航空发动机飞行推力的确定是获得飞机极曲线的重要步骤。为了提出一种测量参数少、计算精度高、适合用于带有加力燃烧室的发动机的推力确定方法,本文对简化总推力计算模型进行改进,利用遗传算法和罚函数法,分析了修正因子的物理意义,对其进行二次优化,结合J85-GE-21发动机台架试验数据对此方法进行验证,将稳态试验数据与计算数据进行比较。结果表明,目标函数的相对误差明显降低,即本文提出的改进方案是有效的,可将其应用于飞行试验中去。 Aero-engine flight thrust determination is an important step in obtaining the aircraft’s polar curve. In order to propose a method to determine the thrust of an engine with afterburner with less measurement parameters and high calculation accuracy, this paper improves the simplified total thrust calculation model by using genetic algorithm and penalty function method, and analyzes the correction factor The physical meaning of this method is optimized for the second time. The method is validated by the test data of J85-GE-21 engine bench, and the steady-state test data and calculated data are compared. The results show that the relative error of the objective function is obviously reduced, that is, the improved scheme proposed in this paper is effective and can be applied to the flight test.