高超声速气流中吹气对钝鼻再入飞行器俯仰动稳定性的影响

M. Khalid, K. Juhany
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引用次数: 0

摘要

吹气通常用于缓解高超声速飞行器钝鼻上的强烈升温率。前缘的射流改变了钝鼻区的流场,影响了飞行器的动力稳定性。作为示范实验,采用激波膨胀法恢复非定常压力系数,对吹气和不吹气条件下经过钝鼻和截鼻锥体的流场进行扰动,得到非定常效果。然后,通过对非定常压力系数相对于俯仰角(α)或俯仰速率($\dot \theta $)的微分与力臂相对于重心的积分,得到静力矩和俯仰力矩的导数。钝鼻体和截锥形体的动态稳定性明显下降。即使当气流从钝鼻飞行器肩部的切向吹风转变时,其动态稳定性也会有所下降。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Effects of blowing upon dynamic stability of blunt nosed re entry vehicles pitching in hypersonic flow
Blowing is often used to alleviate the intense heating rates on blunt noses of hypersonic vehicles. This flow efflux at the leading edge transforms the flow field in the blunt-nose regions with implications on the dynamic stability of the vehicles. As a demonstrative exercise, the flow fields past blunt-nosed and truncated-nosed conical bodies under blowing and no-blowing conditions were perturbed to obtain the unsteady effects using the shock expansion method to recover the unsteady pressure coefficient. Static and pitching moment derivatives were then duly obtained by integrating the differential of the unsteady pressure coefficient with respect to the pitch angle (α) or the pitch rate ( $\dot \theta $ ) together with the moment arm with reference to the centre of gravity. The results obtained for blunt-nose and truncated conical bodies show a noticeable drop in dynamic stability. Even when the flow is transformed from a tangential blowing at the shoulder of the blunt-nosed vehicle shows some degradation in dynamic stability.
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