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为了满足机载航空推进系统模型对精度、实时性及数据存储量的苛刻要求,提出了一种机载模型建模方法.对传统的机载稳态模型建立过程中使用的相似准则进行了充分讨论,得出了一种具备更高建模精度的相似准则.在新的相似准则基础上,建立了包含泰勒展开式中非线性2阶项的高精度稳态变量模型,有效解决了分段线性稳态变量模型在大包线、变状态条件下精度难以保证的问题;为了解决超声速状态下安装推力与发动机净推力差别较大的问题,建立了考虑外流特性的简化进气道模型,给出了一种计算安装推力的方法,即由简化发动机模型计算安装推力中符合相似准则的部分,由进气道模型计算溢流阻力、放气阻力及发动机推力中不符合相似准则的部分.仿真结果表明:基于新的相似准则所建立的机载模型具有大包线、变状态适应性,输出参数误差均在0.5%以内.
In order to meet the demanding requirements of accuracy, real-time and data storage of airborne propulsion system model, an airborne model modeling method is proposed, and the similar criteria used in the establishment of traditional airborne steady-state model , A similar criterion with higher modeling accuracy is obtained.On the basis of the new similarity criterion, a high-precision steady-state variable model with non-linear second-order terms in Taylor expansion is established to effectively solve the problem of piecewise linear stability In order to solve the problem that the difference between thrust and engine thrust under supersonic condition is large, a simplified inlet model considering the outflow characteristics is established and the model of the inlet is given A method of calculating the thrust force of installation, that is, simplifying the engine model to calculate the part of the thrust force meeting the similar criterion and calculating the part of the thrust resistance, deflation resistance and engine thrust which do not accord with the similar criterion from the intake port model, : The airborne model established based on the new similarity criterion has large envelope and variable state adaptability with output parameter errors within 0.5%.