Abstract: 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.