PRIN 2022 招标公告。2022年2月2日第104号决定

项目名称：HERMES - Hypersonic vehicles Enhancement via Robust Multi-fidelity optimization for the Exploitation of Space

CODICE CUP D53D23004350001

预算： € 86.536

U.R. 负责人 Francesco Bonelli

其他研究单位： 米兰理工大学

项目简要说明
The project is situated within the field of hypersonic flight and access to space technologies, with particular reference to atmospheric re-entry of space vehicles, reusable launchers, and suborbital vehicles. Hypersonic flight is currently a sector of great scientific and industrial interest, as it involves applications related to research, space exploration, high-speed transport, and suborbital tourism. The design of these vehicles requires tools capable of describing complex physical phenomena, such as aerothermodynamic effects and non-equilibrium thermochemistry, while also taking into account uncertainties related to operating conditions and numerical models. The project concerned the development of multifidelity methodologies for robust design and aerodynamic optimization of hypersonic vehicles. 

Particular attention was devoted to modeling thermochemical processes in neutral air and in the presence of ablated species using both State-to-State models and multi-internal-temperature models derived in a self-consistent manner from the State-to-State approach.

目的
The project aimed to develop numerical tools and robust design methodologies for hypersonic vehicles, capable of integrating models and data with different levels of accuracy and computational cost. The objective was to improve the predictive capability of simulations, including a more accurate description of thermochemical processes for neutral air in the presence of ablated species. 

A central purpose was to reduce the computational cost of the vibrationally resolved State-to-State approach through the implementation of a multi-internal-temperature approach, in which vibrational levels are grouped into sets characterized by Boltzmann distributions at different temperatures. 

预期成果
预期成果涉及制定一种多保真方法，以降低设计与优化流程的计算成本，同时保持对空气动力学性能预测的高精度。 

特别预期改进在存在烧蚀物种条件下用于中性空气的逐态化学动力学模型，并开发多内部温度模型，以在多保真框架下降低计算成本。 

已取得的成果 
该项目使得基于多保真模型与不确定性量化技术的超声速飞行器稳健设计数值方法得以开发并完善。特别是，已制定出有助于超声速飞行器空气动力学稳健优化的程序。逐态模型已得到改进，用于描述在存在烧蚀物种条件下中性空气的热化学现象，并推导出一种多内部温度模型以降低计算成本。总体而言，所开展的活动促进了更高效、更具预测性的超声速飞行器设计工具的发展，并有望降低发射成本、提升进入太空的可及性。