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本文提出了将超音速进气道-发动机装置(简称动力装置)作为统一控制对象的双变量(进气道结尾正激波位移与发动机转速)动态模型。在作者前一篇论文的基础上,本文进一步考虑了动态过程中发动机对进气道的流量反馈机理,并采用矩阵分式描述法进行模型的频域向时域转换,因而使模型更趋近于反映实际。对NASA的48cm进气道—J85发动机装置的数字模拟表明,结果是满意的。
In this paper, a dynamic model of bivariate (positive shock displacement at the end of intake passage and engine speed) with a supersonic inlet-engine device (referred to as a power plant) as a unified control object is proposed. Based on the previous paper of the author, this paper further considers the feedback mechanism of engine inlet flow in dynamic process and adopts the matrix fractional description method to transform the frequency-domain to time-domain of the model, thus making the model closer To reflect the actual. A numerical simulation of NASA’s 48 cm inlet-J85 engine assembly showed that the results were satisfactory.