基于面积律自动判别的飞机机身外形修形方法

为提高超声速飞机方案修形效率，研究了依据飞机截面积分布曲线分析结果进行飞机截面精细化修形的方法。提出了基于面积律自动判别的截面积曲线分析法，能够依据面积律准则快速对可能增大激波阻力的站位进行自动判别和定位。在此基础上建立了飞机机身几何外形快速辅助修形方法，实现了对超声速飞机方案的待修形位置自动快速分析与定位，并根据截面位置部件分析和截面积曲线变化分析，提供针对截面积的量化调整建议。对一种超声速轰炸机方案进行机身几何外形修形的算例表明，本文提出的方法能够快速识别和定位截面积曲线上拐点、阶跃点、极值点及尖角点等增大激波阻力的位置，根据修形方法调整后的方案阻力系数下降了1.5%，验证了方法的有效性。

Aircraft Fuselage Configuration Adjustment Method Using Automatic Judgment of Area Rule

The shock wave drag influence from the section area distribution should be considered in supersonic aircraft design, and the aircraft configuration should be adjusted and optimized according to the area rule. To increase the efficiency of supersonic aircraft configuration adjustment, the accurate shape-modified method is researched through the analysis of aircraft section area distribution curve based on the area rule. An aircraft section area distribution curve analysis method is proposed based on automatic area rule judgment, which could automatically judge and locate the wave drag rising position. And then the fast computer-aided shape-modified method for aircraft fuselage configuration adjustment is given. With the method, the shape of the supersonic aircraft can be analyzed automatically and quickly, and the accurate section positions to be modified along with the adjusted suggestion of quantized section area are provided. The method is used in the fuselage configuration adjustment of a supposed supersonic bomber. Factors increasing the wave drag could be quickly discriminated and located with the method, including inflexions, steps, extremum and concave points on the section area curve. Manual modifications are conducted on the sections according to the adjustment suggestion, and then the drag coefficient is reduced 1.5%, which validates the effectiveness of the method.