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以CFD流场与气动力计算为基础,分别利用小幅度强迫振动模式和差分两种方法推导了飞行器的纵向组合动导数计算表达式;建立了基于CFD技术的飞行器动导数计算方法;以国际标模Finner导弹为例,利用所推导的两种方法进行该导弹的动导数计算,重点分析了减缩频率对动导数计算的影响,提出了利用CFD方法开展动导数计算时减缩频率的选择原则;给出的计算结果与相关文献中的风洞实验结果吻合良好,表明基于CFD技术的动导数计算方法具有较高的工程实用价值。
Based on the CFD flow field and aerodynamic calculation, the expressions of the longitudinal combined kinematic derivatives of the aircraft are deduced by using the small amplitude forced vibration mode and the difference respectively. The calculation method of the dynamic derivative of the aircraft based on the CFD technique is established. The model Finner missile is taken as an example to calculate the dynamic derivative of the missile using the two methods. The influence of the reduction frequency on the calculation of the dynamic derivative is analyzed emphatically. The selection principle of the reduction frequency in the calculation of the dynamic derivative using the CFD method is given. The calculated results are in good agreement with the wind tunnel experiments in the related literature, indicating that the calculation method of dynamic derivatives based on CFD technology has high engineering practical value.