Regarding the calculation method for a spring-driven gyroscope in rotating aircraft

The study presents a method for calculating spring-driven gyros used in a coordinator for rotating aircraft. By analyzing the relationship between the dimensions of the spiral spring and the gyro rotor, as well as the characteristics of the spiral spring, the authors develop a mathematical model to describe the motion of the spring-driven gyro during its spin-up and operational phases. Additionally, a method for determining the key kinematic parameters of this gyroscope type is proposed. The simulation results showed that the spring-driven gyroscope has a short start-up time of 0.017 s, a maximum rotational speed of 21,000 rpm, a drift around the outer frame axis not exceeding 5° within 20 s, and a frame-folding time of 60 s. These characteristics meet the requirements for gyroscopes used in rotating aircraft with short operating duration.