The longitudinal dynamic characteristics of a 60 deg sweptback delta-wing model at angles of attack of up to 21 deg were investigated in this study using a magnetic suspension and balance system. The magnetic suspension and balance system can obtain wind-tunnel data without support interference by suspending a model using magnetic forces. Wind-tunnel tests during accurate pitch oscillations were conducted, and the dynamic longitudinal forces and moment data were obtained. We proposed a method to accurately identify the dynamic pitching moment during pitch motions from our data using a dynamic derivative model. In our model, the dynamic derivative due to the pitch rate and pitch acceleration were considered, and these dynamic derivatives were treated as linear functions of angle of attack. Multiple regression analysis was used to identify the coefficients in the model. Our model can separately describe the static and dynamic part of the total pitching moment. The dynamic pitching moment coefficients were precisely identified by our dynamic derivative model with consideration of the acceleration term for low angles of attack. In addition, the pitch acceleration term could be considered to have the same effect as virtually changing the moment of inertia of the delta-wing model.

在这项研究中，使用磁悬浮和平衡系统研究了60度后掠三角翼模型在高达21度迎角时的纵向动态特性。磁悬浮和平衡系统可以通过使用磁力悬挂模型来获得风洞数据，而不会产生支撑干扰。进行了精确俯仰振荡期间的风洞测试，并获得了动态纵向力和力矩数据。我们提出了一种使用动态导数模型从数据中准确识别俯仰运动过程中的动态俯仰力矩的方法。在我们的模型中，考虑了由俯仰率和俯仰加速度引起的动态导数，并将这些动态导数视为迎角的线性函数。多元回归分析用于确定模型中的系数。我们的模型可以分别描述总俯仰力矩的静态和动态部分。动态俯仰力矩系数是由我们的动态导数模型精确确定的，其中考虑了低攻角的加速度项。另外，俯仰加速度项可以被认为与虚拟改变三角翼模型的惯性矩具有相同的效果。