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首页> 外文期刊>Journal of aerospace engineering >Numerical Experiment of Aeroelastic Stability for a Rocket Nozzle
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Numerical Experiment of Aeroelastic Stability for a Rocket Nozzle

机译：火箭喷嘴气动弹性稳定性的数值实验

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The development of new rocket engine nozzles for launch vehicles encounters a challenging design problem: to meet nozzle performance for high altitude, the nozzle expansion ratios are designed by high value; however, these would lead to overexpanded flow conditions at ground. These conditions in turn generate unsteady internal flow separation. The resulting asymmetries result in side loads, which can potentially damage not only the nozzle but also the entire launch system. The occurrence of excessive side loads in nozzles is one of the most important issues to consider in designing efficient, reusable, and robust launch vehicles. In this work, a fully coupled method using Navier-Stokes simulations is used to numerically investigate the aeroelastic stability for the J-2S rocket nozzle by varying either the material properties or the thickness of nozzle walls. This fully coupled method consists of the following: (1) a flow solver to simulate the flow field, (2) a structural solver to compute the structural dynamic response, (3) a computational mesh dynamics solver to accomplish the deformation of the fluid dynamics grid, and (4) a coupling technique to swap forces and displacements across the fluid-solid interface. It is found that the wall material properties and the wall thickness have tremendous effects on the aeroelastic behavior of rocket nozzles. Thus, the interaction between the shock-encompassed flow inside the rocket nozzle and the rocket nozzle structure has to be considered for the design of rocket engines. (C) 2017 American Society of Civil Engineers.
机译：用于运载火箭的新型火箭发动机喷嘴的开发遇到了一个具有挑战性的设计问题：为了满足高海拔的喷嘴性能，必须以高价值来设计喷嘴膨胀比。但是，这些将导致地面流动条件过度膨胀。这些条件继而产生不稳定的内部流分离。产生的不对称会导致侧向载荷，这不仅可能损坏喷嘴，还可能损坏整个发射系统。喷嘴中出现过多的侧向载荷是设计高效，可重复使用且坚固的运载火箭时要考虑的最重要问题之一。在这项工作中，使用了一种采用Navier-Stokes模拟的完全耦合方法，通过改变材料特性或喷嘴壁的厚度，对J-2S火箭喷嘴的气动弹性稳定性进行了数值研究。这种完全耦合的方法包括以下内容：（1）用于模拟流场的流动求解器；（2）用于计算结构动力响应的结构求解器；（3）用于完成流体动力学变形的计算网格动力学求解器（4）耦合技术，以交换流固界面上的力和位移。发现壁的材料特性和壁厚对火箭喷嘴的空气弹性行为具有巨大的影响。因此，在火箭发动机的设计中，必须考虑到火箭喷嘴内部的被冲击包围的流动与火箭喷嘴结构之间的相互作用。 （C）2017年美国土木工程师学会。

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