为获得通航飞机热固性环氧树脂的固化动力学特性方程和固化动力学参数，利用差示扫描量热法（DSC）在不同升温速率下对热固性环氧树脂进行非等温测试，并拟合实验曲线数值，得到热固性环氧树脂固化动力学特性。采用Ozawa-Wall-Flynn （OWF）和Kissinger-Akahira-Sunose（KAS）方法确定活化能，研究表观活化能随固化度的变化情况。基于Málek方法解析固化反应机理，结果表明：该树脂固化行为符合Sestak-Berggren自催化模型。通过非线性拟合（LSR）确定指前因子（A）、反应级数（m，n），建立固化动力学模型。将模型预测的固化反应速率-固化度曲线与实验结果进行对比，结果表明：模型预测值和实验值基本吻合。因此，获得的固化动力学模型能够准确描述该树脂固化反应过程。研究工作为通航飞机复合材料的制造与修补过程制定固化工艺参数提供参考。

In order to obtain the curing kinetic equation and curing kinetic parameters of thermosetting epoxy resin for general aviation aircraft, the non-isothermal test of thermosetting epoxy resin was carried out by differential scanning calorimetry (DSC) at different heating rates, and the curing kinetic properties of thermosetting epoxy resin were obtained by fitting the numerical values of the experimental curve. The Ozawa-Wall-Flynn (OWF) and Kissinger-Akahira-Sunose (KAS) methods were used to determine the activation energy, and the change of apparent activation energy with the degree of curing was studied. Based on the Málek method, the curing reaction mechanism was analyzed, and the results showed that the curing behavior of the resin was in line with the Sestak-Berggren autocatalytic model. The pre-index factor (A) and reaction order (m, n) were determined by nonlinear fitting (LSR), and the curing kinetic model was established. The curing reaction rate-curing degree curve predicted by the model was compared with the experimental results, and the results showed that the predicted values of the model were basically consistent with the experimental values. Therefore, the curing kinetic model obtained can accurately describe the curing reaction process of the resin. The research work provides a reference for the manufacturing and repair process of composite materials for general aviation aircraft, and the formulation of curing process parameters.