航空发动机过渡态最优控制规律设计的新方法

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 for designing optimal control law of aeroengine in transient states

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 steady-state,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.