建立了运载火箭弹性模型脉动压力风洞试验方法，弹性模型同时模拟气动外形和减缩频率特性。开展了锤头体火箭刚性和弹性2种模型的风洞试验，测量表面脉动压力，研究模型弹性振动对表面非定常压力的影响。试验马赫数为2.5。试验发现刚性模型试验中不同攻角下脉动压力幅值较为接近，且功率谱中无明显主频。弹性模型试验中，小攻角下流场出现了以模型一弯频率及其倍频为特征的非定常压力脉动，同时脉动压力均方根相比刚性模型的结果大幅增加，流固耦合现象明显。在大攻角下弹性模型试验与刚性模型试验的脉动压力均方根比较接近，且压力信号无明显特征频率，流固耦合现象不明显。弹性模型试验中使用应变片对模型弹性梁的振动进行了测量，发现振动起始后经过发散段最终形成极限环振荡。通过滤波处理对比压力与结构振动一阶特征频率信号的相位关系，发现振动发散段模型上表面大部分测点的脉动压力与结构振动有半个周期左右的相位差；最终达到极限环振荡时，上表面脉动压力与振动接近同相位，脉动压力与振动的相位关系影响到流动对结构的做功效果。

A wind tunnel fluctuating pressure test method using the aeroelastic scaled model of a launch vehicle is established. The aeroelastic scaled model is similar to the launch vehicle in geometry and reduced frequency. A wind tunnel test using both the rigid scaled model and aeroelastic scaled model of a hammerhead launch vehicle is conducted to measure fluctuating pressure on the model surface and to evaluate the influence of vibration on unsteady pressure. The Mach number of the test is 2.5. Test results suggest that the flow field of the rigid model has no characteristic frequency while that of the elastic model at a small angle of attack encounters dominant frequencies which are exactly the first order model structural frequency and its multiplication. Moreover， the root-mean-squares of fluctuating pressure increase tremendously when fluid structure interaction occurs. At a high angle of attack， the root-mean-squares of fluctuating pressure on the elastic model decrease to the level near the rigid model results as the fluid structure interaction weakens. The strain at the base of the elastic beam is measured and the result shows a half cycle phase difference between the vibration and the pressure signal of the 1st order characteristic frequency at the divergent stage. Finally the interaction between the pressure and structure reaches a limit cycle oscillation stage and the phase difference decreases to nearly zero. These phase differences have an impact on the capacity of doing work on structure by flow.