Speaker
Description
In the frame of the French Space Operation Act (LOS) signed on 3rd June 2008, CNES and R.Tech are particularly interested by re-entries of space debris. CNES is indeed in charge of ensuring the right application of the law, for every mission launched or operated from the French territory. To predict the debris survivability during their re-entries and assess the prospective risk on ground, the development of complete multidisciplinary tools is required.
With this in mind, CNES and R.Tech develops together their own spacecraft-oriented tool named PAMPERO since 2013. PAMPERO aims to simulate the complete atmospheric reentry of an entire satellite, launcher or the associated fragments due to the breakup process. These characteristics are the following:
- Six degrees-of-freedom flight dynamics,
- Aerodynamics and aerothermodynamics analysis : aerodynamics coefficients & parietal thermal heat fluxes computation,
- Heat transfers modeling by a 3D thermal conduction module,
- Mechanical stress analysis from the aerodynamic and thermal loads,
- Estimate of the destruction phenomena: ablation & fragmentation.
The purpose of this communication is to highlight the latest developments in the PAMPERO code, such as:
- New mesh generation strategy by merging of simple meshes
- Efficiency of the new thermal solver compared to other codes
- Comparison of the degradation model to experiments
- Coupling with the ASTER code, for mechanical stress analysis,
- Rigorous validation of each module of the code performed automatically with a comparison to analytical results, experiments and data of other simulations
Ability of PAMPERO to model complex industrial test cases easily will be presented as well as upcoming developments.
