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为实现大角度范围、多自由度的机动动作模拟,研发一种低速风洞三自由度动态试验支撑机构,可模拟绕速度矢滚转机动动作以及失速偏离、尾旋等危险飞行状态。该机构通过两自由度转台和旋转曲杆的组合运动模拟飞机模型的三轴姿态变化。基于多体动力学理论,采用拉格朗日乘子法推导出该机构曲杆-飞机模型的动力学数学模型;模型中考虑了机构与试验模型的约束关系、机构摩擦力矩的影响。仿真结果表明:采用该支撑机构,飞机模型可在水平风洞中实现绕速度矢量滚转等典型机动动作;曲杆和试验模型的滚转运动基本同步;曲杆主要影响速率响应的动态过程,摩擦力矩对速率的动态过程和稳态值有一定影响。以上数学建模和仿真验证可为风洞试验提供理论依据。
In order to realize the multi-freedom maneuver simulation in wide-angle range, a three-degree-of-freedom dynamic test supporting mechanism for low-speed wind tunnel was developed. It can simulate the maneuvering motion around the speed-lag and the dangerous flight states such as stalling deviation and tail rotation. The agency simulates the three-axis attitude change of the aircraft model through the combined motion of a two-degree-of-freedom turntable and a rotating crank. Based on the multi-body dynamics theory, the Lagrange multiplier method is used to derive the kinematic mathematic model of the crank-plane model. The model takes into account the constraint relationship between the mechanism and the test model and the influence of the mechanical friction moment. The simulation results show that the aircraft model can realize the typical maneuvering motion in the horizontal wind tunnel, such as the rolling around the speed vector; the rolling motion of the curved rod and the experimental model are basically synchronous; the curved rod mainly affects the dynamic process of the velocity response, Frictional torque has some influence on the dynamic process and steady-state value of velocity. The above mathematical modeling and simulation verification can provide theoretical basis for wind tunnel test.