Construction of the Stability Region of the Rocket Angular Stabilization System by the Coefficient Method

The article focuses on the challenge of maintaining stability in the flight trajectory of a rocket equipped with aerodynamic rudders, particularly when the dynamic parameters of the rocket undergo significant variations. In such scenarios, where a single system with variable parameters is replaced by a set of systems with constant "frozen" parameters, the study aims to explore the stability of the angular stabilization system. The chosen approach involves utilizing the coefficient method in conjunction with is sufficient stability conditions of automatic control systems. These conditions are expressed through transfer function coefficients, which directly correspond to the physical parameters of the system being designed. The primary advantage of the coefficient method lies in its ability to bypass the complexities associated with calculating characteristic equation roots. By applying sufficient stability conditions, analytical inequalities that delineate the stability region of the rocket's angular stabilization system within the parameter space of control laws are derived. To validate the effectiveness of this approach, numerical simulations were conducted to analyze the dynamics of the angular stabilization system, specifically in the yaw channel of an experimental model of the rocket. These simulations serve to demonstrate the efficacy of the proposed coefficient method for stability analysis.