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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。
By studying the coupled effect of elastic vibration and gas motion of hammerhead rocket during transonic flight, the technique and method for determining aerodynamic damping coefficient are described by wind tunnel experiment and unsteady numerical calculation with full elastic model. The results of experiment and numerical simulation are given separately, and the results are compared and analyzed. The results show that in the aerodynamic damping experiment, it is very important to simulate the position of the front node of the low-order intrinsic modes. This method can be used as a method to study the unsteady aerodynamic characteristics of spacecraft.