为了实现带加力航空涡扇发动机最大推力寻优,作为途径之一,提出了一种新的加力燃油流量寻优控制方法。在常规开环的加力燃油流量控制计划的基础上,叠加一个闭环的寻优修正,以余气系数、加力燃烧室出口温度、喷口面积等参数为约束条件,并给出了不可测约束参数的解析计算方法以及解析余度校验方法。以某航空发动机动态模型为例进行了寻优控制方法的仿真验证,结果表明,采用新的加力燃油寻优控制方法,在包线范围内平均可以将发动机最大推力提高6%左右,并具备较好的寻优控制安全性。 In order to optimize the maximum thrust of Air Turbofan engine, as one of the ways, a new method for optimizing fuel flow control is proposed. Based on the conventional open-loop afterburner flow control scheme, a closed-loop optimization is added to the optimization, and the residual gas coefficient, afterburner outlet temperature, nozzle area and other parameters are used as constraints, and the unobserved constraints Analytical calculation of parameters and analysis of redundancy test method. Taking aeroengine dynamic model as an example, the simulation and verification of the optimal control method are carried out. The results show that the new optimal fuel control method can increase the maximum thrust of the engine about 6% Better search control safety.