所述方法在某型双转子涡喷发动机气动热力学非线性模型上对抗干扰性和目标跟踪进行了仿真验证。
Simulations on the nonlinear model of the twin spool turbojet engine aerothermodynamics are conducted to verify the disturbance rejection and tracking performance.
根据控制体理论，建立了涡喷发动机中压气机的逐级数学模型。
A stage by stage mathematical model of the compressor in a turbojet engine is developed based on the control volume theory.
应用本文方法对某型双转子加力涡喷发动机仿真模型进行校正，获得了满意的仿真精度。
As an example, the method provided was adopted to rectify the parameters in the simulation model of a given twin-spool reheated turbojet engine, and the simulation achieved satisfactory accuracy.
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