Multi-scale method for high-temperature structure ablation prediction of hypersonic vehicles
US12216974B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 31, 2023 |
| Grant date | Feb 4, 2025 |
| Priority date | — |
| Expiry date | May 31, 2043 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T90/00
- WIPO fieldComputer technology
- WIPO sectorElectrical engineering
Abstract
A multi-scale prediction method for an ablation behavior of a hypersonic aircraft heat resistant structure, includes inputting hypersonic inflow far field boundary conditions into a macro CFD solver to perform numerical simulation of the external flow field of a hypersonic aircraft; extracting the mass fraction and temperature distribution of wall surface components; obtaining an msd.txt file and an atomic path file recording the mean square displacement data through a micro RMD solver; obtaining the ratio of mass loss rate to material density, namely, the ablation retreating rate using the MSD method and Fick's law; inputting it into a CFD solver for performing grid reconstruction and transient calculation to obtain the transient variation in the external flow field of a hypersonic aircraft along the ablation retreating of the aircraft wall surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.