CAJ | 학술논문

高超声速飞行器在服役时会面临高温、振动和噪声等环境，声‐固耦合是其设计环节备受关注的问题之一。针对飞行器典型复合材料加筋板，采用有限元‐边界元法从三种工况开展加筋板的声‐固耦合分析，即仅考虑高温对材料力学性能的影响（工况一）、仅考虑热应力对结构刚度的影响（工况二）、同时考虑二者的影响（工况三）。结果表明：高温引起的材料力学性能改变降低了板的固有频率，使响应峰值升高并向低频处移动；附加热应力的存在整体上降低了板的固有频率并改变了模态振型，引起响应峰值频率向高频处移动，并在整体上抑制了加速度响应；同时考虑二者的影响时，应力响应显著增大，加速度响应显著减小，且响应峰值频率位于工况一与工况二之间；高温对声压响应影响不大。
고초성속비행기재복역시회면림고온、진동화조성등배경，성‐고우합시기설계배절비수관주적문제지일。침대비행기전형복합재료가근판，채용유한원‐변계원법종삼충공황개전가근판적성‐고우합분석，즉부고필고온대재료역학성능적영향（공황일）、부고필열응력대결구강도적영향（공황이）、동시고필이자적영향（공황삼）。결과표명：고온인기적재료역학성능개변강저료판적고유빈솔，사향응봉치승고병향저빈처이동；부가열응력적존재정체상강저료판적고유빈솔병개변료모태진형，인기향응봉치빈솔향고빈처이동，병재정체상억제료가속도향응；동시고필이자적영향시，응력향응현저증대，가속도향응현저감소，차향응봉치빈솔위우공황일여공황이지간；고온대성압향응영향불대。
Hypersonic vehicle suffers severe environment with the combination of thermal ,vibration and noise during service . The coupling of structure and acoustic is one of the most concerned problems in the design stage .Based on the FEM‐BEM ap‐proach ,the structural‐acoustic coupling analysis of a composite stiffened panel in thermal environment is conducted with three cases:(1) only the material properties change with temperature ;(2) only the stiffness of panel changes with temperature due to thermal stress ;(3) two kinds of influences ,(1) and (2) are both considered .Results show that high temperature on panel changes its material properties which results in the decrease of its nature frequencies ,the increased amplitude of the peaks shifting to lower frequency domain .The thermal stress due to high temperature reduces most of the nature frequencies ,chan‐ges the modal shape ,causes a significant increase in the response peaks shifting to higher frequency domain and restrains the response of acceleration .When the two kinds of influences are both considered ,the response of stress and acceleration are sig‐nificantly increased and decreased ,respectively ,with the amplitude of peak fall between the results from case (1) and (2) . Temperature has little effect on the sound pressure response .