Metallic panels are major structural components for thermal protection system of hypersonic vehicles, which are exposed to a severe combination of aerodynamic, thermal and acoustic environments during cruise or re-entry flights. It presents a significant challenge for the integrity and the durability for these structures. Titanium flat and stiffened panels are designed. Then, a series of dynamic response tests of these panels are carried out using a thermal-acoustic apparatus. The temperature of the testing panel is up to 400℃and the exciting acoustic load is over 162 dB. Dynamic responses of these testing panels are measured using high temperature accelerometer and strain gauge during the testing process. Results show that the maximal root mean square (RMS) acceleration values of the flat plate and stiffened panel are approximate to 94.5g and 199.0g, respectively. It is shown that the dynamic RMS values are dominated by sound pressure level of acoustic loads. However, the thermal environment has more effects on the power spectral density distribution than the RMS values of dynamic response excited by acoustic loads.%高超声速飞行器热防护系统包含多种形式的金属壁板结构，巡航或再入过程中经历着严酷的气动热、气动力、噪声等复合环境，严重威胁着飞行器结构的完整性和可靠性。为评估壁板结构的耐噪声性能，设计了钛合金平板和加筋板试验件，采用热噪声试验系统开展了试验件中心温度最高为400℃、噪声最高为162dB的动响应试验，采用高温加速度计和高温应变片对动态响应进行了测试。结果表明，钛合金平板和加筋板的最大加速度均方根值分别可达94.5 g和199.0g，金属壁板动态响应均方根值与噪声量级密切相关，受热环境影响较小，而热环境显著改变了动态响应的频谱分布。
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