论文部分内容阅读
提出一种直接求解直接阻尼导数的方法,该方法不仅适用于轴对称外形,也适用于非轴对称外形.数值模拟飞行器的非定常强迫沉浮运动和强迫角振动,并在Etkin的非定常气动力模型基础上,辨识得到飞行器的洗流时差导数和俯仰阻尼导数,研究飞行器俯仰通道各阻尼导数的数值计算方法.对弹道外形和基本带翼导弹标模外形及Hyflex升力体外形进行研究分析表明,将阻尼导数分量相加得到的俯仰阻尼导数与直接求解强迫角振动得到的俯仰阻尼导数与试验结果吻合很好,各阻尼导数分量随质心位置的变化趋势也与理论预测相符.对于带翼飞行器,超声速条件下,洗流时差导数在俯仰阻尼导数中占主导作用.
A direct solution to the problem of direct damping derivatives is proposed, which is not only applicable to the axisymmetric shape but also to the non-axisymmetric shape.Numerical simulation of unsteady forced aerodynamic ups and downs and forced angular vibration of an aircraft, Based on the model, the time-difference derivative and pitch-damping derivative of washer flow were identified and the numerical calculation method of each damping derivative in the pitch channel was studied.Analyzing and analyzing the ballistic profile, the basic profile of the winged missile and the shape of the Hyflex lift body, The results show that the pitch-dependent damping derivative obtained by adding the damping derivative components is in good agreement with the experimental results obtained by directly solving the forced vibration, and the trend of each damping derivative component with the center of mass is in good agreement with the theoretical prediction.For a winged aircraft, Under supersonic conditions, the time derivative of wash flow plays a dominant role in the pitch-dependent derivative.