The research of the test technology includes the development of jet simulator and ground calibration system

the data correction method and the wind tunnel verification test. Jet simulator with built-in thrust balance and calibration system with ground measurement test capability were designed and manufactured. Three main factors affecting the thrust balance measurement results were analyzed

including additional stiffness effect

pressure effect

and flowing effect. Then

a correction method of measurement data was established through calibration system. After that

a ground experimental study on the thrust and thrust angle of the nozzle with four deflection angles at 0°

5°

10° and 15° was carried out under different nozzle pressure ratios. At last

the jet simulator was installed on the aircraft model in 8m×6m wind tunnel of CARDC

and an experimental study on the longitudinal aerodynamic characteristics with nozzle pressure ratio of 3 was carried out. According to the experimental result

this test technique can be used to measure the thrust

the vector angle and the aerodynamic characteristics of the nozzle. From the measurement result

the effective thrust angle of deflection was the maximum when the nozzle pressure ration was 2. At this point

the actual deflection angle was 10°

and the effective deflection angle can be increased by 3°.When the nozzle was deflected by 10°

the thrust had the biggest influence on the aerodynamic force of the model. The lift coefficient can be increased by 0.066.