基于多孔材料的航天器火工冲击传递机理与隔冲方法研究

As a need of stage separation and deployment of appendages in space mission, a large amount of Pyroshock devices are installed in the spacecraft. Therefore high shock transient response is generated during the separation of the release components, which tends to cause damage to the nearby micro mechanism and hardware. The purpose of this article is to provide a method based on porous material for Pyroshock response reducing and spacecraft structure optimization. At present, some Pyroshock problems have occurred in space engineering practice, which should cause the launch delay and even led to flight failures. Firstly, an equivalent and simplified modeling method of typical space Pyroshock devices is proposed to obtain the loading spectrum rapidly and accurately. Afterwards, the transfer mechanism of Pyroshock in porous medium is studied to reveal the reflection and transmission law of the stress wave. In addition, the influence of cell dimensions and porosity is discussed for parametric design for Pyroshock isolation. Finally, the design and experimental validation are implemented by numerical and experimental analysis. The research in this project will benefit developing the theoretical systems for predicting spacecraft-launcher separation shock response and shock isolation design. The research results can effectively improve the Pyroshock environment and design level of the spacecraft, which has both theoretical significance and engineering value.

航天器为了完成飞行任务中的星箭分离、级间分离、附件展开等动作，安装了大量的火工分离装置。该类装置利用炸药爆轰驱动机构运动，在分离过程中将产生高冲击瞬态响应，容易对附近的微机构和硬件造成损伤。目前，我国航天实践中已经发生众多分离冲击问题，引起了型号发射的延误，甚至导致了飞行事故。为实现火工冲击响应的有效降低与控制，本项目拟采用多孔材料进行火工冲击响应传递机理与隔离方法研究。首先开展典型航天火工冲击载荷等效方法研究，提出一种等效简化冲击载荷模型，实现快速、精确的载荷谱提取。在此基础上，进行多孔结构冲击传递机理研究，探索应力波在多孔介质中反射、透射的规律，提出一种基于多孔结构的定量隔冲设计方法。最终结合数值模拟和试验分析，完成火工冲击隔离构件设计及试验验证。相关成果有助于火工冲击隔离方法研究体系的完善，能够有效改善航天器冲击力学环境，提升飞行器设计水平，具有重要的理论意义和工程应用价值。

航天器为了完成飞行任务中的星箭分离、级间分离、附件展开等动作，安装了大量的火工分离装置。该类装置利用炸药爆轰驱动机构运动，在分离过程中将产生高冲击瞬态响应，容易对附近的微机构和硬件造成损伤。目前，我国航天实践中已经发生众多分离冲击问题，引起了型号发射的延误，甚至导致了飞行事故。为实现火工冲击响应的有效降低与控制，本项目拟采用多孔材料进行火工冲击响应传递机理与隔离方法研究。项目提出一种近-中-远场火工冲击分步建模与载荷提取方法，简化了动力学建模过程，兼顾了计算精度和计算效率。建立了基于变截面杆理论、周期结构带隙理论的航天器冲击隔离定量设计方法，揭示了多孔周期结构冲击隔离机理。创新引入多孔材料，利用其结构非连续性，引发冲击应力波传递过程中的多次反射与耗散，实现火工冲击的有效隔离与抑制。本项目涉及的过渡段、缓冲孔结构已应用于合作单位；冲击隔离性能更优秀的周期结构梁、蜂窝隔振接口等结构具有良好的应用前景。数据有效性方法已经开发GUI界面软件，提供给相关应用单位使用。相关成果有助于火工冲击隔离方法研究体系的完善，能够有效改善航天器冲击力学环境，提升飞行器设计水平，具有重要的理论意义和工程应用价值。