CN110077629B - Method and system for shielding local low-energy electronic environment of spacecraft by using artificial magnetic field - Google Patents
Method and system for shielding local low-energy electronic environment of spacecraft by using artificial magnetic field Download PDFInfo
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Abstract
The invention relates to a method and a system for shielding a local low-energy electronic environment of a spacecraft by using an artificial magnetic field, belonging to the technical field of space radiation. The technical scheme of the invention is as follows: determining the magnetic field intensity and spatial distribution of the solenoid coil according to the number of turns, current and other parameters of the solenoid coil; arranging a certain number of solenoid coils at different positions on the spacecraft, and analyzing the change condition of the local low-energy electron radiation environment of the spacecraft under the action of a magnetic field; the parameters, position and layout of the solenoid coil are adjusted to ensure that the low energy electron radiation environment of the local region of interest is reduced to an acceptable level.
Description
Technical Field
The invention relates to a method and a system for shielding a local low-energy electronic environment of a spacecraft by using an artificial magnetic field, belonging to the technical field of space radiation.
Background
The surface charge-discharge effect can be caused by the interaction of the thermal plasma in the space and the surface material of the spacecraft, and the charge current source comprises charge electron current, charge proton current, secondary electron current, back scattering electron current, photo-generated electron current, current caused by the difference of resistance and capacitance inductance of adjacent surfaces, electron or ion current actively emitted by the satellite and the like. The satellite reaches the final charge potential when all current sources are balanced, i.e., the total charge current equals zero. Electrical discharges are induced when the relative charge of the adjacent surfaces of the spacecraft is too high, and the resulting electromagnetic pulses interfere with the proper operation of the spacecraft.
At present, the surface potential protection design of the spacecrafts at home and abroad is generally based on conducting and grounding treatment on surface materials, so that the surface potential can meet the requirements. However, due to the requirement on the transmittance of electromagnetic waves, part of the high-resistivity surface materials cannot reduce the charging potential through an effective grounding means, so that the materials have a charging risk, and a hidden danger influencing the on-orbit reliable operation of the spacecraft is formed.
Theoretical analysis and on-orbit tests show that the charging electron current plays a decisive role in charging, and if a certain method can be adopted to reduce the charging electron current, the charging effect can be greatly relieved. Since the primary cause of charging the surface of the spacecraft is low-energy electrons (in the order of tens of keV), which are easily deflected by the magnetic field, the magnetic shielding method is considered to alleviate the local low-energy electron radiation environment of the spacecraft.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method overcomes the defects of the prior art, provides a method for shielding the local low-energy electronic environment of the spacecraft by using the artificial magnetic field, and can solve the problem that the surface charging potential of part of surface materials of the spacecraft can not be reduced by measures such as grounding and the like.
The technical solution of the invention is as follows: the method for shielding the local low-energy electronic environment of the spacecraft by using the artificial magnetic field comprises the following steps:
designing a solenoid coil, selecting parameters and layout of the solenoid coil; the parameters comprise size, number of turns of coil and energizing current;
establishing a three-dimensional space model of the spacecraft;
energizing selected solenoid coils to enable the solenoid coils to generate magnetic fields, and determining a magnetic field model of the magnetic fields generated by the solenoid coils in the spacecraft three-dimensional space model according to parameters of the solenoid coils;
respectively counting the change of low-energy electron radiation generated by electron radiation environments in local low-energy ranges of the spacecraft on a protected surface of the spacecraft before and after the action of a magnetic field in a three-dimensional space model of the spacecraft, wherein the three-dimensional space model of the spacecraft comprises the magnetic field model; if the change of the low-energy electron radiation environment on the surface of the spacecraft after the action of the magnetic field meets the design requirement, the designed solenoid coil is used; if the magnetic field does not meet the design requirements, adjusting the parameters and the layout of the solenoid coil, and counting the change of the low-energy electron radiation environment on the surface of the spacecraft before and after the action of the magnetic field again until the change of the low-energy electron radiation environment on the surface of the spacecraft meets the design requirements; the protected surface of the spacecraft is the surface of the spacecraft needing magnetic field shielding.
Further, the layout method comprises the following steps: arranging eight solenoid coils on four corners of two cabin plates of the spacecraft respectively; the two deck boards are parallel to each other and are both vertical to the protected surface of the spacecraft; the current directions in the solenoid coils on the same deck plate are the same, and the current directions in the solenoid coils on different deck plates are opposite.
Further, the mounting surface of the solenoid coil is perpendicular to the surface to be protected, and the axial direction of the solenoid coil is parallel to the surface to be protected and perpendicular to the mounting surface.
Further, the number of turns of the solenoid coil is not less than 100000, and the current in the solenoid coil is not less than 10A.
Further, the method for counting the change of the low-energy electron radiation environment on the surface of the spacecraft comprises the following steps: and counting the injection flux of low-energy electrons on the surface of the spacecraft, and calculating the current of the unit area of the surface of the spacecraft according to the injection flux.
Further, the local low energy range is a spatial range that obeys a maxwell distribution.
Further, the parameter of the Maxwell distribution is N-1.12 cm-3，T＝1.2×104eV。
Further, the particle emission flux of the local low energy range is characterized by
f(θ)＝fo cosθ，
Wherein theta is the included angle between the particle emission direction and the normal direction of the emission surface, f (theta) is the particle differential flux of a unit solid angle in the theta direction, and the unit is cm-2·s-1·sr-1·eV-1，f0Is the particle differential flux in cm-2·s-1·eV-1。
A system implemented according to a method for shielding a local low-energy electronic environment of a spacecraft with an artificial magnetic field, comprising:
a first module to design a solenoid coil, selecting parameters and layout of the solenoid coil; the parameters comprise size, number of turns of coil and energizing current;
the second module is used for establishing a spacecraft three-dimensional space model;
a third module, which energizes the selected solenoid coil to enable the solenoid coil to generate a magnetic field, and determines a magnetic field model of the magnetic field generated by the solenoid coil in the spacecraft three-dimensional space model according to the parameters of the solenoid coil;
the fourth module is used for establishing an electronic radiation environment model of the spacecraft in a local low-energy range;
the fifth module is used for respectively counting the changes of the low-energy electron radiation environments on the surface of the spacecraft before and after the action of the magnetic field; if the change of the low-energy electron radiation environment on the surface of the spacecraft after the action of the magnetic field meets the design requirement, the designed solenoid coil is used; if the magnetic field does not meet the design requirements, adjusting the parameters and the layout of the solenoid coil, and counting the change of the low-energy electron radiation environment on the surface of the spacecraft before and after the action of the magnetic field again until the change of the low-energy electron radiation environment on the surface of the spacecraft meets the design requirements.
Further, the layout method comprises the following steps: arranging eight solenoid coils on four corners of two cabin plates of the spacecraft respectively, wherein the current directions of the solenoid coils on each cabin plate are the same, and the current directions of the solenoid coils on the two cabin plates are opposite;
the mounting surface of the solenoid coil is vertical to the protected surface, and the axial direction of the solenoid coil is parallel to the protected surface and is vertical to the mounting surface; the protected surface is the surface of the spacecraft needing magnetic field shielding;
the number of turns of the solenoid coil is not less than 100000, and the current in the solenoid coil is not less than 10A.
Compared with the prior art, the invention has the advantages that:
1. the problem that the electrification of surface materials cannot be reduced through grounding measures at present can be solved.
According to the invention, the low-energy electrons are shielded in an artificial magnetic field mode, so that the surface charging current and potential of the spacecraft are reduced by a non-contact method, the problem that the surface charging potential of part of high-resistivity surface materials is difficult to effectively reduce through conventional grounding is solved, and the surface electrification hidden danger of the spacecraft is reduced.
2. The protection equipment can be opened and closed according to the needs, and energy is saved.
During a magnetic storm or geomagnetic substorm period, when the space low-energy electronic environment is severe and the spacecraft charging risk is high, the solenoid current can be started through the electromagnetic valve, so that the artificial magnetic field is started, and the local low-energy electronic environment of the spacecraft is reduced. During the quiet period of the space environment, when the space low-energy electronic environment is relaxed and the spacecraft has no charging risk, the current of the solenoid can be closed, and the artificial magnetic field can be closed, so that the energy of the spacecraft can be saved.
3. The operating principle determines a high reliability of the measures.
According to the invention, the low-energy space electronic environment is reduced by electrifying the solenoid to generate an artificial magnetic field, the electrification risk of the spacecraft can be effectively ensured to be reduced under the working condition of the solenoid, and the problem of potential electrification hazards of the spacecraft caused by the fact that a surface conductive film is damaged and difficult to detect in the installation process of the conventional common spacecraft surface material is solved.
Drawings
FIG. 1 is a flow chart of the magnetic field shielding-based surface charging protection technology established by the invention;
FIG. 2 is a solenoid coil placement scheme for shielding the low energy electron radiation environment of a spacecraft to floor antenna location;
FIG. 3 is a schematic diagram of an isotropic particle source model
FIG. 4 is a low energy electron differential spectrum
FIG. 5 is a simulation of the motion of low energy electrons in a magnetic field
Fig. 6 shows the variation of the local low-energy electron radiation environment of the spacecraft under the scheme of fig. 2.
Detailed Description
The following is further described with reference to the accompanying drawings.
Referring to fig. 1, the method and system for shielding the local low-energy electronic environment of a spacecraft by using an artificial magnetic field specifically include the following steps:
(1) designing a solenoid coil, and adjusting parameters such as the size, the number of turns, the energizing current and the like of the coil to enable the solenoid coil to generate enough magnetic field intensity in a certain space range;
(2) establishing a spacecraft model and a magnetic field model of a solenoid coil;
(3) establishing a low-energy electron source model;
(4) the change of the local low-energy electron radiation environment of the spacecraft before and after the action of the magnetic field is analyzed through simulation;
(5) analyzing the local surface charging effect of the spacecraft before and after the action of the magnetic field;
(6) and (5) adjusting the parameters, the number and the layout of the solenoid coils, and repeating the steps (4) to (5) until the surface charging effect of the target position meets the control requirement.
The specific technical scheme is as follows:
(1) the solenoid coil and its magnetic field strength are determined.
Designing a solenoid coil, selecting parameters and layout of the solenoid coil; the parameters include size, number of coil turns, and energizing current.
The steady current can generate a magnetic field, which can be calculated with the following equation given the current:
where R is the distance from the field point to the source point, eRIs a unit vector, μ, from field point to source point0Is a constant value, mu0＝4×π×10-7N/A2N is the number of turns of the solenoid coil, and r is defined as a vector from the origin of coordinates to the field point, and r' is a vector from the origin of coordinates to the source point, then
I is the current value and dl' is the length of the current cell. Then the magnetic induction intensity in each direction is obtained as follows:
the diameter of the solenoid is 10cm, the number of coil turns is 100000, and the current in the coil is 10A.
(2) And establishing a spacecraft model and a magnetic field model of the solenoid coil.
And establishing a three-dimensional space model of the spacecraft. The spacecraft model is mainly used for establishing a three-dimensional geometric model according to the overall dimension of a spacecraft, so that the spatial position, distribution and the like of a magnetic field can be conveniently determined under unified coordinates.
And electrifying the selected solenoid coil to enable the solenoid coil to generate a magnetic field, and determining a magnetic field model of the magnetic field generated by the solenoid coil in the spacecraft three-dimensional space model according to the parameters of the solenoid coil. The magnetic field model calculates the magnetic induction intensity and direction of different spatial positions by using the formula in (1) mainly according to the selected solenoid parameters.
The spacecraft has the size of 2m multiplied by 4m and is provided with 2 solar panels, 8 solenoids are divided into 2 groups and distributed on 4 angles of a plus X plate and a minus X plate of a satellite cabin plate, and the current directions of the 4 solenoids on each plate are the same, but the current directions of the plus X plate and the minus X plate are opposite. The mounting surface of the solenoid coil is perpendicular to the protected surface, and the axial direction of the solenoid coil is parallel to the protected surface and perpendicular to the mounting surface. As shown in fig. 2. The protected surface of the spacecraft is the surface of the spacecraft needing magnetic field shielding. The mounting surface of the solenoid coil is perpendicular to the protected surface, and the axial direction of the solenoid coil is parallel to the protected surface and perpendicular to the mounting surface.
(3) Modeling low energy electron sources
And establishing an electronic radiation environment model of the local low-energy range of the spacecraft. The local low energy range is a spatial range that follows a maxwell distribution. The space thermal plasma meets the characteristics of isotropy and uniformity in a kilometer space range, wherein the isotropy means that the flux of particles in a unit solid angle in each direction of a certain point is equal, and the uniformity means that the flux characteristics of the particles at any point in space are the same. In order to examine the shielding effect of the artificial magnetic field on actual space particles, a particle space distribution model consistent with actual distribution should be constructed.
The space low-energy electron radiation environment is constructed according to the cosine law, namely the particle emission flux is characterized by
f(θ)＝focos(θ)
Wherein theta is the included angle between the particle emission direction and the normal direction of the emission surface, f (theta) is the particle differential flux of a unit solid angle in the theta direction, and the unit is cm-2·s-1·sr-1·eV-1，f0Is the particle differential flux in cm-2·s-1·eV-1. When a surface source of a cosine law is adopted to construct a space particle source, the obtained space distribution characteristics of the particle source meet the requirements of uniformity and isotropy.
For the actual space situation and the spacecraft simulation requirement, a spherical source with a certain radius can be adopted, and as shown in fig. 3, any surface infinitesimal on the spherical source emits particles according to the cosine law.
Aiming at electrons in the space thermal plasma, a particle spectrum with Maxwell distribution is adopted, and the structure of the particle spectrum is as follows:
wherein f is0Is the particle differential flux, in units of 1/(cm)2·s-1·eV-1) (ii) a N is the particle number density in cm-3(ii) a m is the mass of the particles in kg; k is the boltzmann constant, v is the particle velocity, and T is the particle temperature in eV. For low energy electrons in a spatial thermal plasma, N1.12 cm-3，T＝1.2×104eV. With this formula, the distribution of spatially low energy electrons can be obtained, as shown in fig. 4.
(4) The change of the local low-energy electron radiation environment of the spacecraft before and after the action of the magnetic field is analyzed through simulation.
And respectively counting the changes of the low-energy electron radiation environment on the surface of the spacecraft before and after the action of the magnetic field.
This part of the analysis is based on the charged particles being influenced by lorentz forces in a magnetic field,
where F is the Lorentz force experienced by the charged particles, q is the charge of the charged particles, v is the velocity of the charged particles, and B is the magnitude of the magnetic field. The magnetic induction intensity and the direction of any position in space are determined according to the magnetic field model, and the stress condition and the speed change condition in the motion process of the electronic trajectory can be calculated in real time according to the electronic trajectory, so that the trajectory change can be solved, and when the trajectory deviates from the three-dimensional model region of the spacecraft, the particle can be considered to be incapable of hitting the spacecraft. Enough charged particles are set, the calculation is carried out, the calculation result is counted, and parameters such as low-energy electron injection flux on the surface of the spacecraft, unit area current and the like can be obtained. The simulation diagram of the motion of low-energy electrons in a magnetic field is shown in FIG. 5.
(5) And analyzing the local surface charging effect of the spacecraft before and after the action of the magnetic field.
And (4) judging based on the statistical result of the step (4): if the change of the low-energy electron radiation environment on the surface of the spacecraft after the action of the magnetic field meets the design requirement, the designed solenoid coil is used; if the magnetic field does not meet the design requirements, adjusting the parameters and the layout of the solenoid coil, and counting the change of the low-energy electron radiation environment on the surface of the spacecraft before and after the action of the magnetic field again until the change of the low-energy electron radiation environment on the surface of the spacecraft meets the design requirements.
And determining parameters such as low-energy electron current density on the surface of the spacecraft, calculating the surface charging effect of the spacecraft by using a surface charging analysis tool, comparing the charging effect conditions before and after the magnetic field is applied, and determining the shielding effect of the magnetic field.
The electron current density incident on the location was counted for a solar screen of the spacecraft placed in the-Z plane of fig. 2, as shown in fig. 6. Current per unit area can be seen to be from 0.35nA/cm2Reduced to 0.22nA/cm2. The current per unit area is reduced by 37%, and a significant reduction in the corresponding charging potential can also occur.
And (3) adjusting the parameters, the number and the layout of the solenoid coils, and repeating the steps (4) to (5), so that the surface charging effect of the target position can meet higher control requirements.
The current 8 solenoid solution of fig. 2 is already substantially satisfactory. If the requirement on the electron current density is stricter, measures such as increasing the number of turns of the solenoid, the solenoid current, the number of the solenoids, changing the arrangement position and the like can be taken, and the steps (4) to (5) are repeated, so that the surface charging effect of the target position reaches a higher control requirement.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The method for shielding the local low-energy electronic environment of the spacecraft by utilizing the artificial magnetic field is characterized by comprising the following steps of:
designing a solenoid coil, selecting parameters and layout of the solenoid coil; the parameters comprise size, number of turns of coil and energizing current;
establishing a three-dimensional space model of the spacecraft;
energizing selected solenoid coils to enable the solenoid coils to generate magnetic fields, and determining a magnetic field model of the magnetic fields generated by the solenoid coils in the spacecraft three-dimensional space model according to parameters of the solenoid coils;
respectively counting the change of low-energy electron radiation generated by electron radiation environments in local low-energy ranges of the spacecraft on a protected surface of the spacecraft before and after the action of a magnetic field in a three-dimensional space model of the spacecraft, wherein the three-dimensional space model of the spacecraft comprises the magnetic field model; if the change of the low-energy electron radiation environment on the surface of the spacecraft after the action of the magnetic field meets the design requirement, the designed solenoid coil is used; if the magnetic field does not meet the design requirements, adjusting the parameters and the layout of the solenoid coil, and counting the change of the low-energy electron radiation environment on the surface of the spacecraft before and after the action of the magnetic field again until the change of the low-energy electron radiation environment on the surface of the spacecraft meets the design requirements; the protected surface of the spacecraft is the surface of the spacecraft needing magnetic field shielding.
2. The method for shielding the local low-energy electronic environment of the spacecraft of claim 1 by using the artificial magnetic field is characterized in that the method for layout is as follows: arranging eight solenoid coils on four corners of two cabin plates of the spacecraft respectively; the two deck boards are parallel to each other and are both vertical to the protected surface of the spacecraft; the current directions in the solenoid coils on the same deck plate are the same, and the current directions in the solenoid coils on different deck plates are opposite.
3. The method for shielding a local low-energy electronic environment of a spacecraft of claim 2 using an artificial magnetic field, wherein: the mounting surface of the solenoid coil is perpendicular to the protected surface, and the axial direction of the solenoid coil is parallel to the protected surface and perpendicular to the mounting surface.
4. The method for shielding the local low-energy electronic environment of the spacecraft by using the artificial magnetic field according to any one of claims 1 to 3, wherein the method comprises the following steps: the number of turns of the solenoid coil is not less than 100000, and the current in the solenoid coil is not less than 10A.
5. The method for shielding the local low-energy electronic environment of the spacecraft by using the artificial magnetic field as claimed in any one of claims 1 to 3, wherein the method for counting the change of the low-energy electronic radiation environment on the surface of the spacecraft comprises the following steps: and counting the injection flux of low-energy electrons on the surface of the spacecraft, and calculating the current of the unit area of the surface of the spacecraft according to the injection flux.
6. The method for shielding the local low-energy electronic environment of the spacecraft by using the artificial magnetic field according to any one of claims 1 to 3, wherein the method comprises the following steps: the local low energy range is a spatial range that follows a maxwell distribution.
7. Use of an artificial magnetic field for shielding of spacecraft local low energy electricity according to claim 6A method of sub-environment, characterized by: the parameter of the Maxwell distribution is N-1.12 cm-3，T＝1.2×104eV。
8. The method for shielding the local low-energy electronic environment of the spacecraft by using the artificial magnetic field according to any one of claims 1 to 3, wherein the method comprises the following steps: the particle emission flux in the local low energy range is characterized by
f(θ)＝focosθ，
Wherein theta is the included angle between the particle emission direction and the normal direction of the emission surface, f (theta) is the particle differential flux of a unit solid angle in the theta direction, and the unit is cm-2·s-1·sr-1·eV-1，f0Is the particle differential flux in cm-2·s-1·eV-1。
9. A system implemented by the method for shielding a local low-energy electronic environment of a spacecraft according to claim 1, comprising:
a first module to design a solenoid coil, selecting parameters and layout of the solenoid coil; the parameters comprise size, number of turns of coil and energizing current;
the second module is used for establishing a spacecraft three-dimensional space model;
a third module, which energizes the selected solenoid coil to enable the solenoid coil to generate a magnetic field, and determines a magnetic field model of the magnetic field generated by the solenoid coil in the spacecraft three-dimensional space model according to the parameters of the solenoid coil;
the fourth module is used for establishing an electronic radiation environment model of the spacecraft in a local low-energy range;
the fifth module is used for respectively counting the changes of the low-energy electron radiation environments on the surface of the spacecraft before and after the action of the magnetic field; if the change of the low-energy electron radiation environment on the surface of the spacecraft after the action of the magnetic field meets the design requirement, the designed solenoid coil is used; if the magnetic field does not meet the design requirements, adjusting the parameters and the layout of the solenoid coil, and counting the change of the low-energy electron radiation environment on the surface of the spacecraft before and after the action of the magnetic field again until the change of the low-energy electron radiation environment on the surface of the spacecraft meets the design requirements.
10. The system of claim 9, wherein the method of placement is: arranging eight solenoid coils on four corners of two cabin plates of the spacecraft respectively, wherein the current directions of the solenoid coils on each cabin plate are the same, and the current directions of the solenoid coils on the two cabin plates are opposite;
the mounting surface of the solenoid coil is vertical to the protected surface, and the axial direction of the solenoid coil is parallel to the protected surface and is vertical to the mounting surface; the protected surface is the surface of the spacecraft needing magnetic field shielding;
the number of turns of the solenoid coil is not less than 100000, and the current in the solenoid coil is not less than 10A.
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| CN102361797A (en) * | 2009-03-26 | 2012-02-22 | 科学技术设备委员会 | Spacecraft shield |
| CN106516162A (en) * | 2016-11-22 | 2017-03-22 | 上海卫星工程研究所 | Electromagnetic extra-static satellite platform design method |
| CN109319172A (en) * | 2018-09-28 | 2019-02-12 | 兰州空间技术物理研究所 | A kind of spacecraft is in track surface charged effect control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102361797A (en) * | 2009-03-26 | 2012-02-22 | 科学技术设备委员会 | Spacecraft shield |
| CN106516162A (en) * | 2016-11-22 | 2017-03-22 | 上海卫星工程研究所 | Electromagnetic extra-static satellite platform design method |
| CN109319172A (en) * | 2018-09-28 | 2019-02-12 | 兰州空间技术物理研究所 | A kind of spacecraft is in track surface charged effect control method |
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