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鉴于高超声速飞行器特有的外形布局和飞行状态限制,高超声速飞行器声载荷试验存在模型头部气动加热较强、弹舱内走线空间有限、弹翼声载荷测量难度较大等困境。针对这些难点问题逐一进行了分析研究,并提出相应解决方案,满足了试验的要求。通过风洞脉动压力试验,获得飞行器表面脉动压力系数分布、频谱特性、相干函数等重要衡量非定常载荷特性的参数,为高超声速飞行器结构设计提供数据支持。
In view of the hypersonic vehicle’s unique shape layout and flight status limitation, the hypersonic vehicle’s acoustic load test has the problems of strong aerodynamic heating of the model head, limited space for cabins in cabins, and difficulty in measuring acoustic load of the missile wing. In view of these difficult problems one by one carried on the analysis research, and proposed the corresponding solution, satisfies the test request. Through the wind tunnel pulsating pressure test, parameters such as pulsating pressure coefficient distribution, spectrum characteristic and coherence function of aircraft surface are obtained, which provide the data support for the design of hypersonic vehicle structure.