锤头体弹性振动跨音速气动阻尼系数的确定

The determination of aerodynamic damping on hammerhead launch vehicles at transonic speeds

通过研究锤头形运载火箭跨音速飞行时 ,箭体结构的弹性振动与气体运动的耦合效应 ,描述了用全弹性模型的风洞实验和非定常数值计算 ,确定气动阻尼系数的技术和方法。分别给出了实验和数值模拟的结果 ,并对结果进行了对比分析。结果表明 ,在气动阻尼实验中 ,模拟低阶固有模态的前节点位置是非常重要的。该方法可以作为研究航天飞行器非定常气动特性的一种方法。

The structure response of the hammerhead launch vehicles interacts by the transonic air flow.This effect is characterized with the aerodynamic damping coefficient.Experimental and numerical approaches to determine the coefficient were described in this paper.The results were presented and analyzed comparatively.It can be concluded that the methods are practicable to determine the unsteady aerodynamics of the space launch vehicles.