A calculation model of the control stick vibration characteristics was set up. Based on the research of helicopter hinge moment

a calculation model of the swashplate control stick load was established. With reference to conventional airplane measurement cells

the measurement cell with enough strength and sensitivity was developed

solving the contradiction between measurement accuracy and flight safety by ground tests. The flight test was successfully conducted

and the important parameter of swashplate control stick load was obtained. The calculation results are basically consistent with experimental data

and the excitation force frequency is close to 1 and 2 times of the main rotor speed. Engineering computation requirement can be achieved

providing a reference for the design and test of helicopter control system.