3D Spacecraft Radiation Shielding Calculation via Mesh Division
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current methods for 3D shielding simulation of spacecraft are inadequate due to issues with file format compatibility, model accuracy, mesh division, and inability to perform accurate shielding thickness analysis and dose calculations, leading to inaccurate radiation effect assessments.
Innovation Solution
A method and device for radiation effect shielding calculation based on a 3D spacecraft model, involving mesh division, shielding thickness calculation, and visualization of radiation effects, which includes reading and modifying 3D model files, setting material properties, and displaying detailed radiation distributions to evaluate irradiation effects.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If general format files (.step and .iges) are used for three-dimensional spacecraft model, then model compatibility is improved, but information accuracy deteriorates due to unit system changes and data loss
Solution Approach 1:
The patent introduces an intermediate processing system that reads general format files (.step, .iges) and converts them into a proprietary precise format. This intermediary conversion process preserves all critical information including unit systems, material properties, and component positions while maintaining compatibility with various input formats.
Solution Approach 2:
The patent performs preliminary information extraction and validation during the file import stage, before actual shielding calculations begin. This includes pre-processing steps to verify unit consistency, validate material properties, and ensure all necessary data is present, preventing information loss during subsequent processing.
2Productivity
If three-dimensional spacecraft model is simplified for calculation efficiency, then computation speed is improved, but model accuracy deteriorates and material properties cannot be properly assigned
Solution Approach 1:
The patent segments the three-dimensional spacecraft model into discrete components and elements that can be individually processed. This segmentation allows the system to maintain full geometric complexity and material property assignments while optimizing calculations by processing different components independently and in parallel where applicable.
3Ease of manufacture
If traditional mesh division is used for shielding calculation, then computational simplicity is improved, but analysis accuracy deteriorates due to low precision and inconsistent mesh sizes
Solution Approach 1:
The patent implements a dynamic mesh generation system that automatically adjusts mesh density and size based on local geometric features and radiation shielding requirements. Critical areas with complex geometries or high radiation gradients receive finer mesh resolution, while simpler areas use coarser meshes, optimizing both accuracy and computational efficiency.
4Ease of manufacture
If equivalent shielding thickness calculation is used, then calculation simplicity is improved, but three-dimensional shielding thickness analysis capability deteriorates
Solution Approach 1:
The patent transitions from equivalent one-dimensional shielding thickness calculations to full three-dimensional shielding analysis. By implementing ray-tracing algorithms that calculate actual path lengths through complex three-dimensional geometries, the system provides accurate shielding thickness values for any direction and analysis point, enabling comprehensive radiation protection assessment.
5Measurement precision
If comprehensive dose calculation is implemented, then radiation effect assessment accuracy is improved, but computational complexity increases
Solution Approach 1:
The patent replaces complex iterative mechanical calculation methods with optimized algorithms and pre-computed radiation interaction data. By using analytical solutions for radiation transport through various materials and pre-storing interaction cross-sections, the system achieves high-dose calculation accuracy while significantly reducing computational complexity and processing time.
Data Source
AI summary
A radiation effect shielding calculation method based on a three-dimensional spacecraft model is provided. The method includes obtaining the three-dimensional spacecraft model; dividing a 4π space irradiation environment into meshes to obtain space irradiation vectors corresponding to the meshes respectively; setting one or more analysis points at each target model component; inputting the space irradiation vectors to the three-dimensional spacecraft model to obtain a three-dimensional distribution of actual shielding at each analysis point; obtaining a three-dimensional distribution of an equivalent aluminum shielding thicknesses according to equivalent thickness conversion for different materials; calculating residual irradiation effect values of the three-dimensional distribution of the equivalent aluminum shielding thicknesses of each analysis point to obtain corresponding detailed irradiation data; and performing information post processing and integrating in all directions to obtain a corresponding total radiation effect value.