Abstract: With the continuous development of flight control technologies, the active side bar is widely studied so as to improve the flight control quality of aircraft. Now, the primary task is to design the active side-stick device that meets the requirements. The forward push, backward pull, left press and right press of the active side-stick are the key technologies to control the pitch and roll of modern aircraft, and are extremely important for the design of the pitching and roll isolation control mechanism of the active side-stick. Therefore, this paper designs the pitching and roll isolation control mechanism of the active lever according to the principle of the two-degree-of-freedom gyroscope. Active side-stick device is an important spare part of aircraft. Both vibration fatigue failure and static strength that meet the requirements are crucial to the successful design of active side-stick. In this paper, the driving rod is simulated from the static strength and mode, and the maximum deformation of the joystick reaches 0.971 56 mm and the maximum stress 109.17 MPa, the natural frequencies of different orders (522.39～1 436.9 Hz) and the distribution nephogram of vibration stress (X direction: 26.624～79.871 MPa; Y direction: 30.751～ 92.252 MPa; Z direction: 28.975～86.267 MPa); The analysis of the simulation shows all results meet the requirements of the material, paving the way for the future research.