基于粒子法的柔性气缸导弹弹射数值仿真

为进一步提高冷发射装备的可控性、隐蔽性、可重复性和轻量化等作战能力，对一种柔性气缸导弹弹射方式和弹射系统的工作机理进行研究。以粒子法为主要计算方法，对柔性气缸内部的气体射流进行数值计算，结合有限元方法，仿真计算柔性气缸流固耦合工作过程。通过柔性气缸导弹弹射系统实验结果与数值仿真结果的数据对比，验证数值计算方法的正确性与可靠性。改变计算参数，以某16吨导弹为研究对象，对柔性气缸导弹弹射系统的多喷口弹射与弹射工质进行规律性探索。发现柔性气缸导弹弹射系统工作过程中，导弹过载出现两次峰值且较为平滑，调整各个喷口启动时间，可使导弹的弹射动能基本不变，又可优化导弹过载。相比于高压氮气和高压空气，以超临界二氧化碳为弹射工质的柔性气缸导弹弹射系统中，导弹获取的弹射动能下降约41.1%，系统的弹射时间延长约17.1%。

Numerical Simulation of Ejecting a Missile From Missile Ejection System with Flexible Cylinder Based on Corpuscular Method

The working mechanism of a flexible cylinder ejection system and its ejection mode are studied to further improve the controllability, concealment, repeatability and lightweight of cold launch equipment. Corpuscular method is used to calculate the gas jet inside the flexible cylinder, and simulate and calculate the fluid-structure interaction of the flexible cylinder combined with finite element method. The experimental results and the numerically simulated results of the flexible cylinder ejection system are compared to verify the correctness and reliability of the numerical calculation method. For a 16-ton missile, the multi-nozzle ejection and ejection medium of the flexible cylinder ejection system were explored by changing the calculation parameters. It is found that the missile overload has two peaks and is relatively smooth during the work of the flexible cylinder ejection system. The ejection kinetic energy of the missile is basically unchanged and the missile overload is optimized by adjusting the starting time of each nozzle. In the flexible cylinder ejection system using supercritical carbon dioxide, instead of high-pressure nitrogen or high-pressure air, as the ejection medium, the ejection kinetic energy obtained by the missile is reduced by about 41.1%, and the ejection time of the system is extended by about 17.1%.