直升机旋翼气动试验测力天平原位校准技术

研究了直升机旋翼气动试验测力天平原位校准技术。针对安装于直升机全尺寸旋翼试验塔顶部的机械式多分量气动力测量天平的测量原理和结构特点,确定了基于力叠加原理的组合加载原位校准方法。依其原理研制了原位校准装置,介绍了装置的关键机械结构设计,及基于自适应协同算法的控制系统;研制了高精度微小形变测量系统并评估校准误差;通过旋翼试验塔现场的原位校准试验对校准装置性能进行了验证。结果表明:各力素的原位相对校准不确定度均优于0.1%(k=2),被校系统各分力的相对线性度均优于1%。通过原位校准可获得新的天平工作公式。

On-situ Calibration Technology of Force Balance for Helicopter Rotor Aerodynamic Test

Studied the on-situ calibration method of five-component helicopter aerodynamic measurement balance. According to the measurement principle and structural characteristics of the helicopter aerodynamic measurement balance which mounted on the top of a helicopter fullscale rotor test tower, the researchers determined the on-situ calibration technical scheme of the combined loading based on the principle of force superposition. According to its principle, the field calibration device is developed, and the design of key mechanical structure and the control system of adaptive cooperative algorithm are introduced. A high precision micro-deformation measurement system was developed to evaluate the calibration error. Finally, the performance of the calibration device was verified through the on-situ calibration test of the rotor test tower, and the on-situ relative calibration uncertainty of each force element was evaluated to be better than 0.1% (k=2).