中文摘要：

为揭示跨声速阶段仪器舱附近脉动压力的空间相关特性，以某旋成体模型为研究对象，基于风洞试验获取了仪器舱附近脉动压力载荷分布规律，计算了测点间的脉动压力空间相关系数。通过曲线拟合与归一化处理，获得了模型仪器舱脉动压力空间相关特性曲线，并研究了攻角、马赫数与雷诺数对空间相关性的影响。结果表明，该模型仪器舱脉动压力空间相关特性具有波动与衰减的特点，随着流动复杂程度的增加，其相关性逐渐降低。同时，在跨声速范围内，该模型仪器舱脉动压力空间相关特性对马赫数以及较高的雷诺数比较敏感。对脉动压力空间相关特性的研究，为飞行器结构响应分析以及载荷环境预示提供了支撑。

英文摘要：

Based on a rotated model, the distribution of the fluctuating pressure nearby the instrument cabin is obtained in the wind tunnel and the spatial correlation coefficients between the test points are calculated to show the spatial correlation characteristics of the fluctuating pressure. With the curve fitting and normalized method, the spatial correlation curves of the instrument cabin are acquired and the influences of attack angle, Mach number and Reynolds number are discussed. It is showed that the fluctuating and attenuation characteristics exist in the fluctuating pressure spatial correlation of the instrument cabin and the correlation extent is weakened by the complex flows. In the transonic range, some sensitivities to the special Mach number and high Reynolds number exist in the fluctuating pressure spatial correlation characteristics of the model. Some references are provided for spacecraft random vibration response analysis as well as load and environment prediction with the study of the spatial correlation characteristics of the fluctuating pressure.