论文部分内容阅读
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.
Aiming at the design problem of the optimal control law of aero-engine transition states, a new method, dynamic stability method, is proposed based on the calculation model of engine dynamic characteristics by extrapolating all the state variable rates The deviation of the working equations tends to 0, so that the simulation of the transition state is stabilized. The steady-state parameter values at this time are the parameters corresponding to the operating points in the transition state. Then, according to the specified physical constraints, Optimization can directly establish the corresponding control law; Finally, the control law by taking the big / small way to merge, so as to obtain the required optimal control law of transition state .To some type of turbofan engine optimal acceleration control law of the improved design For example, the results show that the method has the advantages of high design accuracy, simple implementation and quick and intuitive.