Helicopter landing aerodynamic characteristic wind tunnel test method

The invention discloses a wind tunnel test method for aerodynamic characteristics of helicopter landing, which adopts a six-degree-of-freedom parallel mechanism to realize ship attitude simulation, adopts a master-slave mode synchronization method to realize synchronous acquisition of helicopter model load and ship attitude, and realizes single-degree-of-freedom or multi-degree-of-freedom combined motion simulation of a ship through computer control. The ship attitude simulation accuracy is improved, synchronous acquisition of the ship attitude and the helicopter load is realized through a master-slave synchronization mode, abundant data can be acquired, and the ship attitude simulation method has important significance for analyzing and researching the influence relationship between the ship attitude and the helicopter load. 本发明公开了一种直升机着舰气动特性风洞试验方法，采用六自由度并联机构实现舰船姿态模拟，采用主从模式同步方法实现直升机模型载荷和舰船姿态的同步采集，通过计算机控制实现舰船单自由度或多自由度的组合运动模拟，提高了舰船姿态模拟的准确性，通过主从同步模式，实现了舰船姿态和直升机载荷的同步采集，可获取丰富的数据，对分析和研究舰船姿态与直升机载荷之间的影响关系，具有重要意义。