The invention discloses a wing system applied to a hypersonic aircraft, which comprises a wing structure unit and a thermal sensing unit, and the thermal sensing unit is arranged on the wing structure unit; a bearing structure in each wing structure unit comprises a plurality of bearing I-shaped beams, and a plurality of high-thermal-conductivity material blocks are embedded in the bearing I-shaped beams; the thermal sensing unit comprises a signal collecting and processing device and a thin film thermoelectric material, the thin film thermoelectric material covers the surface of the high-thermal-conductivity material block, and the signal collecting and processing device is installed on the bearing structure. The wing structure is optimally designed through binding force/thermal coupling, the temperature of the wing surface can be detected through the Seebeck effect generated by the thin film thermoelectric material, and the device has the advantages of being simple in mechanical structure and integrated.
本发明公开了一种应用于高超声速飞行器的机翼系统,包括机翼结构单元和热感知单元,所述热感知单元设置在机翼结构单元上;所述机翼结构单元中的承载结构包括若干承载工字梁,所述承载工字梁上镶嵌有若干高导热材料块;所述热感知单元包括信号采集与处理装置和薄膜热电材料,所述薄膜热电材料覆盖于高导热材料块的表面,所述信号采集与处理装置安装在承载结构上。本发明结合力/热耦合优化设计机翼结构,利用薄膜热电材料产生的塞贝克效应,能够对机翼翼面进行温度检测,具有机械结构简单,一体化集成的优点。
Wing system applied to hypersonic flight vehicle
一种应用于高超声速飞行器的机翼系统
29.08.2023
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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