一种超声速民机全周向角近场声爆快速预测方法
By combining the supersonic surface element method and the plane nonlinear wave characteristic line correction formula with the area balance principle and potential function method, a rapid near-field sonic boom prediction of the full circumferential angle of supersonic civil aircraft was realized. This solved the problems of large computational load and insufficient accuracy of traditional methods, simplified the sonic boom prediction process, and improved the accuracy.
CN116738889BActive Publication Date: 2026-07-17NORTHWESTERN POLYTECHNICAL UNIV
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- NORTHWESTERN POLYTECHNICAL UNIV
- Filing Date
- 2023-06-30
- Publication Date
- 2026-07-17
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Figure CN116738889B_ABST
Abstract
本发明提供一种超声速民机全周向角近场声爆快速预测方法，包括：采用超声速面元法对飞机流场进行求解，得到声爆信号监测位置线的压力系数分布；利用变换公式压力系数分布，变换为声爆信号监测位置线的线化超压信号分布；利用平面非线性波特征线修正方程，对线化超压信号分布进行非线性修正，得到带有多值点的扭曲超压信号分布；利用面积平衡原则与势函数方法，在扭曲超压信号分布中确定激波位置，根据激波位置对扭曲超压信号分布进行修正，得到声爆信号分布。该方法避免了飞机“体积分布”与“升力分布”两个等效截面积分布的求解，且考虑了激波传播过程中的非线性效应，能够对任意复杂外形超声速民机进行全周向角的近场声爆快速预测。
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