摘要 热隔膜成型工艺已成为国外大型飞机长桁等 C 型构件的自动化制造方法，对于热隔膜的研究也越来越多。在等截面及渐变铺层 C 型梁的热隔膜成型过程中，经常会面临褶皱缺陷。针对褶皱的形成原理，采用了国内外的 3 种对比材料、2 种 C 型梁模型，通过不同厚度及温度、压力的工艺试验，对热隔膜成型过程中的温度、压力、材料、热隔膜次数及坯料的铺放形式进行了研究。试验结果表明，预成型温度要保持在 65℃ 为宜，保压时间不低于 15min，多次热隔膜压力不超过 6kPa/min，可有效地抑制褶皱产生，同时由铺丝工艺制备的坯料在热隔膜时层间滑移更均匀。相关研究为国产大飞机热隔膜成型提供初步理论基础。
Abstract：Hot diaphragm forming technology has become an automatic manufacturing method for C spar components in the large aircraft abroad, and more and more researches on hot diaphragm forming has been done. In the hot diaphragm forming process of equal cross section and gradual lamination C spar, wrinkle defects are often occurred. According to the principle of hot diaphragm forming, three kinds of comparative materials at home and abroad, two kinds of C spar models, were used to study the temperature, pressure, material, multiple hot diaphragm and the laying form of hot diaphragm through the technological experiments of different thickness, temperature and pressure. The experimental results show that the pre-molding temperature should be kept at 65℃, the holding time is not less than 15min, and the pressure of multiple hot diaphragm is not more than 6kPa/min, which can effectively inhibit the formation of folds. At the same time, the slip between layers of the embryo prepared by wire laying process is more uniform in the hot diaphragm. The related research provides a preliminary theoretical basis for the hot diaphragm molding of domestic large aircraft.
李璐璐，任亚辉，孙松强，王雨. 复合材料C型梁热隔膜成型影响因素分析[J]. 航空制造技术, 2020, 63(8): 93-100.
LI Lulu，REN Yahui， SUN Songqiang，WANG Yu. Analysis of Influencing Factors on Hot Diaphragm Forming for Composite C Spar. Aeronautical Manufacturing Technology, 2020, 63(8): 93-100.
2020, 
