The invention discloses a self-adaptive bump air inlet channel structure design method, and belongs to the field of aircraft air inlet channel structure design. Comprising four parts of high-bearing and large-deformation flexible skin design, main bearing structure design, distributed pressure-driven multi-airbag system design and control system design. According to the design scheme of the honeycomb filling flexible skin, the pneumatic pressure of the air inlet channel can be effectively borne, large out-of-plane deformation can be achieved, and the honeycomb filling flexible skin is an important composition structural part for achieving the self-adaptive bulging function; deformation of the bump molded surface is achieved through inflation and deflation of the air bag, the driving form is simple, the response speed is high, and the occupied size of the driving system is small; the multi-air-bag driving mode plays a good distributed driving role, the molded surface can be directly and effectively driven to deform under the effect of incoming flow loads, and therefore high-precision control over the molded surface of the bulge air inlet channel can be achieved.
一种自适应鼓包进气道结构设计方法,属于飞行器进气道结构设计领域。包括高承载及大变形的柔性蒙皮设计、主承载结构设计、分布式压力驱动的多气囊系统设计以及控制系统设计四个部分。本发明中蜂窝填充柔性蒙皮的设计方案能够有效承受进气道的气动压力并且可以实现较大的面外变形,是自适应鼓包功能实现的重要组成结构件;本发明通过气囊充放气实现鼓包型面的变形,驱动形式简单,响应速度快,并且驱动系统的占用体积小;本发明中多气囊的驱动方式起到很好的分布式驱动作用,能够在来流载荷作用下直接有效地驱动型面变形,从而可以实现鼓包进气道型面的高精度控制。
Design method for self-adaptive bump air inlet channel structure
一种自适应鼓包进气道结构设计方法
2025-02-25
Patent
Electronic Resource
Chinese
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
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