为了保证星载测风多普勒差分干涉仪的力学稳定性和热稳定性, 设计了一种低热传导微应力装夹支撑结构, 采用胶合与弹性压紧相结合的方法对干涉仪进行安装.首先, 结合多普勒差分干涉仪的结构特点和稳定性要求, 采用四点环形凸台的粘接形式对底座粘接面进行了优化设计, 并与已有的网格化多点凸台粘接面形式进行对比.然后, 针对随机振动条件下干涉仪与底座粘接面响应应力过大的问题, 设计了施加预紧力的压盖结构来提高粘接可靠性.最后, 对干涉仪组件进行了有限元仿真和环境振动试验, 分析和验证了干涉仪组件的低热传导性和力学可靠性.结果表明, 所设计的四点环形凸台粘接形式相较于已有粘接形式在相同条件下由底座导入光学组件的热量减少了63.54%, 随机振动时粘接面最大响应应力为2 MPa, 干涉仪组件的模态频率均在1 900 Hz以上; 有限元仿真与试验结果的相对误差均在8.6%以内.基于四点环形凸台面粘接并施加预紧力的干涉仪组件具有低热传导、高力学可靠性的特点, 结构设计合理, 性能可靠.

In order to ensure the mechanical stability and thermal stability of the satellite-borne Doppler asymmetric spatial heterodyne interferometer on wind measurement, a low heat conduction and microstress support structure is designed, and the interferometer is clamped by the combination of bonding and elastic compression. Firstly, according to the structural characteristics and stability requirements of the interferometer, a ring bonding surface is proposed, the bonding surface is optimized and compared with the existing one. Then, in view of the question that the response stress of the interface between the interferometer and the base is too large under the condition of random vibration, a cover structure with pretension is designed to improve bonding reliability. Finally, finite element simulation and test are carried out to analyze and verify the low thermal conductivity and mechanical reliability of the interferometer assembly. Experimental results indicate that the ring bonding surface has a 63.54% reduction in the heat input from the base to the optical components under the same conditions than the existing one. The maximum response stress of the adhesive surface at random vibration is 2 MPa. The basic frequencies of the interferometer component are all above 1900 Hz. The relative error of the analysis and test results is less than 8.6%. The interferometer based on the ring bonding surface and pretension has the characteristics of low heat conduction and high mechanical reliability, the structure design is reasonable and the performance is reliable.