作者：孙科
作者单位：中国飞行试验研究院, 陕西 西安 710089
关键词：发动机试验;音爆;胞格;矩形模式
摘要：
为实现跨代战机发动机的音爆特性及音爆激波的包长分布状态测试，提出一种数值测试算法三阶精度的Runge-Kutta测试分析算法。以某型航空发动机设计参数为研究对象，给出该算法对音爆的控制方程组，运用Runge-Kutta法分析和测试该型战机发动机的音爆波在空中传播所生成的胞格结构以及在传播中出现的二维音爆波和三维音爆波包长分布的角形和矩形模式。运用航空仿真平台和风洞实验数据，与该方法得出的音爆波在空中的精确传播特性进行对比，结果表明该数值测试方法具有较好的实现性和较高的测试精度。
Test method of sonic boom for aeroengine
SUN Ke
Flight Test Establishment of China, Xi'an 710089, China
Abstract: In order to achieve the test for sonic boom characteristics of inter-generational fighter aeroengine and sonic wave packet length distribution state, a new type of numerical test algorithm (third-order-accuracy Runge-Kutta test & analysis algorithm) was proposed. Design parameters of a certain type of aeroengine were taken as research object and control equations of the algorithm on sonic boom was given, and Runge-Kutta method was also used to analyze and test the structure of diagonal mode caused by sonic wave of the fighter aeroengine during propagation in air and angular and rectangular mode of 2D sonic boom wave and 3D sonic boom wave in packet length distribution generated in propagation. Based on the aviation simulation platform, wind tunnel test data and comparison with accurate propagation characteristics of sonic boom wave in air obtained in the method, the results show that the numerical test method has excellent realization and high test precision.
Keywords: aeroengine test;sonic boom;diagonal mode;rectangular mode
2018, 44(1): 27-30 收稿日期: 2017-04-02;收到修改稿日期: 2017-06-19
基金项目: 国防基础科研项目（A0520132031）
作者简介: 孙科(1982-),男,山西大同市人,高级工程师,硕士,研究方向为飞行器飞行试验机载测试技术。
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