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为解决超机动飞行中发动机喘振裕度不可测量的难题,提出一种发动机喘振裕度的建模方法.喘振裕度的模型分为常规飞行时的无畸变模型与超机动飞行时的损失量模型两部分.无畸变模型是基于喘振裕度特征选择算法筛选最优模型输入,以非线性拟合方法建模实现;损失量模型则基于在线攻角预测模型实时评估发动机进口畸变度,进而计算获得.而后利用上述估计模型对发动机的稳定性进行实时预测,在不改变发动机原控制回路的基础上,对涡轮落压比控制指令进行喘振损失补偿,实现高稳定性控制.最后,通过大攻角机动飞行的数字仿真,验证了上述方案可以准确控制发动机喘振裕度在11%～13%,保证了发动机工作的稳定性和高效性.
In order to solve the problem of unmeasurable surge margin in super-maneuvering flight, a modeling method of engine surge margin is proposed.The models of surge margin are divided into the non-distortion model of conventional flight and the model of super maneuver Loss model.None-distortion model is based on the selection of the optimal model for the surge margin feature selection algorithm, which is modeled by non-linear fitting method. The loss model is based on on-line angle of attack prediction model to assess the engine inlet distortion , And then calculate the obtained.And then use the above estimation model to predict the stability of the engine in real time, without changing the original control loop of the engine, to compensate for the surge pressure loss of the turbine pressure ratio control command to achieve high stability control. Through the numerical simulation of maneuvering flight at high angle of attack, it is verified that the above scheme can accurately control the surge margin of the engine at 11% ~ 13%, ensuring the stability and high efficiency of the engine work.