高超声速风洞多天平测力试验技术研究

在同一次试验中通过安装多台天平测量多个部件气动力，可以更加详细地了解飞行器的气动特性，并可以降低试验成本、提高试验效率。多天平测力技术在亚跨超声速风洞中应用已经非常成熟。但是，在高超声速风洞中，由于模型尺寸小、来流温度高，多天平的布局比较困难，所以目前国内在高超声速风洞中进行的多天平测力试验相对较少。为满足型号研制的需要，在 CARDC 超高速所的Φ1m 高超声速风洞上开展了多天平测力试验技术研究。选取某飞行器的3个控制舵为研究对象。针对试验模型径向尺寸小，而轴向尺寸相对较大的特点，确定采用铰链力矩天平轴线与测量舵转轴互相垂直的“纵轴式”布局方式；采用合理的小型化六分量天平结构形式，升降舵天平测量元件的长、宽、高尺寸为20mm×20mm×25mm；为更加真实地模拟天平的工作状态，设计了专用的加载头，并采用单元加载和组合加载相结合的方法进行校准，校准结果表明，天平主要分量的静校准度均在0．7％以内；在采取温度补偿措施之后，零点漂移明显减小；采用了天平-舵偏角变换装置一体化设计，有效提高了定位和安装精度。在Φ1m 高超声速风洞上开展的 Ma＝5条件下的风洞试验结果表明，采用的多天平测力试验技术是可行的，可以应用到高超声速风洞测力试验中。

Technique investigation on force test with multi-balance in hypersonic wind tunnel

The aerodynamic characteristics of aerocrafts can be acquainted with multi-balance which also helps to reduce the cost of experiments and raise efficiency.The force test technique with multi-balance was quite mature in transonic and supersonic wind tunnel.However,it was not widely used in hypersonic wind tunnel because of the small model scale and the high tempera-ture.In order to meet the need for project development,the force test technique with multi-bal-ance investigation was carried out in Ф1m hypersonic wind tunnel of CARDC.Three controlling rudders of the same aerocraft were chosen as research objects.The axes of hinge-moment bal-ances and the rotation axes of the measured rudders were vertical.The rational miniaturized six component balance configuration style was adopted.For example,the sizes of the elevator bal-ance’s measuring elements were 20mm×20mm×25mm.The calibration method of the balances was investigated.The calibration results had shown that the static calibration accuracy of the main components of balances was less than 0.7%;the zero excursion clearly reduced after the temperature compensation methods were used;the integral design of balance and angle transfor-mation device improved the accuracy of orientation and installation in effect.The wind tunnel ex-periment with Ma=5 was performed and the results of typical conditions had been given.The ex-perimental results indicated that force test technique with multi-balance could be used in hyper-sonic wind tunnel aerodynamic test.