强冲击环境下航天器典型结构中多模式组合波传播规律研究

As the rapid increase of the space projects and the flight missions, the flight failures caused by severe pyro-shock environment occurs frequently in recent years. The flight accidents endanger the economic, national defense and people’s lives, so the reliability of the space equipment under pyro-shock environment receives extensive attention. Now the assessment of the shock environment receives extensive attention. Now the assessment of the shock environment adaptability of the space equipment mainly relies on large amount of ‘trial and error’ shock tests, because we lack the knowledge of the dynamic response characteristics of the equipment. As a result, the test assessment has great uncertainty, and result in many problems such as high development costs and massive dependence on imported electronic components. In order to reduce the development costs and time, and at the same time to ensure high reliability, the accurate prediction of the severe pyro-shock environment and the dynamics response caused by this environment in the spacecraft structure should be investigated as soon as possible. This project aims to combine the method of theoretical analysis, numerical simulation, and experiment verification together to systematically investigate the propagation law of the multi-mode stress waves caused by the pyro-shock environment in typical spacecraft structures. Then the dynamic response of the structure is analyzed through considering the behavior of waves, based on which an accurate prediction method is developed. This project can provide important theoretical foundations for the adaptability design of space equipment, and has great significance on theoretical research and engineering application.

随着航天型号谱系的快速发展和发射密度的逐年提高，分离火工品爆炸引起的强冲击环境导致的航天器飞行事故频发，危及经济、国防和人民生命安全，航天设备冲击环境适应性受到广泛关注。目前航天设备依靠大量“试错”式地面冲击试验进行飞行前环境考核，由于缺乏对航天设备冲击动力学响应规律的深刻认识，试验考核具有很大的不确定性，衍生出研制成本高、严重依赖进口元器件等诸多问题。为降低产品研制成本、缩短研制周期，同时确保航天器高可靠性，需要尽快开展航天器典型结构中冲击动力学响应规律及冲击环境精确预示方法的研究。本项目拟结合理论分析、数值仿真和试验验证的方法，系统研究强冲击环境下航天器典型结构中多模式复合应力波的传播规律，从波传播的角度给出航天器典型结构冲击动力学响应规律的解释，获得适用于工程实践的冲击环境预示方法，指导航天设备的冲击环境适应性设计，具有重要的理论价值和广阔的应用前景。

随着航天型号谱系的快速发展和发射密度的逐年提高，分离火工品爆炸引起的强冲击环境导致的航天器飞行事故频发，危及经济、国防和人民生命安全，航天设备冲击环境适应性受到广泛关注。目前航天设备依靠大量“试错”式地面冲击试验进行飞行前环境考核，由于缺乏对航天设备冲击动力学响应规律的深刻认识，试验考核具有很大的不确定性，衍生出研制成本高、严重依赖进口元器件等诸多问题。为降低产品研制成本、缩短研制周期，同时确保航天器高可靠性，需要尽快开展航天器典型结构中冲击动力学响应规律及冲击环境精确预示方法的研究。本项目拟结合理论分析、数值仿真和试验验证的方法，系统研究强冲击环境下航天器典型结构中多模式复合应力波的传播规律，从波传播的角度给出航天器典型结构冲击动力学响应规律的解释，获得适用于工程实践的冲击环境预示方法，指导航天设备的冲击环境适应性设计，具有重要的理论价值和广阔的应用前景。