航空发动机过渡态最优控制规律设计的新方法

A new method for designing optimal control law of aeroengine in transient states

针对航空发动机过渡态最优控制规律的设计问题,提出了一种新的方法——动态稳定法:在发动机动态特性计算模型的基础上,通过额外提取其中所有的状态量变化率,使其共同工作方程组的偏差趋于0,从而让过渡态仿真稳定下来,此时的稳态参数值即为对应过渡态工作点的各项参数;然后分别根据指定的物理约束条件,通过简单的静态迭代优化即可直接建立相应的控制规律;最后将这些控制规律通过取大/小的方式进行合并,从而获得所需过渡态最优控制规律.以某型涡扇发动机最优加速控制规律的改进设计为例,结果表明该方法具有设计精度高、实现简单以及快速直观等优点.

A new method fixed dynamic method （FDM）, which delt with the issue of designing optimal control law of aeroengine in transient states, was proposed. Firstly, based on a detailed non-linear aerothermodynamic model, it made the errors of nonlinear equations set to zero via extracting all of state variable rates and let the model reach steadystate, which meant the parameters in this state were equal to that in transient state; secondly, according to the given limited conditions respectively, the control laws can be built directly via simple static programming method; finally, merged all of them via Max/Min selection and obtained the optimal control law. The computing results of the improved acceleration control law of some turbofan engine indicate that the FDM is accurate and effective.