CN111581719B - Radiation effect calculation method, device and equipment based on spacecraft three-dimensional shielding - Google Patents
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Abstract
The invention relates to a radiation effect calculation method, a radiation effect calculation device and radiation effect calculation equipment based on three-dimensional shielding of a spacecraft, which are applied to the technical field of aerospace, wherein the method comprises the following steps: acquiring a three-dimensional model of the spacecraft; determining a ray vector emitted by taking a target device as a center in the three-dimensional model according to a preset resolution; calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model; determining the radiation effect value of each ray vector according to the total equivalent aluminum shielding thickness and a preset effect depth curve; and obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a radiation effect calculation method, device and equipment based on three-dimensional shielding of a spacecraft.
Background
With the importance of aerospace in China, more and more spacecrafts enter space. There are meteorological conditions on earth and space conditions. According to incomplete statistics, 40% of spacecraft faults are caused by space environment, some can even reach 80%, and faults caused by radiation environment are dominant. The radiation environment mainly has three sources including a Galaxy cosmic ray, a solar cosmic ray and an earth radiation band, and high-energy particles generated by the Galaxy cosmic ray, the solar cosmic ray and the earth radiation band penetrate through the spacecraft skin to enter the position of a single device, so that effects such as radiation dose, single event upset, displacement damage, deep charge and discharge and the like can be generated, and the spacecraft is caused to malfunction. Therefore, protection of the spacecraft is of paramount importance.
In order to reduce the failure occurrence rate of the spacecraft, the irradiation resistance condition of the spacecraft can be analyzed and calculated in the development process of the spacecraft, and the improvement of the spacecraft can be guided according to the calculation result.
However, in the related art, the software for performing radiation effect evaluation is based on a simple shielding model, for example, shielding around the component is equivalent to a uniform spherical shell, a simple flat plate and the like, so that the actual shielding around the component cannot be actually represented, the total radiation dose encountered is overestimated, and because the spacecraft has a complex structure, larger errors can be generated by performing calculation according to the simple shielding model.
Disclosure of Invention
In view of the above, the present invention provides a method, apparatus and device for calculating radiation effect based on three-dimensional shielding of spacecraft, in order to overcome the problems in the related art to at least a certain extent.
In order to solve the technical problems, the invention adopts the following technical scheme:
in a first aspect, a radiation effect calculation method based on three-dimensional shielding thickness of a spacecraft includes:
acquiring a three-dimensional model of the spacecraft;
determining a ray vector emitted by taking a target device as a center in the three-dimensional model according to a preset resolution;
calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model;
determining the radiation effect value of each ray vector according to the total equivalent aluminum shielding thickness and a preset effect depth curve;
and obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector.
Optionally, the acquiring the three-dimensional model of the spacecraft includes:
acquiring a three-dimensional model file of the spacecraft based on OCC;
extracting information in the three-dimensional model file;
converting the extracted three-dimensional model information to obtain identifiable three-dimensional data;
optionally, the method further comprises: and classifying and storing the three-dimensional data.
Optionally, the determining, according to a preset resolution, a ray vector emitted by the three-dimensional model centering on the target device includes:
acquiring the preset resolution;
determining the number of rays according to the preset resolution;
dividing the three-dimensional model based on a mesh algorithm to obtain a plurality of regular triangle distribution arrays;
and taking the target device as a starting point, and taking the vertex of the regular triangle as a point through which the ray passes to obtain a plurality of ray vectors.
Optionally, the determining the radiation effect value of each ray vector according to the total equivalent aluminum shielding thickness and a preset effect depth curve includes:
acquiring a preset effect depth curve;
and comparing the total equivalent aluminum shielding thickness of each ray vector with the effect depth curve to obtain a radiation effect value corresponding to the total equivalent aluminum shielding thickness.
Optionally, the calculating the equivalent aluminum shielding thickness on each ray based on the shielding analysis entity intersection method and the material density of the shielding part in the three-dimensional model includes:
performing entity intersection calculation on the shielding part in the three-dimensional model and the ray vector to obtain the three-dimensional shielding thickness of the shielding part;
obtaining the equivalent aluminum shielding thickness of each shielding part according to the three-dimensional shielding thickness of the shielding part and the material density of the shielding part;
and obtaining the total equivalent aluminum shielding thickness of the ray vector according to the equivalent aluminum shielding thickness of each shielding part on the same ray vector.
Optionally, before the calculating the physical intersection between the shielding part and the ray vector in the three-dimensional model, the method further includes:
filtering the three-dimensional model to determine the shielding parts participating in the calculation.
Optionally, the method further comprises:
and displaying the total equivalent aluminum shielding thickness on each ray vector in the form of a color temperature chart, and calculating the percentage of the equivalent aluminum shielding thickness of each shielding part on the same ray vector.
In a second aspect, a radiation effect calculation device based on three-dimensional shielding thickness of a spacecraft, includes:
the acquisition module is used for acquiring a three-dimensional model of the spacecraft;
the first determining module is used for determining a ray vector which is emitted by taking the target device as the center in the three-dimensional model according to the preset resolution;
the calculation module is used for calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model;
the second determining module is used for determining radiation effect values of the ray vectors according to the total equivalent aluminum shielding thickness and a preset effect depth curve;
and the radiation effect calculation module is used for obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector.
In a third aspect, a radiation effect computing device based on three-dimensional shielding of a spacecraft, comprising:
a processor, and a memory coupled to the processor;
the memory is used for storing a computer program;
the processor is configured to invoke and execute the computer program in the memory to perform the radiation effect calculation method based on spacecraft three-dimensional shielding as described in the first aspect.
In a fourth aspect, a storage medium stores a computer program, which when executed by a processor, implements a radiation effect calculation method based on three-dimensional shielding of a spacecraft according to any of the first aspects of the invention.
The invention adopts the technical scheme, and can realize the following technical effects: firstly, acquiring a three-dimensional model of a spacecraft; determining a ray vector emitted by taking a target device as a center in the three-dimensional model according to a preset resolution; calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model; determining the radiation effect value of each ray vector according to the total equivalent aluminum shielding thickness and a preset effect depth curve; and obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector. Therefore, the total equivalent aluminum shielding thickness of the device in each ray direction can be obtained by directly calculating the three-dimensional model of the spacecraft, and a user can further obtain radiation effect data borne by the spacecraft.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a radiation effect calculation method based on three-dimensional shielding of a spacecraft according to an embodiment of the invention;
FIG. 2 is a schematic flow chart of a radiation effect calculation method based on three-dimensional shielding of a spacecraft according to another embodiment of the invention;
FIG. 3 is a schematic flow chart of a radiation effect calculation method based on three-dimensional shielding of a spacecraft according to another embodiment of the invention;
FIG. 4 is a schematic structural diagram of a radiation effect calculation device based on three-dimensional shielding of a spacecraft according to an embodiment of the invention;
fig. 5 is a schematic structural diagram of a radiation effect computing device based on three-dimensional shielding of a spacecraft according to an embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, based on the examples herein, which are within the scope of the invention as defined by the claims, will be within the scope of the invention as defined by the claims.
For a better understanding of the solution provided in this application, it is necessary to understand the following:
with the importance of aerospace in China, more and more spacecrafts enter space. There are meteorological conditions on earth and space conditions. According to incomplete statistics, 40% of spacecraft faults are caused by space environment, some can even reach 80%, and faults caused by radiation environment are dominant. The radiation environment mainly has three sources including a Galaxy cosmic ray, a solar cosmic ray and an earth radiation band, and high-energy particles generated by the Galaxy cosmic ray, the solar cosmic ray and the earth radiation band penetrate through the spacecraft skin to enter the position of a single device, so that effects such as radiation dose, single event upset, displacement damage, deep charge and discharge and the like can be generated, and the spacecraft is caused to malfunction. Therefore, protection of the spacecraft is of paramount importance.
In order to reduce the failure occurrence rate of the spacecraft, the irradiation resistance condition of the spacecraft can be analyzed and calculated in the development process of the spacecraft, and the improvement of the spacecraft can be guided according to the calculation result. And in the running process of the spacecraft, the service life of the spacecraft can be estimated according to the measured particle radiation data. However, the current general radiation effect evaluation software is based on a simple shielding model, such as equivalent shielding around the components to be uniform spherical shell, simple flat plate and the like, so that the actual shielding around the components cannot be actually represented, the situation often ignores the mutual shielding effect among different components in the spacecraft, overestimates the total radiation dose encountered, and the corresponding shielding design belongs to over-design. Because the spacecraft has a complex structure, calculation according to a simple shielding model tends to bring about no small error.
The three-dimensional shielding analysis considers the shielding contribution of a more real spacecraft structure, can acquire shielding thicknesses in any position in the spacecraft in different directions, and further acquires an accurate and reliable total radiation dose result by combining space environment information; meanwhile, the radiation effect value can be reduced by reasonably arranging the positions of the equipment and utilizing the mutual shielding function of the equipment, so that the shielding resources of the spacecraft and the key shielding resources of a single machine are fully utilized, and the shielding effect with optimal cost performance is achieved. There are several software on the market that calculate the effect of spatial radiation, such as spacedradition, micro-field and SSAT. Space Radiation can only be calculated according to a simple mask model; micro shield can perform three-dimensional mask calculation, but can only be set according to a predetermined model shape inside software; SSAT can perform three-dimensional shielding analysis, but the most prominent problem is that an abnormal complex spacecraft structure model needs to be converted into a geometric description model which can be identified by SSAT software, a user often needs to manually carry out a great deal of complicated modeling work, and the accuracy and reliability of the SSAT are difficult to guarantee. The invention provides a three-dimensional shielding analysis radiation effect calculation method capable of importing STp/igs format in combination with the current use situation of tools of ProE, UG and the like of spacecraft overall design departments in China, overcomes the defect of geometric modeling surface of SSAT tools, ensures that the analysis and evaluation of the radiation effect are quicker, more accurate and reliable, and meets the current situation and the requirement of special aerospace engineering in China.
Examples
Fig. 1 is a schematic flow chart of a radiation effect calculation method based on three-dimensional shielding of a spacecraft according to an embodiment of the invention. As shown in fig. 1, the present embodiment provides a radiation effect calculation method based on three-dimensional shielding of a spacecraft, including:
step 101, acquiring a three-dimensional model of a spacecraft;
in some embodiments, the three-dimensional model file of the spacecraft may be drawn for main stream three-dimensional software such as CATIA, UG, pro/E, and after the main stream three-dimensional software is obtained, the main stream three-dimensional software is read and converted through OCC (Open CASCADE), so as to obtain an identifiable three-dimensional model. Wherein OCC is a C++ class library based on OO concept, and is used for open source program of design application program of precision equipment and the like
102, determining a ray vector emitted by taking a target device as a center in the three-dimensional model according to a preset resolution;
in some embodiments, the resolution determines the fineness of the computation mask, the ray is emitted by using the principle of linear approximation of mask analysis with the target device as the center, the resolution is higher as the number of rays is larger, the user can choose to set different resolutions, and the resolution is inversely proportional to the computation speed.
Step 103, calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model;
in some embodiments, the physical intersection method mainly uses a calculation function provided by three-dimensional design software such as proE, etc., to emit rays outwards from a point of interest, and calculates the intersection length of a part model and a ray vector, i.e. the thickness of a shielding layer of the part with respect to the direction of the ray vector.
104, determining radiation effect values of the ray vectors according to the total equivalent aluminum shielding thickness and a preset effect depth curve;
it will be appreciated that the effect depth profile can be obtained from prior art related data.
And 105, obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector.
In the embodiment, a three-dimensional model of a spacecraft is acquired first; calculating the shielding thickness of each ray vector of the three-dimensional model according to a linear transmission method, wherein the rays are obtained by carrying out finite element subdivision on the three-dimensional model according to a mesh algorithm based on a preset resolution; calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model; determining the radiation effect value of each ray vector according to the total equivalent aluminum shielding thickness and a preset effect depth curve; and obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector. Therefore, the total equivalent aluminum shielding thickness on each ray vector of the device can be obtained by directly calculating the three-dimensional model of the spacecraft, and a user can further obtain radiation effect data borne by the spacecraft.
Fig. 2 is a schematic flow chart of a radiation effect calculation method based on three-dimensional shielding of a spacecraft according to another embodiment of the invention. As shown in fig. 2, the present embodiment provides a radiation effect calculation method based on three-dimensional shielding of a spacecraft, including:
step 201, acquiring a three-dimensional model file of the spacecraft based on OCC;
in some embodiments, the three-dimensional model files may be imported by mainstream three-dimensional software such as CATIA, UG, pro/E, or format files such as IGES (igs/. IGES) and STEP 203 (stp/. STEP) may be generated.
Step 202, extracting information in the three-dimensional model file;
step 203, converting the extracted three-dimensional model information to obtain identifiable three-dimensional data;
specifically, the data exchange module of Open CASCADE can realize the function of reading neutral files such as IGES and STEP, and has good collaborative capability. The STEP and IGES file formats are formulated by the international standardization organization, and are the data file formats with better CAD/CAM compatible effects in most of the current, and main stream three-dimensional software such as CATIA, UG, pro/E can import and generate IGES (igs/. IGES) and STEP 203 (stp/. STEP) files. The data exchange module of the Open CASCADE comprises a plurality of related functions, can read data information stored in the model data file, and can convert the data information into a data structure which can be identified by the Open CASCADE and store the data structure in the object memory. Operating the model in the graphics device environment requires reading data from the object memory and processing the data. Taking the STEP format file as an example, the opencascades defines an array class Handle (Top Tools HSequence Of Shape),
and 204, storing the three-dimensional data in a classified mode.
In some embodiments, the three-dimensional model data after conversion may be stored in the class, including information such as color, size, rendering, and the like. When reading data, the model data is acquired by for-loop traversing the array of handles- (toptools_ HSequence Of Shape), thereby displaying the model in the graphics device environment.
Step 205, determining a ray vector emitted by taking a target device as a center in the three-dimensional model according to a preset resolution;
the resolution determines the fine degree of calculation shielding, rays are emitted by using a shielding analysis straight line approximation principle as a center by using an analyzed device, the resolution is higher as the number of rays is larger, a user can select different resolutions, and the resolution is inversely proportional to the calculation speed.
Wherein, the ray can be obtained by the following steps:
step 301, obtaining the preset resolution;
in some embodiments, the preset resolution may be set by the user according to the actual situation. It will be appreciated that the resolution determines how fine the computational mask is, and that the resolution is inversely proportional to the computational speed, using the principle of linear approximation of the mask analysis, with the device being analyzed being centered to emit radiation, the greater the number of radiation rays, the higher the resolution, the more resolution the user can choose to set.
Step 302, determining the number of rays according to the preset resolution;
based on the related embodiment, after the preset resolution is determined, the number of rays is also determined.
Step 303, dividing the three-dimensional model based on a mesh algorithm to obtain a plurality of regular triangle distribution arrays;
in some embodiments, the mesh algorithm is a commonly used three-dimensional finite element analysis algorithm. Specifically, the regular octahedron is utilized to divide the three-dimensional sphere (the three-dimensional model is considered to be in one three-dimensional sphere) uniformly, so that a regular triangle star distribution array with uniform and equal size is formed on the spherical surface.
And 304, taking the vertex of the regular triangle as a ray starting point to obtain a plurality of rays.
Based on the above embodiment, the vertices of each triangle form a ray. The dividing method can strictly ensure the uniform distribution of the solid angles and ensure that the calculation result of each time can be reproduced.
Step 206, filtering the three-dimensional model to determine shielding parts participating in calculation.
In some embodiments, in the model preprocessing, a certain filtering means is used to specify which elements participate in the shielding analysis and calculation, so that small pieces such as fasteners, pins and the like can be filtered, and the resolving speed is improved.
Step 207, obtaining an equivalent aluminum shielding thickness of each shielding part according to the shielding thickness of the shielding part and the material density of the shielding part;
in some embodiments, the shielding thickness of the shielding part may be multiplied by the material density of the shielding part to obtain an equivalent aluminum shielding thickness of each shielding part.
Wherein, material equivalent aluminum shielding thickness= (material density/aluminum density) ×material thickness.
Step 208, obtaining the total equivalent aluminum shielding thickness of the ray vector according to the equivalent aluminum shielding thickness of each shielding part on the same ray vector.
In some embodiments, calculating the total shield thickness in a certain direction uses the principle of shield analysis straight line approximation. The ESA standard ECSS-E-10-12 indicates that the shield thickness calculation through which the radiation is transmitted in the material is largely two methods, normal transmission (NORM) and straight line transmission (SLANT). The normal transmission calculation shielding thickness considers the transmission distance of rays in the direction perpendicular to the surface of shielding materials, while the linear transmission can be obliquely intersected with any material surface, and the actual shielding thickness can be overestimated for the normal transmission of complex shielding structures. The three-dimensional shielding and radiation dose evaluation method of the spacecraft based on the ProE adopts a linear approximate transmission principle, namely, the thickness of a substance on a straight line along the direction is used as the thickness of the shielding for calculating the thickness of the shielding in the specific direction inside the spacecraft. Therefore, in this embodiment, the equivalent aluminum shielding thicknesses of the shielding parts of the same ray vector may be added to obtain the total equivalent aluminum shielding thickness on the ray vector.
Step 209, displaying the total equivalent aluminum shielding thickness on each ray vector in the form of a color temperature chart, and calculating the percentage of the equivalent aluminum shielding thickness of each shielding part on the same ray vector.
In some embodiments, the total equivalent aluminum shielding thickness on each ray vector is displayed in the form of a color temperature chart, so that a user can more clearly know the shielding thickness in the spacecraft.
Step 210, obtaining a preset effect depth curve;
in some embodiments, the effect depth profile may be obtained from prior art related data.
Step 211, comparing the shielding thickness of each ray vector with the effect depth curve to obtain a radiation effect value corresponding to the shielding thickness.
And 212, obtaining the radiation effect of each ray vector of the spacecraft according to the total equivalent aluminum shielding thickness and the radiation effect value.
In some embodiments, effect data such as effects of radiation dose, single event upset, displacement damage, deep charge and discharge, etc. may be calculated by effect calculation methods in the prior art.
Fig. 4 is a schematic structural diagram of a radiation effect calculating device based on three-dimensional shielding of a spacecraft according to an embodiment of the invention. Referring to fig. 4, an embodiment of the present application provides a radiation effect calculating device based on three-dimensional shielding of a spacecraft, including:
an acquisition module 401, configured to acquire a three-dimensional model of a spacecraft;
a first determining module 402, configured to determine a vector of rays emitted in the three-dimensional model centered on the target device according to a preset resolution;
a calculation module 403, configured to calculate a total equivalent aluminum shielding thickness of each of the ray vectors based on a shielding analysis entity intersection method and a material density of a shielding part in the three-dimensional model;
a second determining module 404, configured to determine a radiation effect value of each of the ray vectors according to the total equivalent aluminum shielding thickness and a preset effect depth curve;
and the radiation effect calculation module 405 is configured to obtain a radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector.
The specific implementation scheme of this embodiment may refer to the radiation effect calculation method based on three-dimensional shielding of a spacecraft and the related description in the method embodiment described in the foregoing embodiment, which are not repeated herein.
Fig. 5 is a schematic structural diagram of a radiation effect computing device based on three-dimensional shielding of a spacecraft according to an embodiment of the invention. Referring to fig. 5, an embodiment of the present application provides a radiation effect computing device based on three-dimensional shielding of a spacecraft, including:
a processor 501 and a memory 502 coupled to the processor;
the memory is used for storing a computer program;
the processor is configured to invoke and execute the computer program in the memory to perform the radiation effect calculation method based on the spacecraft three-dimensional mask as in the above embodiments.
The specific implementation scheme of this embodiment may refer to the radiation effect calculation method based on three-dimensional shielding of a spacecraft and the related description in the method embodiment described in the foregoing embodiment, which are not repeated herein.
The embodiment of the invention provides a storage medium which stores a computer program, and when the computer program is executed by a processor, the method realizes each step in a radiation effect calculation method based on three-dimensional shielding of a spacecraft.
The specific implementation scheme of this embodiment may be referred to the description related to the foregoing embodiment of the radiation effect calculation method based on three-dimensional shielding of a spacecraft, which is not described herein.
It is to be understood that the same or similar parts in the above embodiments may be referred to each other, and that in some embodiments, the same or similar parts in other embodiments may be referred to.
It should be noted that in the description of the present invention, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Furthermore, in the description of the present invention, unless otherwise indicated, the meaning of "plurality" means at least two.
Any process or method descriptions in flow charts or otherwise described herein may be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing specific logical functions or steps of the process, and further implementations are included within the scope of the preferred embodiment of the present invention in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the present invention.
Those of ordinary skill in the art will appreciate that all or a portion of the steps carried out in the method of the above-described embodiments may be implemented by a program to instruct related hardware, where the program may be stored in a computer readable storage medium, and where the program, when executed, includes one or a combination of the steps of the method embodiments.
In addition, each functional unit in the embodiments of the present invention may be integrated in one processing module, or each unit may exist alone physically, or two or more units may be integrated in one module. The integrated modules may be implemented in hardware or in software functional modules. The integrated modules may also be stored in a computer readable storage medium if implemented in the form of software functional modules and sold or used as a stand-alone product.
The above-mentioned storage medium may be a read-only memory, a magnetic disk or an optical disk, or the like.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.
Claims (8)
1. The radiation effect calculation method based on the spacecraft three-dimensional shielding is characterized by comprising the following steps of:
acquiring a three-dimensional model of the spacecraft;
determining a ray vector emitted by taking a target device as a center in the three-dimensional model according to a preset resolution;
calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model;
determining the radiation effect value of each ray vector according to the total equivalent aluminum shielding thickness and a preset effect depth curve;
obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector;
the calculating the equivalent aluminum shielding thickness of each ray vector based on the shielding analysis entity intersection method and the material density of the shielding part in the three-dimensional model comprises the following steps:
performing entity intersection calculation on the shielding part in the three-dimensional model and the ray vector to obtain the shielding thickness of the shielding part;
obtaining the equivalent aluminum shielding thickness of each shielding part according to the shielding thickness of the shielding part and the material density of the shielding part;
wherein, equivalent aluminum shielding thickness of shielding part= (material density/aluminum density of shielding part) ×shielding thickness of shielding part;
obtaining the total equivalent aluminum shielding thickness of the ray vector according to the equivalent aluminum shielding thickness of each shielding part on the same ray vector;
adding the equivalent aluminum shielding thicknesses of the shielding parts of the same ray vector by adopting a linear approximate transmission principle to obtain the total equivalent aluminum shielding thickness on the ray vector;
the determining the ray vector emitted by the three-dimensional model with the target device as the center according to the preset resolution comprises the following steps:
acquiring the preset resolution;
determining the number of rays according to the preset resolution;
dividing the three-dimensional model based on a mesh algorithm to obtain a plurality of regular triangle distribution arrays;
and taking the target device as a starting point, and taking the vertex of the regular triangle as a point through which the ray passes to obtain a plurality of ray vectors.
2. The method for calculating radiation effect based on three-dimensional shielding of a spacecraft according to claim 1, wherein said obtaining a three-dimensional model of a spacecraft comprises:
acquiring a three-dimensional model file of the spacecraft based on OCC;
extracting information in the three-dimensional model file;
and converting the extracted three-dimensional model information to obtain identifiable three-dimensional data.
3. The radiation effect calculation method based on three-dimensional shielding of a spacecraft according to claim 2, further comprising: and classifying and storing the three-dimensional data.
4. The method for calculating radiation effect based on three-dimensional shielding of spacecraft according to claim 1, wherein said determining radiation effect value of each of said ray vectors according to said total equivalent aluminum shielding thickness and a preset effect depth curve comprises:
acquiring a preset effect depth curve;
and comparing the total equivalent aluminum shielding thickness of each ray vector with the effect depth curve to obtain a radiation effect value corresponding to the total equivalent aluminum shielding thickness.
5. The method for calculating radiation effect based on three-dimensional shielding of spacecraft according to claim 1, wherein before the step of physically intersecting the shielding part in the three-dimensional model with the ray vector, the method further comprises:
filtering the three-dimensional model to determine the shielding parts participating in the calculation.
6. The radiation effect calculation method based on three-dimensional shielding of a spacecraft according to claim 1, further comprising:
and displaying the total equivalent aluminum shielding thickness on each ray vector in the form of a color temperature chart, and calculating the percentage of the equivalent aluminum shielding thickness of each shielding part on the same ray vector.
7. A radiation effect calculation device based on three-dimensional shielding of a spacecraft, comprising:
the acquisition module is used for acquiring a three-dimensional model of the spacecraft;
the first determining module is used for determining a ray vector which is emitted by taking the target device as the center in the three-dimensional model according to the preset resolution;
the calculation module is used for calculating the total equivalent aluminum shielding thickness of each ray vector based on a shielding analysis entity intersection method and the material density of shielding parts in the three-dimensional model;
the second determining module is used for determining radiation effect values of the ray vectors according to the total equivalent aluminum shielding thickness and a preset effect depth curve;
the radiation effect calculation module is used for obtaining the radiation effect of each ray vector of the spacecraft target device according to the radiation effect value of each ray vector;
the calculation module calculates a total equivalent aluminum shielding thickness of each of the ray vectors based on a shielding analysis entity intersection method and a material density of a shielding part in the three-dimensional model, comprising:
performing entity intersection calculation on the shielding part in the three-dimensional model and the ray vector to obtain the shielding thickness of the shielding part;
obtaining the equivalent aluminum shielding thickness of each shielding part according to the shielding thickness of the shielding part and the material density of the shielding part;
wherein, equivalent aluminum shielding thickness of shielding part= (material density/aluminum density of shielding part) ×shielding thickness of shielding part;
obtaining the total equivalent aluminum shielding thickness of the ray vector according to the equivalent aluminum shielding thickness of each shielding part on the same ray vector;
adding the equivalent aluminum shielding thicknesses of the shielding parts of the same ray vector by adopting a linear approximate transmission principle to obtain the total equivalent aluminum shielding thickness on the ray vector;
the first determining module is further configured to obtain the preset resolution;
determining the number of rays according to the preset resolution;
dividing the three-dimensional model based on a mesh algorithm to obtain a plurality of regular triangle distribution arrays;
and taking the target device as a starting point, and taking the vertex of the regular triangle as a point through which the ray passes to obtain a plurality of ray vectors.
8. A radiation effect computing device based on spacecraft three-dimensional shielding, comprising:
a processor, and a memory coupled to the processor;
the memory is used for storing a computer program;
the processor is configured to invoke and execute the computer program in the memory to perform the spacecraft three-dimensional shielding based radiation effect calculation method of any of claims 1-6.
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| CN103149581A (en) * | 2013-01-23 | 2013-06-12 | 哈尔滨工业大学 | Computing method of displacement absorbed doses of space three-dimensional structure device |
| CN106295051A (en) * | 2016-08-19 | 2017-01-04 | 中国空间技术研究院 | A kind of three dimensional analysis method of telecommunication satellite radiation dose |
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| CN103149581A (en) * | 2013-01-23 | 2013-06-12 | 哈尔滨工业大学 | Computing method of displacement absorbed doses of space three-dimensional structure device |
| CN106295051A (en) * | 2016-08-19 | 2017-01-04 | 中国空间技术研究院 | A kind of three dimensional analysis method of telecommunication satellite radiation dose |
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