For hypersonic maneuvering flight in near space, because of the limited aerodynamic lift provided by the low-density air, lightweight of the structure of vehicles is more demanded, in the meanwhile, the severe thermal/mechanical environments, such as oxidation environment, high dynamic pressure and high hypersonic aerodynamic heating, bring a strong challenge for thermal protection system for vehicles. In order to increase improve the efficiency and reliability of structures, it is needed to development the method of design and evaluation based on integration of "materials/structures" and "thermal protection/insulation", and realize the objects of optimization of the vehicle structures. This application is the continuity of the “integrated project” of “Research on the material/structure integration and thermal protection/insulation integration of near space hypersonic vehicle”. This project will mainly solve some key problems such as the multi-physical analysis theory and methods in thermal/mechanics/oxidation coupling environment, and reliability simulation strategy and methods based on the uncertainty. They are the complementarity and extension of the original project. it’s expected to realize the integration, sublimation and innovation by this project, and providing an base for realize the great-leap-forward development of thermal protection materials and structures for near space hypersonic vehicle.
近空间高超声速机动飞行,由于低密度空气提供气动升力有限对飞行器结构轻质化提出了苛刻的要求,大气层内有氧环境、高动压与高超声速气动热/力耦合等因素对飞行器热防护技术提出了严峻的挑战。为提高结构效率和可靠性,必须实现材料/结构一体化、防/隔热一体化设计和评价,以达到飞行器结构的匹配和最优化的目的。本项目是“近空间高超声速飞行器材料/结构一体化、防/隔热一体化研究”集成项目的延续资助申请,重点解决热/力/氧耦合作用下的多物理场耦合分析理论和方法以及考虑不确定的模拟策略和方法。是对原研究内容的丰富与深化,以期更好地实现集成升华、创新的目标,为我国近空间高超声速飞行器轻质结构与热防护技术的跨越式发展奠定基础。
近空间高超声速机动飞行,由于低密度空气提供气动升力有限对飞行器结构轻质化提出了苛刻的要求,大气层内有氧环境、高动压与高超声速气动热/力耦合等因素对飞行器热防护技术提出了严峻的挑战。为提高结构效率和可靠性,必须实现材料/结构一体化、防/隔热一体化设计和评价,以达到飞行器结构的匹配和最优化的目的。本项目是“近空间高超声速飞行器材料/结构一体化、防/隔热一体化研究”集成项目的延续资助申请,重点解决了热/力/氧耦合作用下的多物理场耦合分析理论和方法以及考虑不确定的模拟策略和方法。是对原研究内容的丰富与深化,研究成果为我国近空间高超声速飞行器轻质结构与热防护技术的跨越式发展奠定了基础。
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数据更新时间:2023-05-31
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