery strategy and a surface delivery strategy are constructed; the targeted delivery strategy includes the design of a first delivery angle, and the surface delivery strategy includes the design of a second delivery angle; the outer boundary constraint of the targeted delivery orbit is determined based on the initial orbital height, and the inner boundary constraint of the targeted delivery orbit is determined based on the first delivery angle, and the high-energy electron emitter operates according to the orbit and emits a high-energy electron beam based on the targeted delivery strategy; the outer boundary constraint of the surface delivery orbit is determined based on the emission point location, and the inner boundary constraint of the surface delivery orbit is determined based on the second delivery angle, and the high-energy electron emitter operates according to the orbit and continuously emits a high-energy electron beam based on the surface delivery strategy.

[0158] This invention, by constructing a fixed-point delivery strategy and a surface delivery strategy, quantitatively provides the relationship between various physical parameters of the ellipsoidal ring corresponding to the high-energy electron trajectory and the high-energy electron emission parameters. Specifically, the constructed high-energy electron transmitter trajectory provides the initial orbital height of the high-energy electron transmitter; the fixed-point delivery strategy quantitatively provides the required emission speed, emission time, and delivery angle for fixed-point delivery, enabling rapid and timely delivery to a specific point in space; the surface delivery strategy achieves the capability of delivery over a single ellipsoid or multiple ellipsoidal surfaces; this invention can be used to perform electron accumulation testing on loads at corresponding locations.

[0159] In one embodiment, as shown in Figure 2, a spatial coordinate system O is established. E xyz, with the +z axis representing the direction of the geomagnetic dipole, and its magnetic moment being μ. E Then the geomagnetic field of a point P(x,y,z) in space is calculated as follows:

[0160]

[0161] In the formula, B0 = 3.07 × 10 -5 (T) represents the surface magnetic field strength at the Earth's equator. R is the geocentric distance from point P. E The radius is the Earth's radius.

[0162] Due to the minuscule mass of electrons, we can neglect the effect of Earth's gravity and construct a dynamic model of a high-energy electron located at a point P(x,y,z) in space under the influence of a geomagnetic dipole field, based on the geomagnetic field. The dynamic model is expressed as follows:

[0163]

[0164] In the formula, m e e is the electron mass; e is the unit charge; γ is the relativistic factor; (v x ,v y ,v z () represents the high-energy electron velocity v in O E The projection components of the xyz coordinate system; (x,y,z) is the position of point P in space; (B x B y B z ) represents the geomagnetic field of point P in space.

[0165] It is worth noting that, since high-energy electrons correspond to high velocities, a relativistic factor needs to be introduced, and the calculation expression is as follows:

[0166]

[0167] In the formula, c is the speed of light; v is the instantaneous velocity of high-energy electrons.

[0168] It should be understood that although the steps in the flowchart of Figure 1 are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some of the steps in Figure 1 may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the sub-steps or stages of other steps.

[0169] In one embodiment, as shown in FIG7, a charged particle beam delivery device for point-to-point and surface-to-surface application is provided, comprising: a trajectory construction module 402, a delivery strategy design module 404, a point-to-point delivery module 406, and a surface-to-surface delivery module 408, wherein:

[0170] The orbit construction module 402 is used to construct the orbital model of the high-energy electron emitter and determine the initial orbital altitude of the high-energy electrons.

[0171] The delivery strategy design module 404 is used to determine the trajectory of high-energy electrons based on Larmor cyclotron motion, reciprocating bounce motion between mirror points of the geomagnetic field, and drift motion along geomagnetic meridians, and to construct a fixed-point delivery strategy and a surface delivery strategy. The fixed-point delivery strategy includes the design of the first throwing angle, and the surface delivery strategy includes the design of the second throwing angle.

[0172] The fixed-point delivery module 406 is used to determine the outer boundary constraint of the fixed-point delivery orbit based on the initial orbital height of the high-energy electrons, and to determine the inner boundary constraint of the fixed-point delivery orbit based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy.

[0173] The surface delivery module 408 is used to determine the outer boundary constraint of the surface delivery orbit based on the launch point location, and to determine the inner boundary constraint of the surface delivery orbit based on the second delivery angle. The high-energy electron transmitter operates according to the orbit and continuously emits high-energy electron beams based on the surface delivery strategy.

[0174] Specific limitations regarding the charged particle beam positioning and coverage delivery device can be found in the limitations of the charged particle beam positioning and coverage delivery method described above, and will not be repeated here. Each module in the aforementioned charged particle beam positioning and coverage delivery device can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device in hardware form, or stored in the memory of a computer device in software form, so that the processor can call and execute the corresponding operations of each module.

[0175] In one embodiment, a computer device is provided, which may be a server, and its internal structure diagram is shown in Figure 8. The computer device includes a processor, memory, network interface, and database connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system, computer programs, and a database. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The database stores data on the targeted and surface delivery of charged particle beams. The network interface communicates with external terminals via a network connection. When the computer program is executed by the processor, it implements a method for targeted and surface delivery of charged particle beams.

[0176] Those skilled in the art will understand that the structure shown in Figure 8 is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or may combine certain components, or may have different component arrangements.

[0177] In one embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program, the processor executing the computer program to perform the following steps:

[0178] Step 202: Construct a high-energy electron emitter orbital model and determine the initial orbital altitude of the high-energy electrons.

[0179] Step 204: Based on the Larmor cyclotron motion, the reciprocating bounce motion between mirror points of the geomagnetic field, and the drift motion along the geomagnetic meridian, determine the trajectory of high-energy electrons and construct a fixed-point delivery strategy and a surface delivery strategy; the fixed-point delivery strategy includes the design of the first delivery angle, and the surface delivery strategy includes the design of the second delivery angle.

[0180] Step 206: Determine the outer boundary constraint of the orbit for fixed-point delivery based on the initial orbital height of the high-energy electrons, and determine the inner boundary constraint of the orbit for fixed-point delivery based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy.

[0181] Step 208: Determine the outer boundary constraint of the orbital operation for surface delivery based on the launch point location, and determine the inner boundary constraint of the orbital operation for surface delivery based on the second launch angle. The high-energy electron transmitter operates according to the orbit and continuously emits high-energy electron beams based on the surface delivery strategy.

[0182] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, the computer program performing the following steps when executed by a processor:

[0183] Step 202: Construct a high-energy electron emitter orbital model and determine the initial orbital altitude of the high-energy electrons.

[0184] Step 204: Based on the Larmor cyclotron motion, the reciprocating bounce motion between mirror points of the geomagnetic field, and the drift motion along the geomagnetic meridian, determine the trajectory of high-energy electrons and construct a fixed-point delivery strategy and a surface delivery strategy; the fixed-point delivery strategy includes the design of the first delivery angle, and the surface delivery strategy includes the design of the second delivery angle.

[0185] Step 206: Determine the outer boundary constraint of the orbit for fixed-point delivery based on the initial orbital height of the high-energy electrons, and determine the inner boundary constraint of the orbit for fixed-point delivery based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy.

[0186] Step 208: Determine the outer boundary constraint of the orbital operation for surface delivery based on the launch point location, and determine the inner boundary constraint of the orbital operation for surface delivery based on the second launch angle. The high-energy electron transmitter operates according to the orbit and continuously emits high-energy electron beams based on the surface delivery strategy.

[0187] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0188] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0189] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these modifications and improvements all fall within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the appended claims.

Claims

1. A method for targeted and surface delivery of charged particle beams, characterized in that, The method includes: constructing a high-energy electron emitter orbital model to determine the initial orbital altitude of the high-energy electrons; determining the high-energy electron trajectory based on Larmor cyclotron motion, reciprocating bounce motion between geomagnetic mirror points, and drift motion along geomagnetic meridians; and constructing a fixed-point delivery strategy and a surface delivery strategy. The fixed-point delivery strategy includes the design of a first delivery angle, and the surface delivery strategy includes the design of a second delivery angle. The method also includes determining the outer boundary constraints of the fixed-point delivery orbital operation based on the initial orbital altitude of the high-energy electrons, and determining the inner boundary constraints based on the first delivery angle. The transmitter operates along a trajectory and emits a high-energy electron beam based on the fixed-point delivery strategy. The outer boundary constraint of the trajectory for surface delivery is determined based on the launch point location, and the inner boundary constraint of the trajectory for surface delivery is determined based on the second launch angle. The high-energy electron transmitter operates along the trajectory and continuously emits a high-energy electron beam based on the surface delivery strategy. The fixed-point delivery strategy includes the design of the first launch angle, as well as the design of the launch speed and launch time. The design of the first launch angle includes: based on the periodic influence of the reciprocating bounce motion between geomagnetic mirror points and the drift motion along geomagnetic meridians, and through the period of the repeated bouncing motion... The calculation of the period of drift along the geomagnetic meridian is used to determine the first launch angle; and the cyclotron radius for precise delivery is calculated based on the influence of Larmor cyclotron motion. The design of the launch speed includes: determining the overall drift speed of the high-energy electron along the geomagnetic meridian based on the gradient drift and curvature drift corresponding to the geomagnetic dipole magnetic field, and adjusting the launch speed accordingly; the design of the launch timing includes: determining the overall drift speed along the geomagnetic meridian and the motion along a single geomagnetic field line based on the drift time along the geomagnetic meridian and the motion along a single geomagnetic field line. The delivery time is calculated; and the drift time along the geomagnetic meridian is adjusted by adjusting the launch time to meet the delivery time requirements; the coverage delivery strategy includes the design of the second throwing angle and the design of the launch speed; for single ellipsoidal coverage delivery, the second throwing angle and launch speed are determined by calculating the period of drift along the geomagnetic meridian based on the influence of the period of drift along the geomagnetic meridian; and the gyroscopic radius is calculated based on the influence of the Larmor cyclotron motion; for multi-ellipsoidal coverage delivery, transmitters at different orbital heights are deployed by combining single ellipsoidal coverage with different orbits.

2. The method for targeted and surface delivery of charged particle beams according to claim 1, characterized in that, Also includes: Establish a spatial coordinate system, calculate the geomagnetic field at a certain point in the coordinate system, and construct a dynamic model of high-energy electrons under the action of a geomagnetic dipole field based on the geomagnetic field.

3. The method for targeted and surface delivery of charged particle beams according to claim 1 or 2, characterized in that, Constructing a high-energy electron transmitter orbital model and determining the initial orbital altitude of the high-energy electrons includes: constructing a fixed-point delivery trajectory configuration of the high-energy electrons and determining the coverage configuration of the high-energy electrons; and limiting the latitude of the coverage configuration by the geomagnetic mirror point position and the altitude at which the high-energy electrons impact the atmosphere to determine the initial orbital altitude of the high-energy electrons.

4. The method for targeted and surface delivery of charged particle beams according to claim 3, characterized in that, Constructing the fixed-point delivery trajectory configuration of high-energy electrons and determining the coverage configuration of high-energy electrons includes: the fixed-point delivery trajectory configuration is represented as: In the formula, Location of the launch point; The location of the target point; The parameters to be determined are as follows: Based on the fixed-point delivery trajectory configuration, the trajectory of high-energy electrons is determined according to the Larmor cyclotron motion, the reciprocating bounce motion between geomagnetic mirror points, and the drift motion along the geomagnetic meridian. The coverage configuration of the high-energy electrons is determined to be an ellipsoidal ring based on the trajectory of the high-energy electrons.

5. The method for targeted and surface delivery of charged particle beams according to claim 4, characterized in that, The latitude of the coverage configuration is limited by the location of the geomagnetic mirror point and the height of the high-energy electron impact on the atmosphere to determine the initial orbital altitude of the high-energy electron. This includes: calculating a first latitude based on the location of the geomagnetic mirror point and calculating a second latitude based on the height of the high-energy electron impact on the atmosphere; selecting the smaller value between the first latitude and the second latitude as the orbital altitude constraint of the ellipsoidal ring to determine the initial orbital altitude of the high-energy electron.

6. A device for targeted and surface delivery of charged particle beams, characterized in that, The method for targeted and surface delivery of charged particle beams according to any one of claims 1 to 5, the apparatus comprising: an orbit construction module for constructing an orbital model of a high-energy electron emitter and determining the initial orbital height of the high-energy electrons; and a delivery strategy design module for determining the trajectory of the high-energy electrons based on Larmor cyclotron motion, reciprocating bounce motion between geomagnetic mirror points, and drift motion along geomagnetic meridians, and constructing a targeted delivery strategy and a surface delivery strategy; the targeted delivery strategy includes the design of a first delivery angle, and the surface delivery strategy includes the design of a second delivery angle; targeted delivery... The first module is used to determine the outer boundary constraint of the orbit for fixed-point delivery based on the initial orbital height of the high-energy electrons, and the inner boundary constraint of the orbit for fixed-point delivery based on the first delivery angle. The high-energy electron transmitter operates according to the orbit and emits a high-energy electron beam based on the fixed-point delivery strategy. The second module is used to determine the outer boundary constraint of the orbit for surface delivery based on the launch point position, and the inner boundary constraint of the orbit for surface delivery based on the second delivery angle. The high-energy electron transmitter operates according to the orbit and continuously emits a high-energy electron beam based on the surface delivery strategy.

7. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 5.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

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