首页> 外文期刊>Journal of Dynamic Systems, Measurement, and Control >Damage-mitigating control of a reusable rocket engine: part I -- life prediction of the main thrust chamber wall
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Damage-mitigating control of a reusable rocket engine: part I -- life prediction of the main thrust chamber wall

机译:可重复使用的火箭发动机的减轻损害的控制:第一部分-主推力室壁的寿命预测

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The goal of damage-mitigating control in reusable rocket engines is to achieve high performance without overstraining the mechanical structures; and the major benefit is an increase in structural durability with no significant loss of performance. This sequence of papers in two parts investigates the feasibility of damage mitigating control of a reusable rocket engine similar to the Space Shuttle Main Engine (SSME). The challenge here is to characterize the thermo-mechanical behavior of thestructural materials for damage prediction in conjunction with dynamic performance analysis of the thermo-fluid process in the rocket engine, and then utilize this information in a mathematically and computationally tractable form for synthesizingdecision and control algorithms. This paper is the first part and investigates the damage phenomena in the coolant channel ligament of the main thrust chamber of a rocket engine that are characterized by progressive bulging-out and incremental thinningleading to eventual failure by tensile rupture. A creep damage model is analytically derived based on the theories of sandwich beam and viscoplasticity. The objective of this model is to generate a closed form solution of the wall thin-out in real timewhere the ligament geometry is continuously updated to account for the resulting deformation. The creep damage model has been examined for both single-cycle and multi-cycle stress-strain behavior, and the results are in agreement with those obtained fromthe finite element analyses and experimental observation. Due to its computational efficiency, this damage/life prediction model is suitable for on-line applications of decision and control, and also permits parametric studies for off-line synthesis ofdamage mitigating control systems. The second part, which is a companion paper, develops an optimal policy for damage mitigating control of the rocket engine.
机译:可重复使用的火箭发动机中减轻损害的控制的目的是在不过度增加机械结构的情况下实现高性能。主要的好处是增加了结构的耐用性,而没有明显的性能损失。该论文分为两部分,研究了类似于航天飞机主机(SSME)的可重复使用火箭发动机减轻伤害的控制的可行性。这里的挑战是结合火箭发动机中热流体过程的动态性能分析来表征结构材料的热力学行为,以进行损伤预测,然后以数学和计算上容易处理的形式利用此信息来综合决策和控制。算法。本文是第一部分,研究了火箭发动机主推力室的冷却液通道韧带中的损坏现象,这些损坏现象的特征是逐渐凸出并逐渐变薄,最终导致拉伸断裂而失效。基于夹层梁理论和粘塑性理论,分析得出了蠕变损伤模型。该模型的目的是实时生成壁薄壁的封闭形式的解决方案,其中韧带的几何形状不断更新以解决产生的变形。研究了蠕变损伤模型的单周期和多周期应力-应变行为,其结果与从有限元分析和实验观察获得的结果一致。由于其计算效率,这种损坏/寿命预测模型适用于决策和控制的在线应用,并且还允许对危害减轻控制系统的离线综合进行参数研究。第二部分是随笔,它提出了一种减轻火箭发动机的损害控制的最佳策略。

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