三维构型飞机的动导数数值计算  

Numerical Calculation of Dynamic Derivatives of 3D Configured Aircraft

作　　者：罗祎晨 许和勇[1,2] 章胜 胡芳芳 LUO Yi-chen;XU He-yong;ZHANG Sheng;HU Fang-fang(Northwestern Polytechnical University,Xi′an 710000,China;National Key Laboratory of Aircraft Configuration Design,Xi′an 710000,China;China Aerodynamic Research and Development Center,Mianyang 621000,China)

机构地区：[1]西北工业大学,陕西西安710000 [2]飞行器基础布局全国重点实验室,陕西西安710000 [3]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《航空计算技术》2025年第2期43-47,53,共6页Aeronautical Computing Technique

摘　　要：动导数的精确预测对于飞行器的稳定性分析至关重要。针对三维飞机基于双时间推进法数值求解非定常N-S方程,采用传统的谐和俯仰振动方法和差速振动法获取该型飞机组合俯仰动导数,进一步采用升沉振动法获取时差动导数,采用旋转流场法获取阻尼动导数。结果表明:谐和俯仰振动方法和差速上仰法获取的飞机动导数计算结果具有较好的一致性,差速上仰法相较于谐和俯仰振动方法效率更高;升沉振动法获取的飞机时差动导数与旋转流场法获取的飞机阻尼动导数具有较高的可靠性与工程精度,为工程中快速获得精确动导数提供了技术支撑。Accurate estimation of dynamic derivatives is essential for the stability analysis of aircraft.This paper presents a numerical solution to the unsteady Navier-Stokes equations for a specific class of aircraft,employing the dual-time stepping method,and utilize both traditional harmonic oscillation and differential oscillation techniques for pitch motion to derive the combined pitch dynamic derivative.Additionally,the sink-rise oscillation method is applied to determine the time-lag dynamic derivative,while the rotating frame of reference method is used to compute the damping dynamic derivative.The results indicate that the dynamic derivatives obtained via harmonic oscillation and differential oscillation methods exhibit good consistency,with the differential oscillation method demonstrating higher computational efficiency.The time-lag dynamic derivatives derived from the sink-rise oscillation method and the damping dynamic derivatives from the rotating frame of reference method exhibit high reliability and engineering accuracy,thereby providing a robust technical foundation for the rapid acquisition of precise dynamic derivatives in practical applications.

关 键 词：俯仰动导数 数值模拟 差速上仰法 升沉振动法 旋转流场法 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]