The invention provides a model design method for a large aircraft component icing wind tunnel test. The model design method comprises the steps that the large aircraft component for the icing wind tunnel test and the size of an icing wind tunnel test section are determined; according to the size of an icing wind tunnel test section, segmenting a part model used for a test in the full-aircraft model; rectifying the segmented part model; key parameters of the rectified component model are calculated; key parameters of the whole-aircraft model and the component model are compared, and whether the component model can effectively represent the icing characteristics of the whole aircraft in the area or not is evaluated; and after repeated iterative optimization is carried out until the component model meets the test requirement, it is considered that the test model is successfully designed, and the current component model is determined as the model shape for the icing test. According to the invention, the complex flow field of the complex part of the large aircraft can be accurately simulated, so that the icing condition of the complex part of the large aircraft can be accurately simulated.
本发明提供一种用于大型飞机部件结冰风洞试验的模型设计方法,包括确定用于结冰风洞试验的大型飞机部件及结冰风洞试验段尺寸;根据结冰风洞试验段尺寸大小在全机模型中分割出用于试验的部件模型;对分割出的部件模型进行整流;计算整流后部件模型的关键参数;对比全机模型和部件模型的关键参数,评估部件模型是否能够有效代表全机在该区域的结冰特性;经过反复迭代优化,直至部件模型满足试验要求后,则认为试验模型设计成功,确定当前部件模型为用于结冰实验的模型外形。本发明能够准确模拟大型飞机复杂部件的复杂流场,进而能够准确模拟大型飞机复杂部件的结冰状况。
Model design method for icing wind tunnel test of large aircraft component
一种用于大型飞机部件结冰风洞试验的模型设计方法
2024-12-13
Patent
Electronic Resource
Chinese
IPC: | G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / 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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