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概率损害建模和热冲击风险评估UHTCMC推进器在过渡绿色推进操作下
Prakhar Jindal1, Tamim Doozandeh1, Jyoti Botchu1
1Space System Engineering Section, Space Engineering, Faculty of Aerospace Engineering, TU Delft, Kluyverweg 1, 2629 HS Delft, The Netherlands.
Materials (Basel, Switzerland)
|August 14, 2025
概括
本研究为可重复使用的陶复合推进器建模了损坏和疲劳风险. 它使用模拟来评估热冲击和应力,为更安全的绿色推进系统设计开发新的风险指数.
科学领域:
- 材料科学 材料科学 材料科学
- 航空航天工程 航空航天工程
- 计算力学 计算力学 计算力学
背景情况:
- 可重复使用的火箭发动机组件面临极端条件.
- 陶矩阵复合材料提供高温耐受性,但需要进行彻底的疲劳评估.
- 绿色双推进系统需要可靠的,持久的推进器设计.
研究的目的:
- 为可重复使用的陶矩阵复合推进器开发基于模拟的损坏建模和疲劳风险评估框架.
- 为了评估热冲击和短时间燃烧期间压力积累的影响.
- 建立一个保守的,基于物理的组件设计风险估计方法.
主要方法:
- 在经过验证的推进器几何学上进行时间解析的热和结构模拟.
- 开发一个模拟衍生的应力边缘包裹方法,以考虑材料强度的变化.
- 导出一个规范化风险指数来量化在10秒发射窗口内损坏的可能性.
主要成果:
- 在收的喉区域,峰值热梯度率为~380 K/s.
- 在关键区域,正常化热冲击指数超过43.
- 在没有主动冷却的情况下,在模拟条件下,应力边缘在喉中崩2.3秒,在侧翼曲率中接近8秒.
结论:
- 开发的框架为评估陶推进喷嘴安全性提供了一种透明和可重复的方法.
- 确定了在热和机械负荷下潜在损害启动的关键区域和时间框架.
- 该方法支持为下一代绿色空间发动机设计耐疲劳元件.
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