飞机螺旋运动测量技术的发展

Development of Measurement Technique for Aircraft Spin Motion

立式风洞是研究飞机尾旋与尾旋改出的特种设施。由于尾旋试验模型的大小受限于风洞的试验段尺寸和流场的边界条件,较难在模型内部安装测量系统,早期均采用外部系统对处于螺旋运动状态的飞机模型姿态进行捕捉、辨识,进而分析飞机的尾旋特性与改出特性。随着材料科学、智能加工技术和信号传输技术的发展进步,测量系统向模块化、微型化和超微型化发展,使得测量机构能够安置于飞机模型的内部,这样不仅可以实时测量数据并记录,不需要到试验后才进行判读和辨识,而且所测量的数据更加完整。

Spin tunnel is a specific facility to investigate aircraft spin and spin recovery. Since the size of aircraft spin model is limited by cross section of test section and flow field boundary condition, it is difficult to set the measurement system inside model. In earlier time, the attitude of spin model was captured and identified by the external system to analyze further aircraft spin characteristics and recovery characteristics. With the development of materials science, intelligent processing technology and signal transmission technology, measurement system is modularized, miniaturized and ultra microminiaturized, and it can be set inside the aircraft spin model. Thus, data can be taken during the tests, interpretation and identification can be carried out simultaneously, furthermore, the measured data is more complete.